rocket launching system and support device

专利摘要:
ROCKET LAUNCH SYSTEM AND SUPPORT APPLIANCE. A rocket launch system having components held at high altitudes above the earth by balloons that are lighter than air. The system includes a tubular rocket launch car with traction drives via an electromotive cable carried under a pivot of two ground anchored shafts, raised to a coaxial transfer tube carrying three primary attachment cables whose weight is counterbalanced by balloons. lighter than air. The car is then driven to a docking station supported above ground in the stratosphere by a pair of secondary cables suspended under a fastening structure for tensioning balloons. The carriage is hitched by a carriage end gripper guided by two secondary cables and two tertiary cables and lifted by a lower suspension guided by the secondary cables. This lower suspension is supported by an upper suspension suspended from the tension balloon attachment structure. The car that engages an elevation ring guided by two secondary cables is still elevated, rotated in azimuth and elevation, and the rocket ejection occurs from a (...).
公开号:BR112012020262B1
申请号:R112012020262-6
申请日:2011-02-10
公开日:2021-04-20
发明作者:Howard M. Chin；Kimberly A. Carraha
申请人:Howard M. Chin；Kimberly A. Carraha；
IPC主号:

专利说明:

Cross Reference to Related Orders
[001] This application claims the benefit of provisional patent application US 61/337,645, filed February 11, 2010, under title 35, United States Code, section 119(e), which is incorporated herein by reference in the its entirety. BACKGROUND OF THE INVENTION Field of Invention
[002] The present invention relates to a system for distributing various types of charges to the upper atmosphere and beyond, and more particularly, at a high cyclical rate of launch rate of a rocket launcher with an upper launch station. The weight of the cables themselves is offset by lighter-than-air balloons. The cables are stretched by one or more lighter-than-air balloons and anchored by a rotating chain. Description of the State of the Art
[003] Many methods of dispensing useful materials, such as propellants, life support gases, etc. and items manufactured for the upper atmosphere or beyond exist or have been proposed in recent publications.
[004] These primarily involve rockets powered by earth- or maser-based chemical, nuclear or laser energy sources. Various methods of reducing the cost per unit mass of distributing useful materials and manufactured items to the upper atmosphere or beyond, which involve rockets, exist or have been proposed.
[005] These included reusable rocket-powered vehicles, such as the soon-to-be-retired United States of America space shuttle or the now inoperative Buran, Russian space shuttle. Currently, rockets or chemical multistage vehicles with fixed solid fuel-powered rocket propellers, or rockets such as the small US Pegasus, which is transported to high altitudes before launch, are known to be in service.
[006] Proposed methods to lower the cost of distribution to or beyond the upper atmosphere most commonly involve transferring energy to the rockets, increasing either their initial kinetics or potential energy before igniting the main engine or engines. Proposals by which this can be achieved include: lifting suspended under a disposable, free-flying balloon, lighter than air, or high-speed forced ejection from large pistols using chemical propellants or compressed air or compressed hydrogen or high-speed transport altitudes connected to planes, such as Virgin Galactic's White Knight Two or high-altitude transport towed in a tangled cable behind an aircraft, or, high-speed acceleration using ground-based linear induction motors or, jet or motorized skates prior to departure. ignition of the engine or main engines of the rocket.
[007] A proposed method to reduce distribution cost, which does not involve rockets, is the so-called "Space Elevator", in which a large mass is attached to the earth by a single cable many thousands of kilometers long. The large mass orbits the Earth in a geostationary orbit and holds the cable taut. This cable could then be used in a manner analogous to a railroad track on which a train travels.
[008] The main difficulty with this latter method is that the tensile strength of the material required for the rope far exceeds that of any existing material, especially since the rope's own weight would be considerable. Another difficulty is providing the vehicle climbing this cable with enough energy to essentially break out of most of the Earth's gravitational field. A super strong microgravity of the cable material would be ideal for such a "space elevator", but that doesn't exist yet. Furthermore, the problem of supplying power to thousands of kilometers of cable has led to consideration of radiated microwaves or laser power for the vehicle to climb. The blurring and obstructive effect of clouds and atmosphere on radiant power is likely to reduce the amount of energy actually reaching the climbing vehicle. Energy dissipation in the vehicle's return (climbing) to land is likely to be quite costly due to the need for braking to prevent it from exceeding the speed capability of the mechanism to keep said vehicle on the cable.
[009] Many of the methods proposed today require the development of new materials or massive structures and are unlikely to find commercial service for many decades, if not ever.
[0010] Most current launch methods involve the use of large amounts of energy, derived primarily from fossil fuels such as coal or petroleum for the production of cryogenic liquid oxygen oxidant, cryogenic liquid hydrogen or other liquid hydrocarbon fuels or solid propellants. This use of non-renewable resources is inherently inefficient because at each stage of fuel production there is a mix of process inefficiencies. Also, the sheer mass and sometimes toxic nature of the exhaust material used to propel the vehicle out of the atmosphere often does ecological damage or can cause weather disturbance.
[0011] Therefore, there is a need for a method of dispensing useful materials, such as propellants, life-support gases, etc., and items manufactured to the upper atmosphere or beyond, at a cost per unit mass of distribution, much smaller than currently commercially available, which uses currently available materials and technologies. In addition, it would be ecologically beneficial to minimize the mass of material used to propel the vehicle out of the earth's atmosphere by using hydroelectric, geothermal or solar photovoltaic generated electricity to lift the vehicle as high as possible before ignition of the engine or engines. of the vehicle.
[0012] Atmospheric monitoring has been in place for over 50 years. Measuring solar radiation, residual gas concentrations, temperature, pressure, and other parameters by which the direction of the earth's climate change can be predicted have greatly increased our understanding of our world's climate. Of particular importance in relation to the ozone hole, the continual increase of carbon dioxide and other "greenhouse" gases in the atmosphere, and now, more than fifty chemical species in the Earth's atmosphere.
[0013] As high levels of "greenhouse" gases and ozone depletion occur, such as carbon dioxide, chlorofluorocarbons, nitrous oxide and sulfur hexafluoride, which cause global warming and other changes in global climate, arise a growing requirement for atmospheric monitoring on a more continuous basis. Current methods for monitoring atmospheric conditions involve heavily instrumented, manned and unmanned aircraft; free flight balloons with suspended instrument packs; rockets with sampling and instrument loads; and ground-mounted laser and radar stations.
[0014] These, with the exception of ground stations, cannot provide more than a relatively short sampling period of atmospheric data. The longest duration of monitoring by non-terrestrial methods currently does not exceed more than a few days for balloons, and the shortest one, such as for rockets, can be measured in minutes. Many of these atmospheric monitoring methods also use single-use instrument packages, while existing ground stations cannot obtain physical samples to determine chemical composition, bacterial/viral content, or the intensity and spectral analysis of sunlight and others. data throughout the depth of the atmosphere.
[0015] Thus, there is a need for buildings that extend from the surface of the earth to a great height, in which instrumentation for continuous monitoring and sampling of the atmosphere, and incident solar radiation and others can be mounted.
[0016] Over the horizon radio and radar telecommunications are being more widely used for security reasons by many countries across the world.
[0017] Recent security concerns around the world about surprise terrorist attacks have led countries like the United States of America to increase the level of surveillance with the use of radar and other means of detection utilizing various regions of the electromagnetic spectrum . This is evidenced by the 9/11 Commission Act of 2007 of Congress, in relation in part to the interoperable radio telecommunications system for the security of the United States. The ground radar range is limited by the curvature of the Earth's surface and, in an attempt to achieve greater useful ranges, radar and other systems have been mounted on high-flying aircraft or tethered low-altitude balloons.
[0018] Similarly, cellular radio operators are currently aiming to expand the area served by using high-altitude aircraft, with receivers and transmitters proposed to fly in closed circuits over the service area. Extreme high altitude cases of this are the INMARSAT and IRIDIUM satellite telephony systems which use extremely expensive and irreparable geostationary satellites for telecommunications.
[0019] Thus, it can be seen that there is a need for lower cost for high altitude radar and radio telecommunications platforms.
[0020] The present invention also concerns tourism. Visiting tall monuments such as the Eiffel Tower, tall buildings such as the Empire State Building, or high-altitude natural features such as Mount Everest continue to be a common tourist activity. In fact, recently, non-military interest in expensive high-altitude plane flights has also increased. The recent "X Prize" for a safe flight 100 kilometers or more leased by the Burt Rutan Space Ship One is also aimed at marketing high-altitude transport. One problem with Space Ship One and Space Ship Two is that their rocket engines use a liquefied nitrous oxide oxidizer and solid hydroxyl-terminated polybutadiene fuel, which produces a solid exhaust fuel that includes rubber, partially burned soot, and other materials. harmful. In recent publications, it was found that alternative fuels for Space Ship Two are being investigated, asphalt and paraffin. It is likely that, although these are cheap fossil fuels, combustion will not be complete. Producing polluting exhaust products, in the case of asphalt, metal oxides and sulfuric acid compounds are likely. The effect of soot alone, recently calculated at 1,000 launches per year by Ross Martin of the Aeroespace Corporation, suggests stratospheric disturbance and high temperatures at the Earth's poles. The published release rate being only a few times a week.
[0021] There is therefore a growing market for more frequent and less expensive transport of tourists to higher and higher altitudes.
[0022] In recent years, skydiving as a sport has been changed to include wing-type parachutes with radar absorbing material, the use of auxiliary equipment such as small rigid wings, miniature surfboards, rockets and jet engines, even in miniature. Also, the altitude from which the skydiver is jumping has increased, although this has been limited by two main factors. These are the limited ability of civil fixed-wing aircraft and helicopters to operate at high altitudes where there is a civil aviation half-hour limit for enriched oxygen or breathing systems, a requirement for a pressure or cabin process. In the short term, it is expected that pressurized civilian clothing will become available to skydivers enthusiasts as the market for developing skydivers at high altitudes.
[0023] Even the most extreme forms of skydiving are even now being considered. These proposed ways involve jumping from the upper reaches of the atmosphere or even re-entering from space, as can occur when occupants of endangered orbital spacecraft are about to safely return to Earth.
[0024] Thus, there is a growing market for new, and higher altitude platforms for the various new forms of skydiving. Indeed, there is also a continuing demand for low-cost platforms at altitudes of up to ten thousand feet.
[0025] In recent times, the rapid deployment of aircraft to places of military interest has become practically a necessity, for reconnaissance or other purposes. In addition, there is growing interest in commercial hypersonic transport. To this end, hypersonic aircraft with supersonic combustion engines are being developed in many countries to meet these perceived needs.
[0026] However, aircraft engines, designed to run more efficiently at Mach Numbers, have been reported to require a speed in excess of three times the speed of sound for them to start. Considerable complexity, with a concomitant weight penalty is required for an engine to operate the various flight regimes from stationary to hypersonic. In addition to using rockets to achieve starting speed, the other path designs seem to require a two-part engine. The first part is a turboprop or a turbojet, which predominates in the subsonic to supersonic low Mach number flight regimes, the transition to the supersonic combustion engine in high Mach numbers, and closing the first part.
[0027] Motors designed to work in the only hypersonic range, many without moving parts, would therefore be lighter in weight, simpler in construction, and, consequently, less expensive.
[0028] In 2003, the crew of the space shuttle Columbia of the United States of America was destroyed upon re-entry into Earth's atmosphere, due to structural damage that occurred during the launch phase. Thus, over time, there has also been an accumulation of orbital spacecraft in need of repair; and endangered orbital craft and dangerous debris that need to be removed from orbit.
[0029] Since these craft, such as the US space shuttle Columbia, are heavy, and they do not have main engines that can operate for significant periods of time after re-entry due to the danger and weight penalties of carrying cryogenic fuels or Others for use on the return flight into the atmosphere, these craft must leave orbit at specific points so that they may be able to glide to the few airports with runways of sufficient strength and length that exist close to their orbital range.
[0030] Thus, it is inevitable that others will create small craft capable of carrying out useful work outside the atmosphere, with the ability to fly with their own strength in sustained subsonic, supersonic or hypersonic flight in the Earth's atmosphere. These are likely to be launched using rocket energy and, upon re-entry at any point, fly to any of the many existing civil or military airfields suitable for such smaller aircraft, and land safely.
[0031] These will be used for the quick and safe recovery of passengers from damaged orbital craft and repair or removal from orbit of unmanned orbital craft in distress, and unpleasant and dangerous debris. Another type, soon to be put into service, is a small service vehicle for refueling or securing a spacecraft in distress and acting as a tugboat to extend the life of those vehicles. Additionally, small spacecraft or rockets can be used to launch small satellites or modular components for assembling and supplying large buildings in orbit that can be used to escape the Earth's gravitational field, possibly dodge dangerous asteroids, or explore the solar system . The European Space Agency and the Russian equivalent of Roscosmos have recently begun to consider creating a shipyard below Earth's orbit to facilitate missions to the Moon or Mars using yet-to-be-built advanced re-entry return vehicle (ARV) ).
[0032] In addition, it is expected that there will be a continuing need for service satellites and other orbital craft. This service may include delivery of food, fuel, compressed or liquefied gases for breathing or other uses, medical and scientific supplies, mechanical, electrical or other equipment to replace or upgrade space systems, transporting sick or injured people or replacing personnel.
[0033] Thus, it is expected that there will be a need for a fast and inexpensive means of modular launch components for assembly and fueling in space, small utility spacecraft, small satellites and other devices.
[0034] The sensitivity of many telescopes used in astronomy has been largely degraded due to atmospheric dust and aerosols as light is reflected or scattered by the aforementioned particles. The affected smaller telescopes are usually found in the upper reaches of remote mountains, above much of the atmosphere where most of the dust and aerosols are found.
[0035] Thus, there is an additional need for high altitude platforms on which sensitive telescopes can be mounted. In particular, various platforms and telescopes can be used to simulate an extremely large aperture telescope, as currently used to locate planets in other solar systems.
[0036] As the Indonesia tsunami disaster revealed in December 2004, it was clear that reconnaissance of many of the affected areas and subsequent delivery of initial supplies did not take place until days or even weeks after the event, with the result that many tens of thousands more people died than if advance help was available. Thus, there is a need for a rapid suborbital rocket launch system to deliver numerous small unmanned reconnaissance remote controlled aircraft and thousands of tons of GPS-driven terminally-driven parachute aid supplies delivered using single GPS-driven disposable rockets. BRIEF SUMMARY OF THE INVENTION
[0037] Therefore, there is a need for a method of dispensing useful materials, such as propellants, life-support gases, etc., and items manufactured to the upper atmosphere or beyond, at a cost per unit of mass distributed which is much less than currently commercially available, which uses currently available materials and technologies. In addition, it would be ecologically beneficial to minimize the mass of material used to propel the vehicle out of the earth's atmosphere through the use of hydroelectric, geothermal or solar photovoltaic electricity or other renewable energy source to raise the vehicle as high as possible before engine ignition or vehicle engines.
[0038] An objective of the present invention is to provide a high launch rate rocket launcher for sending payloads to space, as well as for satellites located in space.
[0039] Yet another objective of the present invention is to provide a high launch rate rocket launcher that may use hydroelectricity or other renewable energies to raise the rocket to launch altitude.
[0040] It is another objective to use a more ecological and oxidizing fuel made using alternative or renewable energy.
[0041] Yet another objective of the present invention is to provide an upper pivotal launch station using electrical tubular launch cars, the launch station being connected to earth by cables that are connected to lighter-than-air balloons for tensioning and supporting the cables and associated structures.
[0042] Another objective of the present invention is to provide a means for the recovery of potential energy involved in the return of empty rocket launch cars, after launch, to the earth, through currents, through regenerative deceleration using generators. engine for reuse.
[0043] Yet another objective of the present invention is to provide atmospheric monitoring on a more continuous basis, as increased levels of "greenhouse" gases or other pollutants in the atmosphere cause changes in the global climate.
[0044] Another objective of the present invention is to provide high altitude radar and radio telecommunications platforms to greatly increase the spatial volume and surface area of the earth, respectively covered.
[0045] Another objective of the present invention is to provide reasonably priced commercial and continuous access for tourists to visit atmospheric levels inaccessible by other means, with the exception of rockets, airplanes or aircraft lighter than free-flying air.
[0046] Yet another objective of the present invention is to provide platforms at higher altitudes than are currently available for the various new forms of extreme altitude or space skydiving, as well as low-cost platforms at heights up to ten thousand feet that can be accessed no supplemental oxygen or a pressure suit.
[0047] Another objective of the present invention is to provide a quick and inexpensive means of launching small utility craft for safe recovery of passengers from the damaged orbital vessel, repair, upgrade or removal of the unmanned orbital craft from orbit and unpleasant and dangerous debris.
[0048] Yet another objective of the present invention is to provide high altitude platforms above the cloud layers on earth, on which sensitive telescopes can be mounted, especially those that can combine by computational means, electromagnetic waves, including light and radio waves , received in such a way that they act as a single telescope of a diameter equal to the distance of the outermost members of the array, for observations superior to what is currently available, except from space.
[0049] Another objective is to provide a means for service satellites and other orbital craft, for example, to provide food, compressed or liquefied gases for breathing or other uses, fuel, medicine and scientific materials, electrical, mechanical equipment or others to replace or improve spacecraft systems, and for transporting sick or injured people, or replacing personnel.
[0050] It is an objective to provide a transport system for transporting rocket-laden cars along cables that extend upward through the atmosphere to a launch station.
[0051] It is an additional objective to provide cars for transporting rockets along cables to a launch post located high in the atmosphere.
[0052] It is still an additional objective to provide an apparatus for holding and directing rocket loaded cars, the apparatus for the transmission of cars along the cables to a launch station located high in the atmosphere, and for the transmission of empty cars to from the launch station to the ground.
[0053] However, another objective is to provide a system for securely storing rockets and for distributing the rockets or rocket-laden cars to the apparatus to hold and direct the rockets or rocket-laden cars to the apparatus to transport the rockets or loaded cars of rockets to a launch station located above in the atmosphere.
[0054] The arrangement of the apparatus for the transmission of cars loaded with rockets is also an object of the present invention.
[0055] Another object of the invention is a system for driving rockets, rocket components, rocket cars and/or rocket transport device support from a storage facility to an exploration and assembly facility, for subsequent transport for the device to lift the rocket-laden car to a launch station.
[0056] It is another object of the present invention to provide a transverse loader for cars loaded with rockets.
[0057] A further objective is the provision of a lift assembly for lifting a rocket-laden car in apparatus for carrying a rocket-laden car on a set of raised cables to a rocket launch station.
[0058] It is a further objective to provide a small tower for receiving a rocket-laden car, and related apparatus for guiding a rocket-laden car to a guide structure apparatus for disposing the rocket-laden car on the cables routed to the launch station.
[0059] It is yet another object of the invention to provide devices for connecting lighter-than-air balloons to a cable system to stably hold and separate the cables that are routed to the launch station.
[0060] Another objective of the invention is to provide a docking station for anchoring a rocket loading car on a set of cables that go to the launch station.
[0061] The objective of providing electrical energy for transporting a rocket-laden car along a cable system to the elevated launch station is another objective of the present invention.
[0062] Another objective of the present invention is to provide a lifting ring for lifting a rocket-laden car along the cable system above the docking station.
[0063] A further objective is to provide a device for separating cables from the ground for an elevated launch station, and for stabilizing the cables.
[0064] It is also an object of the present invention to provide a connecting apparatus for securing structures and other cable apparatus extending between the ground and an elevated launch station.
[0065] The provision of an apparatus for holding a rocket inside a car is also an object of the present invention.
[0066] Another objective is to provide a telescope mount for use with a set of cables held vertically in the atmosphere.
[0067] The provision of a rocket being carried upward in a car to hold one or more people, or equipment and supplies, is also an object of the present invention.
[0068] A further object of the present invention is an improved hydrostatic pressure compensating suit to be worn by a person to allow for resistance from high accelerations during rocket launch and re-entry into the atmosphere.
[0069] These objectives are achieved in accordance with the preferred embodiments of the invention discussed below. Other objectives will be evident to skilled artisans from the inventive concepts as discussed below and from the appended claims. BRIEF DESCRIPTION OF THE DRAWINGS
[0070] Fig. 1 schematically illustrates some of the features of a preferred embodiment of the rocket launch system, according to the invention.
[0071] Figs. 1A and 1B are detailed views of the features shown in Fig. 1.
[0072] Fig. 2 is a schematic view showing the assembly and the base loading portion of the launcher system, according to the preferred embodiment of the invention.
[0073] Fig. 3 shows the loading of a rocket on a side transport device, according to an aspect of the preferred version of the invention.
[0074] Fig. 4 is a schematic view showing a different view of a car holding a rocket, a tipping mechanism and a side transport device.
[0075] Fig. 5 is a schematic plan view showing a circuit with rails for cars, storage rail, rocket mounting and safety stations, cars, fuel storage devices and an electrical supply system related to preparation of rockets for launching, according to the preferred embodiment of the invention.
[0076] Fig. 5A is an enlarged detail of a portion of rails illustrated in Fig. 5.
[0077] Fig. 6 shows in schematic form, the loading of a rocket in a fuel feed or in the assembly compartment, according to a preferred embodiment of the invention.
[0078] Fig. 7 shows a detail of a transverse loader as shown in Fig. 6.
[0079] Fig. 7A is an enlarged perspective drawing of a detail of a twist lock pin and pin shown in Fig. 7.
[0080] Fig. 8 is a schematic view showing the operation of a lifting assembly of the preferred embodiment of the invention, with a side transport device, and a rocket safety car.
[0081] Fig. 8A is an enlarged detail view of a version of an apparatus for supporting a turntable for rotation.
[0082] Fig. 8B is an enlarged detail view of another version of the apparatus for swivel support 72 for rotation.
[0083] Fig. 9 is a schematic view of a lifting assembly, a rotating bed, a side transport device, a portion of a carriage, according to a preferred embodiment of the invention.
[0084] Fig. 9A is an enlarged perspective view of a tapered alignment pin.
[0085] Fig. 9B is an enlarged perspective view of a fractional twist locking pin.
[0086] Fig. 9C is an enlarged detailed view of the base of a car.
[0087] Fig. 10 shows the apparatus for receiving, aligning and initiating the insertion of a carriage to fasten a rocket to the cable, according to the preferred embodiment of the invention.
[0088] Fig. 10A is an enlarged detail view of a cable spacer.
[0089] Fig. 11 shows a further portion of the preferred part of the invention, with respect to the cable system for transporting rocket-arresting cars.
[0090] Fig. 12 is a detail of the upper portion of the preferred form of the invention, schematically showing a balloon assembly for lifting a cable assembly and the parts disposed therein, according to a preferred aspect of the present invention for the lifting the car from holding the rocket.
[0091] Fig. 13 is a schematic view of an upper part of a preferred part of the present invention showing a portion of the cable assembly, and the different components connected thereto.
[0092] Fig. 13A is an end view of a carriage with an end cap in the open position.
[0093] Fig. 13B is a perspective view of an end of the carriage for use in the apparatus shown in Fig. 13, and Fig. 13C is a side, partially cross-sectional view of the carriage showing operating positions of some of the its components.
[0094] Fig. 14 is a schematic cross-sectional view of the preferred embodiment of the invention, showing a cable assembly and the different parts that accompany it.
[0095] Fig. 14A is an enlarged detail view of a part of a carriage end claw.
[0096] Fig. 15 is a schematic view of a preferred embodiment of the invention, showing a stabilizing portion for the balloons and cable assembly.
[0097] Fig. 15A is a detailed view of a portion of the stabilizing portion for the balloons shown in Fig. 15.
[0098] Fig. 15B is an exploded perspective view of connecting an upper spacer to a cable, and Fig. 15C is a plan view thereof.
[0099] Fig. 15D is an enlarged perspective view of the cable clamp structure by means of a spacing mounting arm.
[00100] Fig. 15E is an exploded perspective view of connecting a lower spacer to a cable and a large harness.
[00101] Fig. 16 is a schematic detailed plan view of part of the stabilization portion of the preferred form of the present invention, taken in the direction 16-16 in Fig. 15.
[00102] Fig. 17 is another detailed view of a part of the stabilizer part of a preferred embodiment of the invention, taken in direction 17-17 in Fig. 15, showing certain force vectors.
[00103] Fig. 18 is a schematic perspective view of a stabilization assembly with thrusters, according to the preferred embodiment of the invention.
[00104] Fig. 19 is a perspective view of a cable stabilization device, according to a preferred form of the invention.
[00105] Figs. 20A and 20B are side views of two of the many lighter-than-air balloon assemblies connected to a cable assembly, in accordance with preferred forms of the invention.
[00106] Fig. 21 is a perspective view of a multi-stranded cable as may be used in the cable of the launching system, in accordance with a preferred form of the invention.
[00107] Fig. 22 shows the construction for assembling items to the side of a cable as shown in Fig. 21.
[00108] Figs. 23 and 24 are cross-sectional views of variations of the construction shown in Fig. 22.
[00109] Fig. 25 shows a cross-sectional view of the coupling of a cable by the wheels of a traction unit for driving up or down said cable, according to a preferred form of the invention.
[00110] Fig. 26 is a perspective view of a retractable arm assembly, according to a preferred embodiment of the invention.
[00111] Fig. 27 is a detail showing a retractable arm assembly for holding a rocket in a car, according to the preferred embodiment of the invention.
[00112] Fig. 28 is a schematic view of the upper portion of a preferred embodiment of the invention of rocket launch if a telescope is to be mounted on top of the main lift balloon or balloons.
[00113] Fig. 28A is a perspective view of the upper portion of Fig. 28.
[00114] Fig. 28B is a detailed cross-sectional side view in enlarged detail of a portion of the apparatus shown in Fig. 28, including a generated rotation drive system and a ring bearing, and Fig. 28C is taken in the direction 28C-28C in Fig. 28B, and showing how generally cables can be terminated.
[00115] Fig. 29 shows a possible telescope assembly for use in the mode shown in Fig. 28, being the view in a detailed perspective.
[00116] Fig. 30 is a schematic view of a single person launching rocket with adequate space, according to a preferred embodiment of the invention.
[00117] Fig. 31 is a variant of the rocket of several individually releasable capsules or people suited to space.
[00118] Fig. 32 shows a person suited to the proper space in a detachable reentry structure using an aeroclip for the initiation of the shock wave.
[00119] Fig. 33 shows another variant of a detachable reentry structure using an aeroclip for the initiation of the shock wave.
[00120] Fig. 34 is a schematic diagram of a spacesuit to be worn by an occupant, in accordance with a preferred embodiment of the invention, for use in exiting and re-entering the atmosphere.
[00121] Fig. 34A is a detail of the spacesuit helmet shown in Fig. 34, and Fig. 34B is an additional detail of the spacesuit helmet of Fig. 34.
[00122] Fig. 35 shows an apparatus for a method of varying the internal volume of a spacesuit shown in Fig. 34.
[00123] Fig. 36 is a detailed view of a person's limb inside a portion of the spacesuit of Fig. 34.
[00124] Figs. 37 and 38 show re-entry-capable aerospace aircraft versions of rocket assemblies mounted on top of rockets, one with extended wings and one with folded wings for transport within a car, in accordance with a preferred embodiment of the invention.
[00125] Fig. 38A is a pictorial view of a body lift-type aerospace lift plane with bent lift and control structures for use with a preferred embodiment of the invention.
[00126] Fig. 39 is a schematic view of a satellite or other payload carried out in a rocket, according to part of a preferred embodiment of the invention with aerodynamic and ejectable protective shields.
[00127] Figs. 40 and 41 show a perspective and cross-sectional view of a rod as a type of cable, to be used in place of a steel cable. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS OF THE INVENTION
[00128] The preferred embodiment of the invention is initially described in general terms referring to some components described in greater detail below. General components are shown in such general terms in Figs. 1, 1A and 1B. The preferred embodiment is a rocket launch system 1, which includes apparatus for moving a rocket 18 to be launched. The rocket 18 is first either in a container or in a rocket transport device, such as a car 20 or is being loaded onto the car 20 from storage supports 7. The cars 20 have cylindrical holes longitudinally within continuous tubes. open-ended 836 (Figs. 13, 13C), which are arranged and held in place for receiving a rocket 18. Carriers 20 are weatherproof and have a longitudinal axis, which is the same longitudinal axis as the tube. 836. The rockets 18, their components, and carts 20, which may or may not be loaded with the rockets 18, are transported to storage racks 7 by a suitable transport rail car on a railway 3 to a loading area outside 5. A crane 48 respectively transports the rockets 18, and/or the cars 20 and/or a rocket component 18 travels or is used to maintain the various parts of the rocket launch system 1 on crane tracks relatively narrow 78. Rockets 18 may have fins 21 (Fig. 7), and each carriage 20 has internal supports in addition to tube 836.
[00129] A cross loader 50 travels on the rails 90 in the directions indicated by arrows A of Fig. 1A, the rails 90 being located farther apart than the crane rails 78. The cross loader 50, which is preferably used for transferring rockets 18, cars 20, etc. from storage brackets 7 to mounting or fuel compartments 10, includes trucks 92 for moving on rails 90, and has a wheeled truck 98 movable on a pair of transverse rails , parallel 97 at the top of the beams 96, and an elevator assembly 100 connected to a wheeled truck 98. The crane 48, which is preferably used to perform maintenance on the launch system, can also be used to remove the rockets 18, and/or cars 20, etc. of the storage brackets 7, and transferring the rockets 18 and/or the cars 20 to the mount/fuel compartments 10 (could normally be a plurality of mounting compartments 10). Elevator assembly 100 moves on rails 97 in the direction indicated by arrows B. Carriage 20, which may or may not have been loaded with a rocket 18 in one way or another, is placed in compartment assembly 10. The entire operation is controlled by suitable control equipment at a local launch control or fuel control systems 120.
[00130] Referring to Figs. 1A and 2, a side transport device 46 transports the car 20 with rocket 18 loaded thereon along a set of rails 17 arranged in the below ground paths 14 and 14a, which are located between the vertical walls 16. The path 14A ( also referring to Fig. 5) leads to a closed loop track 15 also having tracks 17. The side transport device 46 moves in the direction shown by arrows C. The side transport device 46 transports the car 20 with rocket 18 a a launcher 119 which includes a lift assembly 60. The lift assembly 60, referring to Figs. 8 and 9, includes an upper turntable mechanism 61. The carriage 20 is elevated to a turntable mechanism 63 above the ground. Turntable mechanism 63 includes a turntable base 122 and a cannon assembly 123 (Figs. 8, 10, 11). The cannon assembly 123 comprises a turntable 72, a lower guide tube 124 and a secondary guide structure 125, the latter being operatively connected to a set of primary transport and power cables 27.
[00131] The primary cables 27 are electrical energy suppliers for the rocket loaded cars 20 being transported on them. Electric power could be supplied by one set of electrically conducting cables, and the cars 20 could be transported by a second set of strong carrying cables. However, the electrical power lines and the rocket transport lines have been combined into an integrally set of primary transport and power cables that function simultaneously as an electrical energy carrier and to support the rockets (preferably in cars to transport the rockets. said cars to and from high altitudes). The primary cables 27 have a lower end portion at or near the secondary guide structure 125 or turntable mechanism 63 and an upper end portion which, when in use, is at high altitudes. Said primary transport and energy cables 27 are preferably three in number for the realization of three-phase electrical energy. The primary cables 27 referring to Figs. 1, 1B, 11, 12, 13 and 14, are connected to a docking station 166, from which a set of secondary cables 184 extends. The cables 184 operatively guide a lifting ring assembly 182, which is adjusted to a suitable height above docking station 166, as the preselected launch azimuth angle is set with carriage 20 engaged by lift ring assembly 182 and a portion of top ring 172 of docking station 166. After being lifted out of engagement with the top of the ring 172 and released from a carriage end claw 196, the lift ring assembly 182 is adjusted to the preselected lift launch angle. Elevation ring assembly 182 is positioned above docking station 166 and located at altitudes significant for the final step in rocket launch 18 as explained below.
[00132] The cables 27, 184 and any other cables are supported to the upper atmosphere by a series of balloons lighter than air 164 and 160, the balloons are composed of a sheath element attached to a gas lighter than air . Said lighter-than-air balloons 164 are connected to said primary cables 27 intermittently along the length of said primary cables 27 to cumulatively support the own weight of said set of primary cables 27 and any structures made by said primary cables 27. Balloons 160 support the otherwise unsupported portion of cables 27, and any structures connected thereto and all structures and assemblies from and including docking station 166 up to said balloons 160, and tension cables 27 and 184, so that they can carry a payload. The cables 27 are separated from each other by a set of spacers or stabilizer set 158. (The cables have been shown throughout most of the description as cables, but could be rods as explained later).
[00133] Each rocket mounted 18 inside the car 20 is transported from a housing assembly 10 into the lower guide tube 124, then to the secondary guide structure 125, and thence to the docking station 166, by means of a drive structure, which may be a driven traction assembly 26 as shown in Figs. 9 and 9C incorporated into carriage 20. Cart 20 travels along and has an electrically moved energizing apparatus to derive energy from primary cables 27, whose own weight is periodically compensated by balloons lighter than air 164 and which are attached by balloons lighter than air 160. Balloons 160 and 164 preferably have sloping sides, as shown in Figs. 1, 11, 20A and 28; Cylindrical sides, as shown in Fig. 20B, can either be spherical or very well have other shapes. High altitude balloons are well known and are continually being developed and improved. Appropriate balloons 160 and 164 should preferably remain functional in applications for the present invention for many months and optimally per year. Balloons to go into the stratosphere have been known and used since the 1950s. The 20 car is still raised along with the secondary cables 184 and rotated and then tilted according to predetermined amounts as discussed below, after the rocket has been 18 launched.
[00134] The above description presents an overview of the components of a preferred form of the invention. Set forth below is a more detailed discussion of the invention in its preferred forms.
[00135] Rockets 18 and their respective payloads are assembled, loaded into cars 20 and fed if necessary, and kept in a set of explosion-resistant compartments 10 prior to launch. Each compartment 10 is located below the ground surface and is constructed so as to limit damage in the event of an accidental detonation of a rocket propeller 18. Each compartment 10 has an inverted surface in the form of an inverted frusto-cone 12 reference to Figs. 2 and 11 of a cone made of a suitable reinforcing concrete material or the like to limit the effects of any such explosion by upward and lateral deflection. Each compartment 10 is connected via belowground paths 14 and 14a to closed loop path 15. Path 14 terminates in an open sloping chute 86 (Fig. 6) with upwardly sloping wall 16A (Fig. 2) facing into the side opening of compartment assembly 10. This deflects any side component of the possible explosion from compartment 10 up and away from support apparatus (structures, equipment) for launching system 1, and personnel. Path 14 then rotates approximately 90 degrees to join path 14A. Each compartment 10 is capable of holding the rocket 18 within a car 20. Each rocket 18 may comprise a short-lived rocket motor amplifier for ejecting the rocket 18 from its open-ended continuous tube 836 (Fig. 13A ) inside car 20 with a speed such that, even if the rocket's main engine fails, the short-lived rocket engine amplifier and the rocket 18 will not fail and damage the rocket launching system 1. The engine amplifier The rocket would operate only within confinements resistant to the heat and pressure in which it is held, as described below. Each rocket 18 has one or more main engines to drive the rocket 18 for its speed model.
[00136] Each carriage 20 has opposite end openings 24 (Figs. 9C, 13, 13A), and retractable membranes or impermeable end caps 30 (Figs. 9C, 13, 13A) at both ends thereof to protect rockets 18 inside car 20, while car 20 travels from land through the atmosphere. These covers 30 can be moved to open both ends of carriage 20 or retracted membranes 30 to also open both ends of carriage 20, as shown in Fig. 13A. Also within opposing end openings 24 are reversible variable pitch thrusters 31 hinged parallel to a carriage side 20 so that they can be rotated to a position perpendicular to the ends using actuators 29 (Figs. 13B, 13C). Each carriage 20 has multiples of three traction units 26 (Fig. 9C; discussed in detail below) equally spaced around the periphery of carriage 20 for the purpose of gripping and pulling the respective carriage 20 to equally spaced primary power cables 27 Cables 27 and 184 suitably have high tensile strengths and conductivity, as discussed below. Traction units 26 are powered by the above three equally spaced primary power cables 27, the cables 27 carrying three-phase power from which the traction unit 26 receives power. Drive units 26 are reversible, using electrical energy to lift the car 20 or generating electrical energy when used as regenerative brakes. Traction unit 26 operates in regenerative braking mode converting the kinetic energy of car 20, as it is lowered, into electricity which is fed back to cables 27, which recovered electricity can be used to assist in capturing other cars. loaded into adjacent launch systems 1. Traction units 386 (Fig. 28) and 26 (Fig. 9C) operate in a similar manner. The interior of the car 20 is designed to be able to withstand heat, and the effects of explosion caused by the operation of the short-lived amplifier rocket engine. The end caps or membranes 30 (shown in detail in Figs. 9C and 13A) protect the rocket 18 trapped in car 20 from any inclement weather and may contain inert or relatively inert gases such as nitrogen to inhibit the combustion of any materials Reactives that escape from rocket 18 during transport to the high-altitude launch position. Carriage upper end 20 may have twist pin locking receptacles 32 (Fig. 13A) similar to split rotation twist pins 154 (Fig. 9) (discussed below) to receive twist lock pins 204 (Figs. 12 and 13) similar to fractional rotational torsion locking pins 144 (Fig. 9) (also discussed below), which are used to lift cars 20 in preparation for a rocket launch process as discussed below.
[00137] Each car has 20 internal retractable arms 34 or 35 (Fig. 26, 27) that hold the rocket securely inside the car 20, such that the centers of gravity 36 and 37 (Fig. 13) of the car 20 and rocket 18, respectively, are stably positioned in the car means 20 at its center of gravity. Small elastomeric or pneumatic wheels 372 (Fig. 27) can be attached to the periphery of the rocket to help prevent frictional contact between the rocket and the interior of the car 20 during ejection if the rocket's thrust vector does not exactly pass through of the rocket's center of gravity. Retractable arms 35 and associated parts are discussed below.
[00138] Referring to Figs. 3 to 6 there are different ways in which rockets 18 could be loaded onto cars 20. In one version, a rocket 18 is initially mounted horizontally, inserted into car 20, and initially placed on a wheeled loader 38 (Fig. 3) in the direction indicated by arrow D. Carriage 20 is then placed in a hydraulic rotor 39, rotator 39 having a swivel bed 40 otherwise or hydraulically mounted between guard 41 for rotation about pins 42 by means such as a hydraulic actuator 43 (or some other suitable actuator). The hydraulic actuator piston rod 43 is almost entirely retracted into the cylinder since carriage 20 has only passed over the piston and cylinder. Counterweights 44 are designed from each of the four corners of a bed 40 so as to cause the center of gravity of the bed 40 to be coincident with the axis of rotation of the pins 42 and with the center of gravity of the rocket 18 and assembly. of carriages 20 - thus reducing the actuating force that the hydraulic actuator 43 or other means of rotation, has to exert. Rockets 18 could have been placed inside horizontally oriented carriages 20 of side transport devices 46 (or similar conveyors) prior to rotation to a vertical orientation by hydraulic rotors 39, or rockets 18 could have been placed within previously situated strong carriages 20 on the side transport devices 46 in the compartment set 10 by means of transferring the loader 50. Referring to Fig. 6, the cross loader 50 or crane 48 can be used to transfer empty carts 20 to prepositioned side transport devices 46 as explained below, in the set of compartments 10, after which the loader 50 or crane 48 would load a rocket 18 into the car 20.
[00139] Side transport devices 46 are shown in Figs. 1-6, 8, 9 and 10. Side transport devices 46 travel along tracks 14, 14A and track 15 on tracks 17. Track 15 forms a closed loop that passes under an above ground turntable mechanism 63 (Figs. 1A, 8, 10, 11 discussed below) and transports cars 20 each loaded with a rocket 18 from the explosion-resistant housing assembly 10 to the lift assembly 60 as shown in Figs. 2 and 8, and, as well as transporting empty carts 20. Each side transport device 46 has a platform 54 (Fig. 9) with a generally triangular cavity 56 (Fig. 2, 4) for receiving the end of a cart 20, so that carriage 20 is in a vertical position, with the outer edges of carriage fitting 20 in recess 56. Side transport device 46 is shown having independent steerable wheels 58 (Fig. 9) for moving the side transport device 46 on rails 17, and further has a suitable steering mechanism to allow side transport device 46 to travel along paths 14 and 14a, and track 15. A suitable locking mechanism, which may include tapered alignment pins 142 (Fig. 9, discussed below), and fractional rotation torsion pins 144 (Fig. 9, discussed below), are provided to lock carriage 20 in recess 56 in platform 54. Side transport devices 46 still have similar containers found.at the bottom of carriage 20 to receive alignment pins and fractional rotation torsion pins 144, as explained below, to releasably secure devices 46 to upper swivel mechanism 61 which as stated above is part of a lifting assembly 60, as described further evening.
[00140] Along a portion of track 15, a series of rockets 18 and its variants, and other items such as side transport devices 46, cars 20 and variants such as pressurized tourist cars and launch system service cars are stored on storage brackets 7, which are divided by 64 walls. Rockets 18, if not using solid fuel, can be powered during storage support 7 or, preferably, in compartment assembly 10, using various propellant combinations, such as liquid-liquid or liquid-solid fuels, depending on the type 18. A highly high thrust specific propellant combination is liquid oxygen (LOX) and liquid hydrogen (LH2), which can be stored in storage tanks 65 and 66, respectively, as shown in Fig. 5.
[00141] This fuel combination can be produced in a more environmentally beneficial way, using a system in which one or more hydroturbines provide mechanical energy and possibly other hydroturbines drive electrical generators 62 that are included in a power plant 468. hydroturbine(s) receives water from an appropriate source, such as a river with sufficient pressure and mass flow rate, to generate an electrical substation 70 from coupled electrical generators 62, and directly drive compressors as found in gas installations of liquefaction, such as a water electrolysis and gas liquefaction sub-installation in facility 74. Electric power from substation 70 can be used to operate the water electrolysis sub-installation in facility 74, and can be used to supply auxiliary power for an orientation hydroturbine of the gas liquefaction sub-installation at facility 74 to liquefy oxygen (O2) and hi resulting hydrogen (H2), which are respectively stored in the LOX 65 storage tank and the LH2 66 storage tank, as well as the electrical energy to be used to power all other parts of the launch system 1 and the its support device requiring such energy. Other energy sources such as nuclear fission can be used as an alternative in the case of hydroelectric and hydro turbines derived from the horse power shaft are not available. Renewable energy sources such as geothermal, hydro or solar energy are preferred.
[00142] As explained above, rockets 18 are transported on the ground while contained within carriages 20. Side transport devices 46 can move along paths 14 and 14A, and track 15 on parallel rails 17 is relatively narrow (in comparison with rails 90 discussed below). An empty cart 20 in the storage bracket 7 is shown in Figs. 5 and 6 beside an empty side transport device 46. Also shown in Fig. 5 is a pressurized tourist transport variant, a service car vehicle variant, free balloon containing cars or an aerospace touring space passenger car 76. Rails 78 and a pair of rails 90 (discussed below) (Figs. 5 and 6), running parallel to opposite straight parts of track 15, are used for crane movement 48 and loader transfer wheels 50. Empty carriages 20 are shown at the top of side transport devices 46 moving along track 15, from which they can be removed for reconditioning or reloading.
[00143] The charging system is shown in greater detail in Fig. 6. The storage bracket 7 each holds both complete rockets 18 and/or rocket parts making up 18, shown as rocket parts 18A, 18B and 18C , and/or a flat space for aerospace tourism 76 (Fig. 5), and/or empty cars 20 or replacement side transport devices 46. Parts of rockets 18A-18C can be combined for a final rocket 18, but the invention it's not that limited. Rockets 18 with the respective rocket parts 18A-18C are sent to their respective places by means of convoys 3 (see Fig. 1), which rockets 18, rocket parts, etc. it could come from distant factories around the world. The carriage 20 and a side transport device 46 are also shown on the support 7. The crane 48 can travel on rails 78 to mount the rocket parts 18A-18C in a compartment within the storage supports 7 and then on a of cars 20. Crane 48 can also be used to repair lanes 14 and 14a, and track 15. Crane 48 has a cable 49. Crane 48 using its cable 49 with suitable lifting means can lift the mounted rocket 18 and take it to compartment 10 (left part of figure. 6) for insertion into a pre-located cart 20 on top of side transport device 46. A crane 48 is required in addition to other service equipment noted above, for the maintenance of rails 17, 78 and 90 and gutters 97 (discussed below). Care must be taken when using crane 48 for transferring rockets 18, as the cables of the crane 49 tend to sway during the transfer and the rocket suspended on the cable 49 can be damaged.
[00144] As explained below, there is always a risk of accidental detonation of a rocket 18 in compartment 10 if highly reactive oxidizing fuel combinations are used. In order to protect the various structures, equipment and personnel from the blast effects of such detonation, a pair of parallel, inverted L-guide members 80 (Fig. 6) extend over the opposite edges of compartment 10. Each The pair of guide members 80 has an explosion cap 82 slidable in the direction indicated by arrows E, and the explosion cap 82 is slid under the overlapping flanges 84 of the guide members 80 before filling. The explosion cover 82, once located under the flanges 84, cannot be moved even if an explosion occurs. The explosion cover 82 is made of such material not to be destroyed, even if it must withstand an explosion within the compartment 10 during assembly, fuel feeding or otherwise, the explosion being directed away from components. critics through trough 86.
The transverse loader 50, shown in Figs. 1 and 6, is part of a rocket loading system 88 including the pair of ring trucks 90 (wider than the crane rails 78 48) on which the pair of wheel trucks 92 mounts. A guide assembly 94 comprises beams 96 and wheel trucks 92 extends over wide rails 90 and touring trucks 92, which move on wide tracks 90. Guide assembly 94 has parallel rails 97 as shown in Fig. 7 on top of the beams 96 through which lift assembly 100 travels. The entire transverse loader assembly 50 on top of rails 90 is similar to a double girder crane with end trucks. Parallel guide beams 96 are attached to trucks 92. Wheel truck 98 moves through parallel rails 97 as shown in Figs. 1, 1A, 6 and 7. The transverse loader 50 includes an elevator assembly 100 as shown in Fig. 7 with a guide rig support 101 and a movable elevator 102 up and down as shown by arrow F in an apparatus. support 101 using suitable electromechanical means, preferably counterweight. The transverse loader 50 removes rockets 18, or empty cars 20 or variants thereof, or cars 20 attached to various types of rockets 18 or miscellaneous components, from storage supports 7, to compartment assembly 10, from which transport devices Sides 46 transports rockets 18 moved within cars 20 or car variants to other launchers 119.
[00146] Referring further to Fig. 7, an embodiment of the details of the upper portion of the transverse loader 50 in slightly modified form is shown. As noted above, transverse loader 50 has lift assembly 100, with guide support apparatus 101, on which lift 102 is deposited. Support apparatus 101 is shown having opposite extensions 103 which allow connection of apparatus 101 to a truck. wheels 98 for moving the elevator assembly 100, through rails 97 at the top of the beams 96. In order to couple a rocket 18 for elevation, the elevator assembly 100 has depending legs 105 of which a minimum of three is preferred for stability, which are connected to a body 106 affixed to the lower end of elevator 102 which allows a grip assembly 104 to be lowered into housing assembly 10, as indicated by arrow G. Legs 105 are movable radially on guides 110 (as shown by the arrows in Fig. 7A H.) with respect to a rocket 18 located between legs 105, so as to accommodate different diameters of rockets. A fractional rotation twist locking pin 111, or other means of attachment to the rocket 18, is located at the free end of each leg 105, and the upper portion of the rocket 18 has equally spaced fractional rotation twist locking pin sockets 109 or other containers for other attachment means, to receive respective torsion locking pins 111 to allow secure attachment of the rocket 18 to the elevator assembly 100. Pins, 109 are disposed in a portion of the nose 19 of the rocket 18, are generally parallel to the longitudinal axis of the rocket 18. The pin sockets 109 may have access to the cover 113 connected to the nose 19 of the rocket 18, but being removable from the respective socket 109, as needed to provide access to the socket 109, while providing a smooth surface. for rocket 18 when pin socket 109 is not in use to reduce aerodynamic drag when rocket is in flight.
[00147] Upper and lower stabilizer arm assemblies 114 may be provided to stabilize the rocket 18 during side travel secured in the elevator assembly 100 while traveling along rails 90 and rails 97. Stabilization arm assemblies 114 have each hydraulic or other actuator 115 to which an arm 116 of each arm assembly 114 is connected. Arms 116 are rotatable along paths indicated by arrows I. A lug 117 is provided on the free end of each arm 116 to appropriately engage a recess configured 118 on the rocket 18 to receive each of the cams 117.
[00148] As discussed earlier, Fig. 6 shows a side transport device 46 loaded with a car 20 holding a rocket 18 moving on a path 15 towards the launcher 119 discussed below. Another side transport device 46 carrying an empty car 20 is traveling away from the launcher 119, which has delivered a rocket 18 from the car 20 at high altitude, moving on track 15 returning to an unoccupied compartment assembly 10 to be recharged with rocket 18 or returning to storage bracket 7 for maintenance if necessary.
[00149] Referring again to Fig. 5, rocket launch system 1 still includes a launcher 119. A local launch control shelter 120 directs the operation of rocket launch system 1, directing flows of electrical energy to and from adjacent launch systems 1 from energy sources such as power plant 468 or other adjacent rocket launch systems 1, and armature computer surveillance and control systems using measurement data and various monitoring devices. image, placed along launch system 1. This is where personnel are usually located to control the local rocket launch system 1 and coordinate the launch from other members of the launch systems group to minimize the use of energy.
[00150] The lift assembly 60 is arranged below the ground as shown in Figs. 2, 8 and 9. The lifting assembly 60 may have a lifting mechanism, such as a hydraulic piston rod 68 on which the upper swivel assembly 61 (Fig. 9) rests for rotation, by means of a rotary drive 134 , a car 20 with rocket 18 inside, loaded onto the side transport device 46 in the direction indicated by arrow J. The lifting system 60, described in greater detail below with reference to Fig. 8, includes rod 68 having a width, lower bed not. rotary 135 attached to rod 68, mounted to support the upper swivel assembly 61. The upper swivel assembly 61 is composed of a swivel bed 136 (with a table portion 141) mounted on top of the non-rotating lower bed 135 (which is not part of the rotating platform mechanism 63).
[00151] Reference is now made to Figs. 8 and 9. The piston rod 68 is part of a piston 67 which extends from a hydraulic cylinder 69. The hydraulic cylinder 69, 67 and the piston rod 68 do not rotate.
[00152] The above hydraulic system is not the only way to operate the lifting mechanism. An electromechanical system could form the lifting mechanism.
[00153] Turning now to Fig. 10, turntable mechanism 63 is a portion of land above the rocket launcher 119 for receiving rocket-laden cars 20 from the lift assembly 60 and directing them to be transported is shown. The upward movement of the rocket loaded carts 20 is shown by arrow L. As indicated above, the turntable mechanism 63 includes a turntable base 122 and a cannon assembly 123. The turntable base 122 is connected to ground .
[00154] The turntable 72 can be quite heavy, weighing several tons, and must be supported by a structure capable of supporting such a heavy load, to withstand the lifting and lateral forces, and turn smoothly. A detail of a suitable turntable support device is shown in Fig. 8A.
[00155] Fig. 8A shows turntable base 122 having a horizontal surface 270 by being engaged by wheels 284, a tubular vertical part 272, and a horizontal annular flange 274 extending outwardly towards the outer circumference of the platform base turntable 122. The turntable 72 has a tubular portion 276 which extends down the perimeter of the turntable 72, from which one extends inwardly extending the horizontal annular flange 278 having a number of wheel axle supports 280, 281 and 282 extending to engage base wheel 270, strongly tubular portion 272 and horizontal annular flange 274, respectively. Each support axle 280, 281 and 282, respectively, holds wheel axles 284, 286 and 288, respectively. Wheels 284, 286 and 288 travel on wheel surfaces engaging base 270, vertically engaging tubular portion 272 and horizontal annular flange 274 to allow smooth circular rotation of turntable 72 shown in Fig. 8 by arrow K. Alternatively, referring to Fig. 8B, the base of the turntable 122 could have a horizontal bearing base 290, a vertically tubular part 291 and a horizontal annular flange 292. Likewise, the turntable 72 could alternatively have a tubular part 293 extending downward and extending inwardly a horizontal annular flange 294. A set of bearing balls or rollers 295 is located between horizontal annular flange 294 and each base bearing 290 and the annular, horizontal flange 292, and suitable annular grooves Bearing 296 would be used to allow rotation of the turntable 72 with reduced friction than if bearings were not provided.
[00156] The turntable 72, based on the size of the 20 car could be around 46 feet in diameter. For example, if the tubular interior of car 20 to contain the rocket 18 had a radius of 8 feet, and the minimum thickness of the car 20 holding the rocket is 2 feet, with a clearance of the centrally located car 20 being 3 feet, by the diameter of the turntable 72 would be about 46 feet. This is shown in the following drawing:

[00157]
[00158] If R = 8'
[00159] Δ = 2'
[00160] δ= 3'
[00161] a = R + Δ = 8'+ 2' = 10'
[00162] in Δ AOB
[00163] OB = 2nd = 20'
[00164] AB=a(√3)=10√3=17.32'
[00165] Transport side ≈ 2AB = 34.64'
[00166] OC = OB + BC = 20' + 3' = 23' a. Turntable diameter is at least ≈ 2 (OC) = 46'.
[00167] For a modest diameter of the tubular interior of the car 20 to contain the 16-foot rocket 18, the interior diameter of the car, plus a modest clearance ( pés = 2 feet) for the car frame 20, and allowance of 3 feet (δ = 3 feet) for the mechanism to allow turntable 72 to rotate, the diameter of turntable 72 is about 46 feet and a flat side 22 of carriage 20 is about 34.6 feet.
[00168] Cannon assembly 123 is located at ground level, above bed 136 (Fig. 8), and is supported and retained by turntable base 122. The vertical axis of rotation of cannon assembly 123 coincides with the axle of the lift assembly 60. The lower guide tube 124 has a hole 71 for receiving the rocket-laden carriage 20 from the side transport device 46 through a hole 73, as shown in Fig. 10 extending through. of the turntable 72 and the turntable base 122 by means of the lift assembly 60. The turntable 136 (Figs. 8, 9) has tapered alignment pins 142 and fractional twist lock pins 144 to releasably lock the side transport device 46 with respective carriages 20 to the bed 136. The carriage 20 is releasably locked in a similar manner to the side transport device 46 using alignment pins 142 and split-twist locking pins 144. Thus, releasably locked, carriage 20 can be moved as explained below.
[00169] Still referring to Figs. 8 and 10, cannon assembly 123 further includes a turntable 72 which is rotatable relative to the turntable base 122 in the direction indicated by arrow K observed above, a bolt 126 having a pair of parallel, spaced apart arms 127. arms 127, which are pivotable above the turntable 72. Between said arms 127 is arranged the lower guide tube 124 (also part of the cylinder assembly 123). A pair of coaxial horizontal pivot pins 128 extend through each of the arms 127 and on opposite walls of the lower guide tube 124, and are disposed through a pair of support members 129. Inner carriage guides 133 extend along the cylindrical inner walls of lower guide tube 124 and are separated from each other by 120° to enter a set of corner recesses 130 (Fig. 9) which extends in a longitudinal direction along the corner edges of the carriages 20 The corner recesses contain drive units 26. The lower guide tube 124 and the secondary guide frame 125 pivot in the rotary path shown by arrow M in Fig. 8, by means of a suitable rotation drive system, about the same horizontal axis defined by pins 128. Each of arms 127 includes a counterweight 131 discussed below. The center point of the lower guide tube 124 is disposed vertically above the turntable 72 of the gun assembly 123 so that the axes of rotation of each of the turntable and the lower guide tube 124 intersect orthogonally. The vertical axis of rotation of the rotary platform 72 being coincident with the axis of the lifting assembly 60 and any lateral transport device 46 and carriage 20 located therein.
[00170] Secondary guide frame 125 has an integral tube 143 which is maintained at a fixed distance from the common axis itself and the lower guide tube 124. Thus, the secondary guide frame 125 is counterbalanced around its horizontal axis and has 138 inner carriage guides inside integral tube. The lower end of tube 143 integral with secondary guide frame 125 is capable of coming into alignment with the upper end of lower guide tube 124 so that the tubes are coaxial, and inner carriage guides 133 and 138 are also aligned . Lower guide tube 124 is rotatable about coaxial pivot pins 128, and rotates until its outer surfaces surround a stop 132 (Fig. 10) that extends from an integral tube 330, so that the carriage guides 133 and 138 are in alignment. Carriage guides 133 and 138 are powered in the same way as are the power cables 27 (as discussed below), so the traction unit 26 in a carriage 20 can utilize the power. The upper end of the secondary guide frame tube 125 has transitional internal attachment points for primary cables 27 to allow the carriage 20 to move from the inner carriage guides 138 to the primary cables 27.
[00171] As shown in Fig. 2, side transport devices 46, each loaded with a car 20 retaining a rocket 18 moving along path 15 the set of compartments 10. The car 20 with rocket 18 is removed from path 15, transferred to a launcher 119, and after the rocket has been launched, the empty car 20 is returned to the empty side transport device 46 before proceeding along path 15, returning to the set of compartments 10 or storage support 7.
[00172] Returning to Figs. 8 to 10, lifting assembly 60 increases or decreases carriage 20 with lateral transport device 46 attached to rotating bed 136, by increasing piston 67 and rod 68 in the direction indicated by arrow N (showing the ascending and descending directions) for moving carriage 20 on lower guide tube 124, and cleared from turntable 72. Rotating bed 136 has structure described below for releasable attachment of side transport device 46 to accurately align traction unit 26 of carriage 20 with suitable internal transport guides 133 of the lower guide tube 124.
The lifting assembly 60, the side transport device 46 and the carriage 20 are shown in greater detail in Figs. 8 and 9. The hydraulic piston 67 has at its upper end an upper swivel assembly 61 composed of a non-rotating lower bed 135, a rotating upper bed 136 and part of the platform 141. The lateral transport device 46 can travel to a centralized location on the lift assembly 60. As mentioned earlier, the rails 17 are likely to be necessarily wider than conventional rails. Tapered top alignment pins 142 (four are shown) (shown in detail in Fig. 9A) extend from table portion 141 as do split twist locking pins 144 (four are shown) (shown in detail in Fig. 9B). These interconnect with side transport device 46, as explained below. Of course, the location of the respective pins 142 and 144, and the respective sockets could be reversed between the lateral transport devices 46 and the portion 141.
[00174] The upper swivel assembly 61 of the lift assembly 60 is mounted on the rod 68 and can be lifted as shown by arrow N to allow coupling of tapered lower alignment pins 142 and split twist rotation pins 144 shown in Fig. 9 for a mating alignment pin socket 152 and a torsion pin socket 154 on the side transport device 46.
[00175] The upper surface of the side transport device 46 has upwardly extending tapered alignment pins and fractional rotation pins that are virtually the same as lower taper alignment pins 142 and fractional rotation locking pins 144 that extend to from the top of the table portion 141. A mating alignment pin socket 155 and a twist lock socket 153 are provided on the underside of the carriage 20 to receive the tapered alignment pins and the split rotation pins at the top of the device. 46 to releasably attach carriage 20 to side transport device 46.
[00176] The side transport device 46 has four wheels 58 positioned and contoured to ride on electric rails or rails 17 and including rails 17 adjacent to the table portion 141, and are independently aligned as mentioned above. The side transport device 46 can be powered from electric rails 17 similarly to electric trains or electric cars (which would have to be connected to an electric power source) or from some other power source board such as fuel cells or internal combustion engines.
[00177] The lower guide tube 124 has inner carriage guides 133 (Figs. 8, 10) that extend into each of the corner recesses 130 extending along the vertical intersections of sides 22, also shown in enlarged form, ( Fig. 10) of the carriage 20 to engage the drive units 26 of each carriage 20 to move each carriage 20 along carriage guides 133, and to maintain the orientation of carriages 20 in the lower guide tube 124. carriage 26 are provided for securing the primary power cables 27. Carriage traction units 26 are longitudinal mechanisms with cross-sections partially enveloping primary cables 27 in which the carriage 20 travels, and from which the power is derived. Traction units 26 may include motor-generator and gearboxes having pairs of opposing cylindrical wheels 26A, each having an annular groove 137 for receiving a cable 27, as shown in Fig. 25. Wheels 26A rotate in opposite directions, as shown by the arrows O1 and O2. Drive units 26 are positioned along the length of a carriage 20. Appropriate grooves or surface roughness or suitable surface modifications could be provided over the drive unit grooves 26 to increase the friction of the drive unit wheel pairs 26A. , which in effect tightens the respective cables 27. The electric motors could rotate the respective pairs of traction unit wheels 26A. Motors could be connected to gearboxes, and the output shaft could rotate more than a pair of 26A drive wheels. It could also be individual motors operatively connected to the individual pairs of drive wheels 26A. Many of these depend on the load to be transported and the size of the car 20.
[00178] Traction units 26 drive carriage 20 along cables 27 or guides 133 and 138 (Fig. 10). Traction units 26 generate energy, which is returned to the cables when each carriage 20 is pushed in a reverse direction by gravitational force. The generation of this energy provokes a reaction to the gravitational force and delays the movement of the empty car 20 that moves downwards, as it occurs some time after the launch of the rocket 18. Each traction unit 26 can have a minimum of an opposite pair of 26A wheels, as shown in Fig. 25. Drive motors should be a constant or variable torque motor of a frequency drive type to compensate for cable stretch or wheel slip, to make each group of wheels contribute equally and keep the carriage coaxial with the centroid cables 27 or inner carriage guides 133 of the lower guide tube 124 or inner transport guides 138 of the integral tube 330 of the secondary guide structure 125 when driving the carriage 20 to up.
[00179] As noted earlier, the rocket launcher 119 according to the invention has a lift assembly 60 for raising or lowering a car 20 vertically into or out of engagement with the lower guide tube 124 mounted on the turntable 72 of the turntable mechanism 63. The side transport device 46 is movable with respect to the table portion 141 so that the split twist rotation locking pins 144 can be received in the twist pin sockets 154 at the bottom of the side transport device 46. The lifting assembly 60 lifts the table 141 a short distance off the rail bed 17 to enclose the bottom of the side transport device 46. The table 141 is then locked to the bottom of the rail bed. side transport 46 before its wheels 58 and the entire table portion 141 are raised above the rails 17 after the table portion 141 can be rotated with the transport device la side 46 and the carriage 20 mounted thereon by means of the rotating unit 134 to align the carriage drive unit 26 with inner carriage guides 133 on the lower guide tube 124, which rotates freely, or, if necessary, with auxiliary power , with cannon set 123 to maintain alignment with changing winds. This ensures the necessary stable alignment of carriage 20 with rockets 18 held therein, on lower guide tube 124.
[00180] Referring to Figs. 1, 10 and 11, the rocket launch system 1 includes a primary cable assembly 27 which are separated from each other by spacer or stabilizer assemblies 158. Spacer assemblies 158 are shown in detail in Fig. 10A, and include three side pieces 159 which form a triangle, and arms or flanges 161 orthogonal to the plane of said triangle to engage the respective cables 27. The flange pieces 161 or 159, or both sides, are made of electrically non-conductive material. The cables 27 are capable of transmitting electrical energy, are light weight, as explained below, and have a high tensile strength. The preferred construction and manner of employment of a spacer assembly 158 is shown in Fig. 10A. Extending from each of the cables 27 are adaptive connectors 501 (each similar to an adaptive connector 247 discussed below). Adaptive connectors 501 are provided along each primary cable 27 at spaced intervals, connectors 501 being in alignment along the respective cables 27. Each adaptive connector 501 has a pair of parallel spaced flanges 503 aligned generally radially (but not exactly radially, as they circulate the wire extending from the respective cables 27) adjacent to the respective cables 27. The flanges 503 each have a pair of columns 505, 506 of holes, each column of holes 505, 506 in each pair of 503 flanges be in alignment. The column of holes 506 being closest to the respective cables 27 being connected to the cables 27, as explained later with respect to an adaptive connector 247. A set of protrusions (not shown) extend through the respective aligned holes 505 and also the alignment holes in the orthogonal respective flanges 161 to secure each corner of the respective spacer assemblies 158 to the respective primary cables 27. Each arm 159 of the respective spacer assembly 158 has an enlarged portion 520, preferably, of the tubular construction for rigidity and resistance to deformation, which extends between adjacent primary cables 27, which have shoulders or tapered surfaces 522 to help limit the movement of cables 27 with respect to each other, and to create a lateral clearance between spacer assembly 158 and each cable 27 The arms 159 have smaller end portions 524 for connecting to each other and to the respective orthogonal arms 161. the same spacers 158 can have various configurations; spacer assemblies 158 are shown having square cross sections, but circular cross sections are also advantageous. Spacer assemblies 158 can each be one piece, being folded into their triangular shapes and slid onto three primary cables 27, or arms 159 can be welded together, before or after installation on cables 27. Arms 159 are preferably welded together. to spacer assemblies 158, although bolted connections are possible.
[00181] At the top of the rocket launch system 1 is the set of lighter-than-air tensioning balloons 160 (Figs. 1, 1B, 12 to 14), and there are other lighter-than-air tensioning balloons 164 (Figs. 1, 1B, 11, 15, 17, 18, 21) positioned along the cables 27 to compensate for the own weight of the cables 27 and a little contributing to their tension. Balloons 160 are connected to a balloon tensioning fixture structure or large upper harness 162 (shown in Figs. 12-14) for the purpose of supporting the weight portion of the primary cables 27 and all components above the other tensioning balloons 164, docking station 166 (Fig. 13 discussed below), including the operating weight of a car 20 with a ready-to-fly rocket 18. Balloons 160 and 164 must accommodate any fluctuations in elevator and reaction forces due to motion. of car 20 and its contents, and other components. There are variations in the tension elevation of balloons 160 and 164 due to daily thermal and atmospheric pressure variations. An additional amount of elevator is needed to cause the primary cables 27 to be stretched for a significant part of their payload, since the cables 27 must be kept as vertical as possible. As noted, one or more additional sets of lighter-than-air balloons 164 or 164A (Figs. 1, 11, 15, 16, 17, 20A, 20B), which may be smaller than the lighter-than-air balloons. the air 160, must be interspersed along the cables 27 to alleviate the very weight of the cables 27 and the weight of the support structure and the spacer assembly 158 of the primary cables 27, together with daily thermal variations of the elevator with a safety margin for prevent breakage of the cable under its own weight, the net effect, and the cables 27 with cables associated with approximate balloons without weight or negative weight. The primary cables 27 are surrounded by and power a winch or hoist 168 discussed below, and form an overhead cable path 170 shown in Figs. 11 and 13. The suspended cable path 170 is formed of and delimited by primary cables 27, which the carriage 20 engages and from which the power is derived, so that it can move along cables 27. The fastening structure The balloon tensioning device 162 consists of an upper ring 145 and a lower ring 146 (Figs. 13-14), which are rotation counters, on a rotating bearing 149. The upper ring 145 and lower ring 146 are driven by an oriented rotation drive system 177, and are described below.
[00182] The docking station 166 is shown in Figs. 13 and 14. The docking station 166 has an upper ring portion 172 which can be rotated relative to a lower ring portion 174, the portions 172 and 174 being engaged with a bearing ring 176, are driven by a system of oriented rotation drive 147 (see also Fig. 28 for a corresponding rotation drive system 379), which includes and is assisted by reaction force thrusters 178. Geared rotation drive systems 177 and 147 are also used to supply the opposite rotation of the upper ring 145 relative to the lower ring 146 of the balloon tensioning fixture structure 162, and also of an upper ring portion 172 and a lower ring portion 174 of the aforementioned docking station 166. The rotation drive systems 177 and 147 of the tensioning balloon clamping structure 162 and coupling station 166, respectively, are coordinated so that all components between and including upper ring portion 172 and lower ring portion 146 rotate together as a unit, with the associated cables kept from twisting around each other. Force thrusters 178 and 148 wind counters of induced rotation or resulting rotation of a carriage 20, when the lower end of the carriage 20 is held within the upper ring piece 172 of the docking station 166, and the carriage 20 being rotated in an ideal direction for launch. Docking station 166 has two sets of three inner carriage guides 180A, 180B (Figs. 13, 14) for inserting radial recesses 130 of each carriage 20 to keep respective carriages 20 in proper and stable alignment while supplying power supply to the 26 car traction unit.
[00183] Still referring to Figs. 13 and 14, the lift ring assembly 182 is shown. The lifting ring assembly 182 includes a short tubular ring 183 with a triangular or possibly circular cross section, and is guided by and is electrically connected to secondary cables 184 upwardly extending from the upper ring portion 172 of the station. coupling 166 to connect to lower ring 146 of balloon tensioning fixture structure 162. Tertiary cables 186 (Figs. 13, 14) extending upward from lift ring assembly 182 to lower hoist structure 198 Riser ring assembly 182 is guided by and derives electrical power from secondary cables 184 that are connected to docking station 166. Riser ring assembly 182 is supported by tertiary cables 186 that are connected to a carrier. lower hoist 200, which is the lower hoist structure 198. Referring to Fig. 14A, a carriage end claw 196 is provided with a set of four holes 195, through. which the secondary cables 184 pass freely, and a pair of holes 197 through which the tertiary cables 186 pass freely. Electrical power for a carriage end clamp 196 can be supplied by secondary cables 184.
[00184] The tubular lifting ring 183 has a set of guide elements extending into the inner frame or inner carriage guides 188 which are engaged in respective three recesses 130 extending longitudinally into carriage 20 to maintain carriage orientation 20 on the tubular lifting ring 183 and power supply carriage 20. The lifting ring assembly 182 comprises a tubular lifting ring 183, a carriage swivel assembly 189 which in turn includes a pair of opposing pivot pins 190 and a slewing drive system 194, lift ring guides 192 and reversible drive units 193. The rotation drive system 194 rotates the tubular lifting ring 183 which is pivotable about the horizontal axis defined by the pins 190. The center of gravity of the tubular lifting ring 183 is made to fall at its geometric center which is coincident with the pin axis 190. Tubular lifting ring 183 has a clamping or locking mechanism to allow it to be releasably connected to carriage 20 such that a center of gravity 36 of carriage 20 is maintained on pin axis 190. The axis of rotation of the variable reversible tilt impeller 31 is made parallel to the horizontal axis defined by the pins 190. The tertiary cables 186 are respectively connected to the respective guides of the lifting rings 192. The tertiary cables 186 are provided in two groups of cables of fixed length, and are connected to lower hoist conveyor 200 180° apart to connect conveyor 200 to lift ring guides 192 below and auxiliary n the carriage end claw movement orientation 196 (discussed below), and conveys electrical energy if necessary.
[00185] The lifting ring assembly 182 includes the rotary drive system 194 to change the lifting angle indicated by the arrow P (Fig. 13) of the tubular lifting ring 183 and carriage 20 thus secured with respect to the cables 184 and 186. Carriage end claw 196 is also shown in Figs. 12, 13, and 14. Car end grip 196 can be supported by a lower lift cable 201 connected to the lower hoist assembly 198 mounted on the lower lift conveyor 200. Lower lift cable 201 moves in the directions indicated by arrow Q in Fig. 14. Car end grapple 196 is guided in motion through secondary cables 184 that carry electrical energy, and supported by tertiary cables 186. Car end grapple 196 is able to releasably lock to the top of a carriage 20 by means of locking pins 204 which cooperate with the receptacle locking pin 32 on the top of the carriage 20. When the carriage end claw 196 is securely connected to the carriage 20, the carriage end claw 196 is able to lift or assist in lifting carriage 20 from docking station 166 and even through lifting ring assembly 182 until the center of gravity 36 of carriage 20 coincides with the horizontal axis of the bearing shaft of ring assembly 182 defined by pins 190 when lifting ring assembly 182 is below, in contact with upper ring portion 172 of docking station 166. The length of cables 186, which guides the grip movement end clamp 196 must be long enough to allow carriage 20 to rotate about the horizontal axis when end claw 196 separates from carriage 20 and is raised a short distance out of engagement with coupling assembly 166.
[00186] Lower lift 198 is attached to the lower end of lower lift conveyor 200 as noted above, and also as noted above is used to lift or assist drive unit 26 of carriage 20 in moving carriage 20 in and to out of engagement with the tubular lifting ring 183. Lower lift conveyor 200 is raised and lowered as indicated by arrow R on lift cables 202 from upper lift 168 connected to balloon tensioning fixture structure 162 shown in Figs. 12, 13, and 14. Power is supplied to hoist 168 through secondary cables 184. Either three-phase current or forward current can be used to power elevator 168. In the three-phase current system, as shown, the group of four secondary cables 184, further identified (Fig. 14), from left to right as cable 184A is phase one of three, cable 184B is phase two of three, cable 184C is phase three of three, and 184D, which can be used as an electrical neutral or as a three-phase one-phase doubler. Also as noted earlier, lighter-than-air balloons 160 support the upper components of rocket launch system 1 and provide a significant portion of the tension needed to keep the primary cables 27 and secondary cables 184 in tension so as to make stretched even with operating loads. As shown in Figs. 12, 13 and 14 of the balloon tensioning fixture structure 162 is disposed under the lower lighter-than-air or tensioning balloons 160.
[00187] Referring to Figs. 1, 1B, 11, 15, 16, 17, 20A and 20B, these figures show a series of groups of smaller, lighter-than-air 164 or 164A balloons used to lighten the own weight of the cables 27 and associated support structures and assembly. of spacers are shown. Balloons 164 are tapered and balloons 164A are cylindrical, although other shapes and configurations would be possible and fall within the scope of the invention. Each of a number of large seat belts 206 having tensioning balloon support 208 are connected to primary cables 27, via a lower three-sided spacer or stabilizer assembly 210. Each lower spacer assembly 210 is constructed and connected to primary cables 27 in the same way as spacers 158 were constructed and used as described above. Balloons 164 or 164A are respectively connected to balloon supports or attachment points 208 (Fig. 18). Lower spacer assembly 210 has three arms 211 forming an equilateral triangle, as seen in plan, arms 211 being parallel to respective arms 222 of large harness 206. Lower spacer assembly 210 has connecting structure 214 at respective intersections of arms 211 , from which conductor 215 extends. Each conductor 215 of the lower spacer assembly 210 extends by attachment to the respective balloon supports 208 of the large harness 206. There are also provided a number of upper spacer or stabilizer assemblies 216, which, as spacer assemblies 210, separate the primary cables 27 and still maintain ties in place of cables 218 and 219. Upper spacer assemblies are constructed and used as are spacer assemblies 158 and lower spacer assemblies210. Each upper stabilizer 216 has three arms 217 which together form, in a plan view, an equilateral triangle, the arms 217 parallel to the respective arms 222. A connecting cable 220 is at the intersection of the respective arms 217. Pairs of stabilizing lanyards 218 are connected at one end to the connector cable 220 at opposite ends of the arms 217 and ties the supports 221 at the midpoint of the arms 222 parallel to the respective arms 217. Another set of conductor cable 219 is connected between the tether connectors 220 and the balloon supports 208. This arrangement assists in keeping the seat belt 206 stably in place. Seat belts 206 are periodically installed with balloons 164 and 164A, respectively, along the length of the primary cables 27 to compensate for the own weight of the cables 27 and all attached structures, and to induce tension in the cables to help maintain it. them upright.
[00188] A specific assembly A for connecting the various components of the upper spacer 216 is as follows. Upper spacer assembly 216 and the items connected thereto are shown in Figs. 15A, 15B and 15C. As noted above, the upper spacer 216 is composed of three arms 217 that form an equilateral triangle. With reference to Figs. 15B and 15C, the connecting cable 220 comprises a base plate 902 having a central arm 904 and two arms 906 and 908 separated from the central arm 904 by an angle greater than 90°. Connector cable 220 further has a support portion 910 which is generally opposite arm 904. Base plate 902 is advantageously flat, and extending perpendicularly thereto is a cable connecting flange 912 which extends along the middle of the support portion 910. A pair of arm support flanges 914 and 916 also extend perpendicularly from baseplate 902 and are equally angularly spaced from cable connection flange 912. Arms 904, 906 and 908 have holes for support receiving 920, 918 and 922, respectively, extending radially through the respective arms 904, 906 and 908. The cable connection flange 912 has a series of equally spaced, support receiving holes 924 that extend along of the height of the flange 912.
[00189] Each cable 27 has at least one, and more likely than many, connecting structures 925, each connecting structure 925 being composed of pairs of spaced, opposite, parallel flanges receiving connecting flanges 926 , 927 which are parallel to the respective axes of cables 27. Flange 926 has parallel alignment columns of support receiving holes 928 and 930 which are aligned with corresponding holes 928, 930 on the other flange 927. securing each cable connector 220 to a position over a respective cable 27, the flange connecting cable 912 is inserted between the flange receiving connecting flange 926, 927 with the holes 924 in alignment with each of the respective holes 928. A set of protrusions 932 is inserted into the respective aligned holes 928 and 924 and connected to a nut or other locking receiver 933. For their additional connection, cable connectors 220 to respective cables 27, sa similar lugs 256 as shown in Fig. 22 are used to secure the lugs 244 of the cable 27. The flange receiving connection flanges 926, 927 are close enough together to allow the drive units 26 to engage the respective cables 27 as the carriage 20 with traction unit 26 passes the flanges 926 and 927 in the complete operational engagement with the respective cables 27.
[00190] As noted earlier, the pairs of stabilizing lanyards 218 connect cable connector 220 to the respective midpoints of a pair of arms 222 of large seat belt 206. Each stabilizing lanyard 218 has at one end a connecting yoke 934 with a pair of parallel flanges 936 with in-line holes 938, through which extends a shoulder 940 which also passes through hole 908 for subsequent receipt by a nut or other fastener receiver 942 to connect the stabilizing lanyard 218 to the cable connector 220. Similarly, cable tie 219 has a coupling yoke 944 with a pair of parallel flanges 946 with a pair of aligned holes 948. Arm 904 is inserted between flanges 946, and a tongue 950 is inserted in the holes 948 and 920, and on a nut or other fastening receiver 952.
[00191] Fig. 15E shows a detail of the connection of the lower spacer assembly 210 (Fig. 15) to cables 27 and to the large harness 206 by means of the frame connection 214. The pair of connection frames 925 is fixed to the cable 27 by lanyard engagement 244. Connecting structure 925 is comprised of a vertical flange 960 having a connecting flange extending therefrom 962 and including a column of support holes 963. A flange arm support assembly 966 extends to from vertical flange 960 to which they are welded by a suitable welding process, and are respectively connected to the respective arms 217 of the lower spacer assembly by a weld or any other suitable process. Arm support flanges 966 are angled together and angled in that they engage with respective arms 217 to provide structurally strong support. The connection flange 962 is placed between the parallel flanges of the connection frame 925 with the holes being aligned with the holes 928 (see Fig. 15B) and terminals 932 and inserted through the respective aligned flange connection holes 962 and holes 928 and through nuts or other fastening receiver 933 (see Fig. 15A) to fasten connection structure to cable 27.
[00192] The vertical flange 960 has a finger portion 968 that extends through a hole 970. The end of each conductor 215 for attaching the lower spacer assembly 210 to the large harness 206 has a coupling yoke 972 composed of parallel flanges 974, 976 through which aligned bearing receiving holes 978 extend. The yoke 972 is moved so that part of the finger 968 is inserted between flanges 974 and 976 with holes 970 and 978 being aligned. A support 980 is inserted through holes 970 and 978, and into a nut or other fastening receiving means 982.
[00193] It was mentioned earlier that the stabilizing slings 218 were connected to the midpoint of the arms 222. The apparatus for doing this is shown in Fig. 15D. A lanyard connection flange 984 is connected and extends from the midpoint of each of the arms 222. The flange 984 has two short arms 986, each having a support receiving hole 988. Each lanyard 218 has a breech. 944 connection with 946 flanges as discussed above. Forks 944 of each hawser 218 are slid over an appropriate arm 986 of flange 984, and a shoulder is inserted through holes 948 and 988 and tightened in place with a fastener, such as with a nut.
[00194] Structure to couple each of the seat belts, spacers and stabilizers is preferably composed of the same type of components and subcomponents. This kind of structure is strong, stable, easy to manufacture and put into use.
[00195] Numerous three-sided upper spacers or stabilizer assemblies 260, virtually identical to the spacer assemblies 210, are located above the large seat belt 206 (as shown in Fig. 18). The detailed construction of the spacer assemblies 260, and how they are connected to the primary cables 27 is practically the same in the form of the spacer assembly 158 and the lower spacer assembly 210. Spacer assembly 260, as shown in Fig. 18, is connected to the cables 27, by means of connecting structures 262 at the intersection of the pairs of arms 264 connected to the three arms forming an equilateral triangle. A set of lightweight cables 266 (compared to the relatively heavy weight cables 27) extend from the connecting structure 262 to balloon holders 208, which are constructed to hold them to the large belt 206. The lightweight cables 266 support the large belt 206 when assembling the launch system or during maintenance of the balloons 164.
[00196] A set of three electric reaction thrusters 800 are respectively connected to the pivot bearing joints 802 at the intersection of the respective arms 222, as shown in Figs. 18 and 19. Each thruster 800 comprises a fan 804 which is mounted to each vent frame 806. Each frame 806 is pivotally mounted between a pair of arms 808. Each arm 808 has coaxial center pins 809 extending to the frame 806 , allowing each frame 806 to pivot about an SS axis in the direction of arrows T in both clockwise and counterclockwise directions. Arms 808 branch from a central arm 810, which is connected to the pivot bearing joints 802 as discussed above. 800 thrusters are suspended by all electric thrusters. Drives 800 are pivotable and rotatable, and are operated to hold launch system 1 oriented with respect to vertical as required. 800 thrusters compensate for wind forces and stop partial or full deflation of any balloons 164 until they can be replaced or not maintained. The position of large belts 206 with respect to the launch system base 1 is controlled by position sensors 812, which may be a global positioning system (GPS) for providing position reference data to the computers that control the direction. and 800 thruster strength.
[00197] The following is an explanation of the matter in which balloons 164 (which would be applicable to balloons 164A) are connected to primary cables 27 is shown with respect to Figs. 15, 16, 17, 18, 20A and 20B. Spacer assembly 260, together with the lightweight cables 266 shown in Fig. 18, located above the upper stabilizer 216 has been omitted for clarity in Fig. 15. Looking at Fig. 15 first, a portion of primary cables 27 is shown , with lower stabilizer 210 and upper stabilizer 216 being provided to stabilize the upper belt 206. Three balloons 164 (only one of which is shown in solid lines in Fig. 15) are provided to compensate for the very weight of the cable 27, different stabilizers, and any excess loads applied to cables 27. Depending on their diameter, balloons 164 may require tubular spacers made of the same material as the balloons and inflated with the same gas - lighter than air. In order to maintain the cables 27 from touching the balloons 164 (or balloons 164A), straps or stabilizing straps 227 (15A Fig.) are provided for attaching the balloons 164 to the cable separators, such as the upper spacer assembly 260 (Fig. 18) to avoid such contact. Each stabilizer strap 227 is part of a stabilizer 228 that is connected to each of the cables 27 in the same way that other stabilizers are connected to the cables 27. The stabilizers 228 further have a connecting element 229 to secure the respective stabilizer straps 227 in place . The manner in which the above is done can be seen in more detail in Fig. 16, which is a top view taken in the direction 16-16 in Fig. 15. It can be seen that each stabilizer 228 is connected to the primary cables 27 within the three intersections of outrigger 228. Outrigger 228 is composed of three respective arms 234, which collectively intersect to form an equilateral triangle. From each connecting member 229, a pair of stabilizing straps 227 forms an angle so that the respective pairs contact the respective balloons 164, which are nearly tangential. Straps 227 are each connected to a balloon 164 by a tangential strap connection 224. Strap connections 224 prevent cables 27 from contacting balloons 164 (balloons or 164A). Strap connections 224 (Fig. 15) may advantageously be a suitable adhesive, plastic welding or seam with a suitably strong thread to connect the stabilizing straps 227 to the respective balloons 164 (or balloons 164A).
[00198] Fig. 17 shows three balloons 164 connected to their large strap 206 balloon holders 208. Upper stabilizer assembly 216 is shown having their stabilizer cable lanyards 218 connected to tie support 221 over arms 222. Vectors values FF are shown in Fig. 17 extending along the tension cable 219, showing the tension forces extending from the cable connectors 220 to the balloon supports 208.
[00199] A side view of the fastening system is shown in Figs. 20A and 20B. Each balloon 164 (Fig. 20A) and 164A (Fig. 20B) has lightweight, strong, basal tension connectors 232 connected to a large belt 206 balloon holder 208. One or more of the connectors 232 may be tubular to transport gas from replacement lighter than air in each balloon 164 to compensate for leakage. Balloons 164 and balloons 164A are lighter than air, so the pulling forces FF are as shown by the arrows along connectors 232. Connectors 232 are tangent to the lining of each balloon 164 and 164A. A set of three or more connectors or stabilizers 228 (Fig. 16) are shown to connect the respective balloons together at various points.
[00200] As explained above, the balloon tensioning fixture structure 162 has a rotating upper part 145 and a rotating lower part 146 (Figs. 13, 14), which are connected through bearing ring 149 on the vertical axis to reduce friction from the rotational movement as depicted in Fig. 12. Force reaction thrusters 148 are tangentially attached to the periphery of an upper rotating part 145. Likewise, force reaction thrusters 178 are connected to the periphery of the part bottom 174 of the docking station 166. The propulsion units mounted on the top rotating 145 and those mounted on the part 174 are used to keep them non-rotating. The over-the-top drive units 145, in conjunction with the oriented rotation drive system 177, assist in the rotation of the swivel lower portion 146 relative to the swivel top 145. Likewise, the swivel-up drive units 177 174, together with the oriented rotation drive system 147 (Figs. 13, 14), help the rotation of the rotating upper part 172. The secondary cables 184 collected in two groups are connected in front of each other (distant by 180°) at the lower rotary part 146. Upper elevator 168 is connected to lower rotary part 146. Cables 184 connect balloon clamping structure 162 to docking station 166 (Figs. 13, 14) and carry electrical power as required. Cables 184 also guide the movement of lower lift conveyor 200, carriage end grapple 196 and lift ring assembly 182. Cables 184 are long enough to safely allow for a down acceleration period at local acceleration due to gravity of the lower lift conveyor 200 and items suspended thereon, long enough for a rocket 18 to be disconnected from its containment while in free-fall conditions and fully propelled from the car 20. An additional length of cables 184 to allow an additional period of time is also required for deceleration for the rest of the lower lift conveyor 200 and all items (including loaded or empty conveyor 20) suspended thereon. An additional length of cable would allow the deceleration of a fully charged 20 car to rest in the event of a misfire in short boost duration.
[00201] As explained above and further discussed below, a means is required to secure system 1 items for the various cables. Fig. 21 shows a cable 240 made from strands of wire 242. Each filament 242 of the cable 240 may have portions or loops tied off 244 that extend from the outer surface of the cable body 27 to secure the items to the cable 27, leaving most of the outer surface of the cable unobstructed. Each loop 244 extends outward from each cable body 27 and returns to cable body 27. For example, adaptive connector 247 is shown in Fig. 22, as discussed in detail later. Adaptive connector 247 has a flange 248 having a series of bolt holes 249 and further a series of bolt holes 250 that extend through a pair of parallel walls 252 that extend in parallel from a common base 253. adaptive connector 247 can be made against cable 27, with loops 244 sliding between parallel walls 252 and their respective loop holes 254 in alignment with holes 250. A screw 256 can be extended through loop holes 254 and 250 to secure the adaptive connector 247 to cable 27 and a nut can be placed on the respective screws 256 to make a secure connection. A top view is shown in Fig. 23. Alternatively, the parallel walls 255 separated by a spacer 259 as an alternative adaptive connector 257 can be used, as shown in the top view of Fig. 24. Cable 27 can be used gripped by a pair of drive units 26A of cars 20 as shown in Fig. 25, rotating in opposite directions O1 and O2.
[00202] In order to use the rocket launch system 1 described so far, the rockets 18 are loaded into cars 20, respectively, in one of the apparatus as shown in Fig. 5, and transported along path 15 with a device side transport device 46. The side transport device 46 is secured to the lift assembly 60 using respective tapered alignment pins 142 and split rotation twist lock pins 144 and their respective cooperating alignment pin socket 152 and pin socket of fractional rotation torsion lock 154, as explained with respect to Fig. 9. Secondary cables 184 and primary cables 27 are held taut by tensioning balloons 160 and balloons 164, respectively, with balloons 164 that contribute to tension in the primary cables 27. Tension to the lower cables is transferred through balloon tensioning fixture 162 and cable separation and added tension. al are reached through the large belt 206, spacers 158 and spacers 228 (Figs. 11, 15 and 18).
[00203] Each carriage 20 is rotated in alignment with the inner carriage guides 133 and loaded into the lower guide tube 124 (Fig. 8). The upper portion of the lower guide tube 124 is then angled into engagement with the lower portion of the secondary guide frame 125 (Fig. 10) until the lower guide tube 124 engages the stop 132 to align the carriage guides 133 and 138, as discussed earlier. The traction unit 26 is then used to drive the car 20 to the cable 27 via the docking station 166 on its upper part 172 and partially on the lifting ring assembly 182, which is reduced by the use of lifting systems 168 , such that elevator ring assembly 182 engages with top 172 of docking station 166 (Figs. 13, 14). The claw end 196 is lowered and properly secured to the upper end of the carriage 20. The lower lifter 198, fed by current in the secondary cables 184 transferred from the cables 27, lifts the carriage 20 still into engagement with the lifting ring assembly 182 , such that the centers of gravity of the combined lift ring assembly 182, the car 20 and the rocket 18 coincide with the pivot axis of the lift ring assembly 182. The lower elevator 198 thus assists the drive unit. pull 26, which engages inner carriage guides 180A and 180B on lifting carriage 20 upward relative to docking station 166. Then carriage end claw 196 disengages locking pins 204 from pin lock socket 32 of carriage 20 and is minimally fully lifted by the use of lower elevator 198. Lifting ring assembly 182 is guided by secondary cables 184 and supported by tertiary cables 186. Elevator 168 lifts the carriage 20 further until the lower end of the carriage 20 is no longer within the lower part 174 of the docking station 166 and is only within the upper part 172. The meshed rotation drive system 147 within the lower docking station 166 and the rotary drive system 177 in mesh with the balloon tension structure 162 now rotate all components in a coordinated fashion between ring bearings 176 and 149 in a direction suitable for launching rockets 18. Thrusters 148 and 178 function simultaneously to maintain the lower part 174 of the docking station 166 and, the upper ring 145 of the rotating balloon tensioning fastening structure 162 (Fig. 14).
[00204] The next lift 168 lifts car 20 fully out of engagement with docking station 166 (car 20 holding rocket 18 must be lifted higher and higher, according to its combined weight) and as high as necessary for the middle of the short tubular ring 183 for the safe launch of the rocket 18. The rotary drive system 194, in coordination with reversible variable lift thrusters 31 extended to 90°, rotates the short tubular ring 183 with the car 20 at a suitable angle with respect to the horizontal for proper launch. Reversible variable lift thrusters 31 are being used to assist rotary drive system 194 and to prevent carriage 20 from swinging around the horizontal axis via pins 190. When carriage 20 is at the desired lift angle for launch and stable, reversible variable lift thrusters 31 are even rotated on their hinges to avoid contact with the hot rocket gases.
[00205] Variations are possible to aid rotary drive system 194. This includes positioning and stabilizing carriage 20 on lift ring assembly 182, and in particular to prevent carriage 20 from swinging over pivot pins 190. With reference to Figs. 13B - 13C, a reversible variable tilt thruster 31 and a pair of follow-up hub motors 822 can be provided at both ends of the car 20. Each thruster 31 and hub motor 822 can be housed at one end of the car 20 under a end liner 830. Each impeller 31 has a set of rotating blades 826 which are mounted to a pivotable impeller assembly 828 at both ends of carriage 20. Each assembly 828 is mounted on a hinge assembly 829 and is movable between a rest position (shown in dashed lines in Fig. 13C) and an active position parallel with the longitudinal axis of carriage 20 (shown in Fig. 13C in solid lines) by means of a hydraulic actuator 832, which rotates around an actuator pivot 834. When thrusters 31 are in their active position, an air current is created as shown by the U arrows. This prevents the carriage 20 from swinging. Hub 822 motors are reversible as the air current can go in both directions. ections. Likewise, the inclination of the blades 826 is variable to vary with the variance of the ambient air, where the blades 826 are rotating. However, when the rocket engine 18 ignites, the thrusters 31 can be moved at an obtuse angle, as shown in the dotted lines on the left of Fig. 13C to avoid short-term booster escape. The upper end of the impeller 31 is also moved to its obtuse position, to allow the loading of a rocket 18 into the carriage 20. It should be noted that the interior of the carriage 20 has a continuous heat and pressure resistant tube 836 running from the tip. the tip to contain the 18 rocket in it. A set of three or more centering bracket 840 maintains the centering of each variable reversible tilt thruster 31 .
[00206] The upper end of the lift cable 202 (Fig. 14) is fed from the upper lift 168 and reversible drive units 193 of the lift ring assembly 182 starting to drive downward, while in operative engagement with cables secondaries 184. The lift cable 202 e moves unfolded from the lift ring assembly 182, the car 20, the rocket 18 and all other components supported by the cable 202 downwardly assisted by units 193 to overcome friction and drag. from the air, so they are in free fall at an acceleration of lg, and the rocket 18 becomes imponderable with respect to the car 20. There is a slight friction maintained in the upper elevator 168 to maintain control during the free fall, and to prevent any slack and any uncontrolled unwinding of cable 202. Prior to free fall, retractable end liners 30 (Figs. 9, 9C, 13, 13A) of carriage 20 are opened (or end liner 830 shown in Fig. 13C are open) . Retractable arms 34 or 35 (Fig. 26) inside car 20, which had been attached to the rocket 18 in car 20 are retracted (as discussed below), and to the rocket 18's short-lived amplifying rocket motor is ignited to drive rocket 18 out of car 20. The short-lived amplifier rocket engine only operates within a pressure and heat resistant confinement of car 20 to avoid damage to system launch 1.
[00207] After rocket 18 has traveled far enough in its ballistic path, its main engines can be safely ignited, as needed, to prevent damage to the launch system. The outfeed of the cables 202 from the upper lift 168 (Fig. 12) is gradually stopped while the reversible drive units 193 from the lift ring assembly 182 (Fig. 13) are operated in a braking mode to prevent falling additional carriage clearance 20, lower lift carriage 200, carriage clamp end 196 and lift ring assembly 182 (Figs. 12, 13, 14). Reversible variable tilt thrusters 31 (Fig. 13C) can then be used to help rotate carriage 20 to a vertical position, before being retracted into the ends of carriage 20 and can be used to purge exhaust gases from the interior. of said car before closing the time cover 30.
[00208] Short tubular ring 183, of the lifting ring assembly 182 with empty carriage 20, having been rotated to the vertical position (in preparation for rotation about the vertical axis, since the rotational moment of inertia is the highest lowered when the carriage 20 is relative to the vertical position), is then lowered by means of the upper lift 168 in engagement with the upper part 172 of the docking station 166, shown in Figs. 13 and 14. Carriage 20 and carriage end claw 196 can then be brought together to lock carriage 20 to carriage end claw 196 before carriage 20 is lowered into engagement with top 172 if additional support or guidance is needed. The lower end of carriage 20 is then lowered into engagement with upper portion 172 of docking station 166. Lower portion 146 (Fig. 14) of balloon tensioning fixture structure 162 and upper portion 172 of docking station 166 are rotated closely so that the inner carriage guides 188 of the lifting ring assembly 182 (Fig. 13, 14) and the inner carriage guides 180 of the upper portion 172 come into alignment with the cables 27 of the docking station 166 (Fig. 13). Elevator 168 then lowers carriage end clamp 196 onto top of lift ring assembly 182 (Figs. 12, 13, 14) and releases carriage 20. Lift ring assembly 182 also disengages the car 20.
[00209] Carriage 20 quickly drives down the suspended cable path 170 (Fig. 11) formed by primary cables 27 using regenerative braking to keep the low speed of carriage 20 at a manageable level. Power back to the primary cables 27 at this and other launch stations is transferred to another launch system to supplement or replace the energy needed to lift another car 20 to its overhead cable path 170. A minimum group of four systems Active launch pads are planned with a fifth acting as a spare point used for light tasks such as tourism or high altitude skydiving using special light cars until an active launcher requires maintenance or a higher rate of liquid rocket launcher is required. A combined launch rate of once an hour is believed to be possible.
[00210] After the empty carriage 20 re-enters the secondary guide frame 125 (Figs. 1A, 2, 8, 10 and 11), and is further lowered until the carriage 20 disengages the secondary guide frame 125 and becomes centered on the lower guide tube 124 at the point where the combined centers of gravity of carriage 20 and lower guide tube 124 coincide with the axis of rotation of lower guide tube 124. Lower guide tube 124 is returned to the vertical position and the carriage 20 is reduced to suitably an aligned side transport device 46 on top of the lift assembly 60. The side transport device 46 returns the empty carriage 20 to the explosion resistant compartment assembly 10 for reloading or storage support. 7 for replacement and renewal. Another pre-assembled rocket 18, car 20 and side transport device 46 can be loaded into system 1, and next to rocket 18 launched as described above.
[00211] One possible construction of a retractable arm is retractable arm 34 in the direction of arrow V to hold the rocket 18 in a car 20 as shown in Fig. 26. The rocket 18 has at least six equally spaced adjustable slots 300 for receiving the retractable arms 34, having one arm 34 from each slot 300.
[00212] Referring next to Fig. 27, different alternative retractable arms 35 can be provided. Each retractable arm 35 has a head member 302 for insertion of one of the notches 300, and a base member 304 that extend from opposing coaxial pivot pins 306. A rod 308 interconnects a head member 302 and base member 304, and strengthens the networks or keys 310 extending between the base member 304 and the rod 308. The carriage 20 has inside, an explosion resistant tube 312 having a cavity 314. Tube 312 has a pair of protective doors 316 mounted on hinges 318, which can be positioned to close cavity portion 314 (as indicated by arrows W) or pivot outwardly to open cavity portion 314, as shown in Fig. 27. Tube 312 also has an end port covering cavity 320. Port 320 may have an air flow deflector 322 to protect ports 316, 320 and cavity 314, a strain member from column reinforcement 324 and a pin holder 326, securing coaxial pivot pins 328 to the entry of pivot sockets 331 on proximate sides of sidewalls 332 defining cavity portion 314. Door 320 pivots pins 328 between positions open and closed. Walls 332 also have pivot sockets 334 to receive pins 306 of retractable arm 35.
The cavity cover port 320 further has a hydraulically retractable pin 336 for entering and exiting a socket 338 located in an arm 340 of the port 320, and a hole 339 in the base member 304. The port 320 also has legs. Parallels 342 with aligned holes 344. Rod 308 of retractable arm 35 has a strong portion 346 with a slot 348 that extends longitudinally in rod 308. Portion 346 extends between legs 342, and a slide pin 350 extends through slot 348 and at each hole 344 to pair of retractable arms 308 to cover door of cavity 320. A hydraulic arm 352 has legs 354 with in-line holes 360 to go between a pair of legs 362 in an end floor 364 of cavity 314 , legs 362 having aligned holes 366, and legs 354 are held in place by a pin 356 extending through holes 360 and 366. Another pair of parallel legs 368 extend from an axis 369 generally extending forward ap from arm 352, and a pair of aligned holes 370 receiving a pin 371. Doors 316 are opened and closed by hydraulic or electromechanical means, coordinated with door 320.
[00214] The foregoing arrangement locks the ports 316 and 320 which are shown in Fig. 27 in their open position, and the head members 302 of each retractable arm 35 remain in respective slots 300 in the rocket 18. When the rocket 18 is in free fall with carriage 20 and becomes weightless relative to carriage 20, arms 35 are quickly retracted into their respective cavities 314, along with the rest of the mounting operation with holes 35, and doors 316 and 320 are closed just before firing the rocket 18's rocket motor amplifier. Each rocket 18 may have small wheel sets 372 to keep the rocket 18 centered in the tube 312 during launch in case the pressure line is not exactly coaxial. with the inner tube of the car 20 or not passing through the rocket's center of mass.
[00215] Another version of the invention, in addition to launching rockets, can be used if a telescope is to be raised to the top of the unit. With reference to Figs. 28 and 28A, a telescope attached to system 373 is shown. Fig. 28A shows balloon 160 in reduced form. The telescope-related components are discussed below. System 1 has three primary cables 27 that carry electrical energy, and are connected to a 374 docking station. Base station 374 has an upper portion 376 that is rotatable in the direction of arrow X relative to a lower portion 378 using rotation drive system 379. Referring to Figs. 28B and 28C, the rotary drive system 147 rotates the upper 376 and the lower 378 with respect to each other by means of a bearing ring 850 having a reshaped inverted member 852 in cross section, with ball bearing assemblies 854 and 856 on tracks 857, 858 and 859, 860 on top 376 and an L-shaped member 852, and bottom 378 and L-shaped member 852, respectively.
[00216] The upper ends of the cables 27 are quickly attached as shown. A cable 27A extends at an angle through an opening 862 in the bottom 378 and a suitable clamping mechanism 864 to quickly attach to the cable 27A. A second cable 27 is shown as cable 27B, and is quickly secured by a suitable means by a flange 866, as shown in Fig. 28C. A third cable 27 is similarly quickly attached. A motor 868 rotates a gear 870. Gear 870 is sequentially connected to teeth 872 of top 376 to effect the preceding rotation as shown by arrow Y. A housing could include motor 868 and gear 870.
[00217] Three or more reaction thrusters 380 can be used, and they compensate for the relative rotation of parts 390 and 378, which are held stationary when the alternative launch system depicted in Fig. 28 is used to launch the rocket. Similar to other docking stations, a bearing ring 377 and the rotary drive system 147 are included between the top and bottom parts 376, 378 of the docking station 374. The secondary cables 184 also carry electrical energy for the operation of the electrical components . It could be a two-wire direct current device or a four-wire, three-phase device.
[00218] A lift ring 382 directs up or down in the direction indicated by the Z arrows on cables 184. The lift ring 382 includes reversible drive units 386, and frame 387 for securing carriage 20, which is capable of securing rotate in the direction indicated by arrow AA and a rotating unit 381 to change the angle of the lifting ring 382 and carriage 20. An upper docking station 388 has an upper part 390 normally held stationary and a lower part 392, being rotatable in directions shown by arrows BB, around a vertical axis, using rotating unit 381. A bearing ring 394 reduces friction from such rotation. A minimum set of three force reaction thrusters 397 counts the tendency of the tops 390 to rotate around the vertical axis.
[00219] A 396 rigid elevator shaft or lift tube can carry 398 special carriages each with a DC telescope built inside, for top mounting 399. A special light carriage or 20A carriages could also be used for transporting the carriage 20 onto riser tube 396 for mounting 399 after transfer from riser ring 382. A set of electricity attached to cables or rails can be mounted inside riser tube 396, which the wheels of trolleys 398 or 20A could engage and also receive electrical power (as well as the sprocket wheels 26 that carry the cables 27), to allow transport of the carriage 20A up and down inside the lift tube 396. Balloon(s) 160 is connected to or around the riser tube 396 as described above to provide sufficient tension for the leads 184 to allow transport of the riser ring 382 with the special carriage 398 securing the telescope DC to it, as well as to support the cables themselves and the devices connected to the cables.
[00220] The top part telescope mount 399 includes a cannon-like platform 402 on which the rotating turntable 404 is disposed which rotates relative to the stationary top part 390. An extending telescope receiving hole 405 through platform 402 and turntable 404 as shown in Figs. 28A and 29. Mounting walls 406 extend from turntable 404. A telescope holding frame or ring 408 grips the special carriage 398 with DC telescope thereon, with the center of gravity of the carriage 398 disposed at the center of the ring 408 , which acts in the same way as the lift ring assembly 182, but without the drive units. As shown in detail in Fig. 29, ring 408 has coaxial pivot pins 410 which extend into sockets 412 of mounting walls 406. Mounting walls 406, ring 408 and pivot pins 410 for a tilting structure telescopic 411 are provided. Therefore, the car 398 and the CC telescope mounted thereon can be tilted in elevation as desired and the rotation in azimuth shown by the DD arrow of the 404 turntable directly on the car 398 and CC telescope included in any desired direction. Turntable 404 and platform 402 can be made independently rotating in the respective opposite directions shown by arrows HH and II (Figs. 28A, 29) with respect to lift tube 396. This rotation is effected by means of a rotary drive 383, similar to unit 381. Platform 402 may have radially adjustable weights to make its rotational moment of inertia equal to the rotational moment of inertia of turntable assembly 404 and parts above it, so that when they are rotated in opposite directions , no torque net is applied to lift tube 396 as turntable 404 and above parts are rotated.
[00221] The rocket launch system 1 can be used for a variety of purposes. For example, it could be used to launch a single man or basic rocket 601 that has a steerable engine 603 as shown in Fig. 30, which is mobile as indicated by arrows EE to steer the rocket 601. A person or occupant GG is shown using a liquid-filled launch or 605 re-entry suit with 607 joints locked in an optimal vertical aerodynamic position for launch and locked feet first to the top of the 601 rocket to resist the G-force effects of rocket 18 firing during launch . The 605 suit sets the rocket 601 as desired after the rocket 601 stops working and the suit joints are unlocked, allowing the GG occupant to move freely. If the garment is to be used for re-entry, a portion of the liquid surrounding occupant GG can be pumped through porous pads to evaporate-cool the exterior of the garment 605 on re-entry, foot first. (The same pumping operation and cooling effect would apply at launch as well.) The 601 rocket with GG occupants in 605 suit mounted on top should allow GG occupant an excellent view during the launch phase. An aerodynamic fairing around suit 605 cannot be required, unless so configured, and the set of hinges 607 are locked in position, aerodynamic drag is even greater than necessary for optimal launch.
[00222] Fig. 31 shows a possible method for transporting tourists in clothing 605 or materials in rigid capsules 608 detachably attached to a core of rocket 604. Main rocket 601 leaves its launch controlled for a period after its launch. The 604 rocket core is released from the 601 main rocket after the launch of the 601 controlled main rocket has ceased. A 609 windshield can be used to protect tourists in 605 suits or 608 capsules from high-speed air, as per the 601 rocket. penetrates the atmosphere on its way to space, where the 605 suits or 608 capsules can be released in the direction indicated by JJ arrows. The 604 rocket core may have a set of 602 rotating fins, which are transformed into KK directions by the directional control system to guide the 601 rocket.
[00223] Fig. 32 shows an alternative capsule 610 with a sled-like re-entry structure 616. Occupant GG wears the launch or re-entry suit 605. The sled-like re-entry structure 616 includes steering fins 619, and an aeroclip 611. The aeroclip 611 has an extendable type antenna configuration with a disk portion 613 as a shock wave front initiator to produce a shock wave 615 to reduce aerodynamic heating of the clothes 605.
[00224] In Fig. 33, the re-entry suit 605 with person GG is shown fitted within a formed rocket-like structure 617 with directional guide fins 618 aero-clamp 611. Structure 617 has disk 613, as discussed in with respect to Fig. 32. An orientation equipment and storage compartment may be located in the interior structure towards the stern 617.
[00225] A suitable spacesuit 605 is shown in GG persons in Figs. 34 and 35, also serving to accommodate the effects of the G-force. The 605 spacesuit allows the GG occupant to survive, remain conscious and able to remain active while in an upright posture in a high-acceleration environment. For extended operations, this is achieved by immersing the occupant in a fluid of approximately the same density as the body, inside a rigid suit with constant volume joints, servo-assisted, electromechanical or hydraulic, external. Spacesuit 605 has a helmet 650 (in figures 34, 34A, 34B, 36) around person GG's head, and a rigid outer shield 648. An underwear 651 sits near person GG, and an inner face mask 653 with sight 655 seals underwear 651. A non-toxic fluid 656 (Figs. 34, 34A-34C, 36) such as water fills the space between rigid outer shell 648 and underwear 651. If the liquid 656 is heated to a comfortable temperature, the underwear 651 can be omitted. There is a double seal 654 between the underwear 651 and the face mask 653. The underwear 651 could be a tight lining around the person GG, and the face mask 653 could be vented to or from an air supply through an air supply tube 661. An exhaust channel 652 is provided in the full face mask 653 of the spacesuit 605 for draining water if there is leakage into the space between the double seals around the face of the person GG. The water or other suitable non-toxic fluid 656 fills the space between the undergarment 651 and outer shield 648, and the face mask 653 and visor 655 as shown in Figs 34, 34A and 34B. The GG person in spacesuit 605 can rotate their head inside helmet 650 while suspended in water 656. Spacesuit 656 is of lightweight rigid construction, however the volumetric airflow sensors on face mask 653 or visor 655 could be provided to drive a hydraulic or electromechanical piston (explained below) to move in and out to match the volume change due to breathing. Also, in order to equalize the respiration rate, that is, the change in volume divided by the change in time, the pressure sensors in various places (particularly near the chest) in the spacesuit 605 keep the liquid pressure constant, guiding the piston in and out. The use of high pressure hydraulic electric assistance allows the GG person to move freely in the 605 suit in high acceleration environments, such as during launch or re-entry, avoiding the possibility of water or other hydraulic fluid used to activate the suit's joints to escape into the undergarment, which could crush occupant GG.
[00226] With respect to the piston, reference is also made to Fig. 35. Here, the spacesuit 605 has water (or non-toxic fluid of a human body density approximation) 656 filling the garment around the person. GG, and a piston 657 moves in and out of a cylinder 660, fed by high pressure hydraulic fluid or direct actuation of piston 657 by the electromechanical apparatus to vary the volume in garment 605 as needed for normal breathing.
[00227] The rigid outer shell 648 is typical of the garment construction 605 illustrated in Fig. 34 and is shown in Fig. 36. The rigid outer shell 648 of the garment 605 includes a pair of rigid sleeves, each containing inner sleeves 664 ( only one is shown) each of which is made from stretchy, open fabric or a soft, open-pore foam or fabric and a pair of rigid legs each having inner legs of the same construction as inner sleeves 664. The sleeves inner and inner legs hereinafter referred to as "inner sleeves." The pores should be large enough so as not to significantly impede the flow of water through sleeve 664. Sleeve 664 is held centered within garment 605 by weakly elastic tendons 668 connected at an end that matches 605, which extend through sleeve 664 and are connected to, and tangent to, sleeve 664, to which they are connected, at the other end. Tensions in the 668 elastic tendons are detected and used to provide feedback to direct the energized joints of the 605 suit to mirror GG occupant movements, keeping it centered within the suit. A GG occupant just slips on suit 605 and slips his entire body into the typical 664 sleeve. The 605 suit is a practical and efficient space suit to be worn by a GG person on a 601 rocket or inside the 18 rocket, particularly during phases launch, thrust and flight re-entry. The outer shell 648 could have an ablative outer material with heat resistant insulation or thermal insulation.
[00228] Other versions of a rocket are shown in Figs. 37, 38, 38A, and 39. A rocket 700 has an aerospace plane 702 with an implant, and a folded elevation and directional control structure 704 attached to the body shown in Figs. 37, 38 and 38A, and foldable in the directions indicated by arrows LL and MM. A lift body type reentry vehicle 706 is shown in its folded launch configuration in Fig. 38 lift and directional control structures 704 in folded condition. The lift body type Reentry Vehicle 706 with directional control structures and lift 704 foldable in the direction indicated by arrows NN is shown in Fig. 38A in the folded and unfolded configurations. The 700 rocket is basically a military version of the 18 rocket.
[00229] Referring to Fig. 39, a more typical rocket 720 is shown. Rocket 720 includes a satellite or other payload 722, which is protected during launch and flight by a pair of disposable aerodynamic shields 724. After rocket 720 has left the atmosphere, shields 724 are automatically disconnected in the directions indicated by the arrows PP and preferably fall back to earth and the satellite or other payload 722 goes into space. The 720 rocket is essentially a commercial version of the 18 rocket.
[00230] The preferred embodiment described above can be achieved using presently available materials and products. The typical car, loaded with a rocket, can be estimated to weigh 80 tons, although higher weights are possible. Each cable must be strong and electrically conductive. In addition, it must be wear resistant to support the travel of drive wheels up and down the ropes. Thus, cables 27 and 184 may have a steel exterior, with the middle portion of aluminum and a steel core. Cables can be multi-stranded with copper and steel filaments and copper clad wires in steel or other suitable construction. For a 70-ton elevator, the ropes should be about 2/3 inches in diameter. Each of the three cables could be 1.25 inches in diameter, and the secondary cables must each have a diameter of one inch.
[00231] As noted earlier, the weight of the cables is advantageously compensated periodically. Steel cables with a diameter of 1.125 inches weigh about 2.03 pounds per foot. A safety factor of at least five must be used. A one-inch-diameter cable is 120 tons at its breaking point.
[00232] The preferred gas for balloons should be hydrogen, which is much more buoyant than helium and can be generated from water, while limited supplies of helium are primarily extracted from natural gas wells. However, security is an important factor. The higher in the atmosphere the balloons are, the risk of lightning increases. Therefore, the turntable, lift assembly and above all components must be isolated from the ground, electrically charged to the same electrical potential as the high altitude atmosphere to avoid attracting lightning, and the inductively connected electrical power supply . The insulating parts of the rocket launching system could advantageously be made of ceramic or glass.
[00233] The lining for the balloons should be light, strong and resistant to ultraviolet (UV) light. There has been extensive work done on liners coming from the design and operation of other airships and balloons recently.
[00234] The advantages of the rocket launch system of the present invention over those currently in use are quite apparent. The first stage of the NASA-launched Saturn V rockets consumed 203,000 US gallons of RP-1 (refined kerosene) and 331,000 US gallons of liquid oxygen (LOX) in a 2.5-minute period. The present invention could have greatly reduced the amount of thrusters to launch for the same payload by lifting numerous smaller rockets using electrically powered carriages with an equivalent charge to the balloon cables supported at a desired height before launch. The current state of the art uses an enormous amount of non-recoverable fossil fuel energy. For example, Virgin Galactic White Knight Mothership uses tons of JET-A-1 fuel kerosene to reach its launch altitude Space Ship Two which uses a rubber form with a liquid oxidizer, and produces a discharge of black soot. Solid rocket propellants often leave partially burned fluorine and chlorine compounds and hydrocarbons, among other hazardous wastes in their exhaust. All these leaks and waste pollute the environment. On the other hand, the energy used in lifting the cars in the preferred form of the present invention is derived from renewable sources and a significant portion is recovered when the traction unit transfers to its regenerative mode when the car returns under the cable. suspended.
[00235] Furthermore, the present invention will reduce the cost of spaceflight enough to allow the removal of debris in orbit around the planet and even allow the construction of an orbital shipyard. A vivid example of the dangers of space junk in space was the collision of the non-operational Russian Cosmos 2251 communications satellite with a US based mobile phone satellite owned by Iridium on February 11, 2008. Each satellite was traveling at an orbital speed of 17,500 kilometers per hour. The debris from this collision was estimated at 500 pieces. NASA has reported that this collision debris has increased the risk of damage to the International Space Station. The International Association for the Advancement of Space Security has proposed mandatory withdrawal of non-operational satellites.
[00236] The present invention thus includes a set of lighter-than-air balloon support cables, which can be used for a variety of purposes in a very effective and efficient manner. When used to launch rockets, the amount of fuel required at launch is drastically reduced as the rockets are transported to the upper atmosphere before their engines are operated. Rockets can be used for a variety of purposes, and due to reduced energy consumption and resulting cost savings, such uses as recreational sport use of rockets, skydiving, small jet engines or other devices can be economically viable. Likewise, the installations for the maintenance satellites become more viable and economical. Uses for high-altitude platforms such as telescopes could be of enormous benefit to scientists.
[00237] In the preferred embodiment discussed above, three cables have been provided for three-phase electrical power. It is likely that each cable should transmit exactly one third of the electricity. In case this cannot be done or in case there is a possibility that it can be carried out during the use of the rocket launching system, according to the invention, the structure must be provided either to have a neutral line or a ground to obtain the necessary electrical balance between each of the three cables.
[00238] The present invention has many uses in addition to those described above. There is a huge amount of debris orbiting the Earth from the many rockets directed into space. NASA estimates that in 2009, there are about 14,000 objects being tracked by the US Space Surveillance Network. Many of these objects threaten other devices that may pass through the respective orbits of these objects, as collisions could cause considerable damage. The present invention could be used to place debris catchers into orbit for recovery and economically and safely remove such debris from orbit or to recycle such items as they can be reusable in useful structures in orbit.
[00239] The ropes discussed here have been described as being of the general type of rope composed of twisted metal strands and as shown twisted into a helix. These are cables that are electrically conductive, and are similar to those used in cables for cars, funiculars and aerial lifts. Different variations in cables were discussed as well. However, "cable" is not intended to be restricted to steel cables. The cables could also be rods of different types, which come in individual lengths, joined by various types of soldering, or in a series of smaller connections, which are coupled together to obtain the desired length. The important feature of whichever cable is used in accordance with the invention is that it is strong, electrically conductive and capable of taking on the voltages and voltages that exist at high altitudes to carry rocket transport devices and other apparatus as discussed herein. . These rods or other types of cables can be modified in different aspects, such as, for example, to modify the surface or surface configuration of the rods or other cables, so that the system would work more effectively and more efficiently. when the rods or other cables cooperate with the traction units of the respective rocket transport devices. Such rods could have a cylindrical cross-section or other cross-sections, depending, for example, on the nature of the traction units used with it. With reference to Figs. 40 and 41, a 990 rod is shown with connecting flanges 992 connected to gaskets 994. The flanges have fixing holes 996. As required to attach spacers on other structures to the side of the rods to allow for fastening or other connections that can be connected by bonding, solid state or other forms of welding (eg friction welding, explosive welding, arc welding, etc.) or adjustment as deemed necessary. The rods can be modified in other ways depending on factors such as the nature of the connection of the respective rods, the electrical conductivity of the rods, the safety of the rods and the like.
The invention has been described in detail with particular reference to preferred embodiments thereof. However, variations and modifications within the spirit and scope of the invention may occur to persons skilled in the art from the foregoing material and the appended claims.

权利要求:
Claims (15)
[0001]
1. Rocket launch system (1) characterized by comprising: a set of electrical power lines to transport electrical energy from a remote electrical power system on earth, the electrical energy being continuously withdrawable along said electrical power lines, said set of power lines having a lower end portion to be positioned at a low altitude and a high end portion to extend to high altitudes; a set of rocket transport device lines for transporting a rocket transport device between a low altitude and a high altitude, said rocket transport device lines having a lower end portion to be positioned at a low altitude and a portion of high end to extend to high altitudes; secondary lines operatively connected to said set of electrical power lines and said set of rocket carrier device lines to extend to altitudes higher than the highest altitude of said set of electrical power lines and said set of rocket lines. rocket transport device; operating structures (docking station (166), elevator ring assembly (182), car (20) and gripper 196) operatively connected to said branch lines for making operations for said rocket launch system (1); lighter-than-air support balloons (164) connected to said sets of electrical power lines and said rocket carrier lines to hold said power line assemblies and said rocket carrier lines up to a altitude above the earth; and lighter-than-air tension balloons (160) connected to said secondary lines to supply voltage to said secondary lines when said electrical power lines to said rocket carrier device lines are at high altitude above the earth.
[0002]
A rocket launching system (1) according to claim 1, characterized in that respective power lines of said set of power lines and respective lines of said set of rocket carrier device lines are integrally combined into one set of primary power and transport cables (27), said set of primary power and transport cables (27) being three in number for the transport of three-phase power; and where said rocket launch system (1) further comprises a rocket transport device for transporting a rocket along said primary power and transport cables (27), said rocket transport device including: a car (20) containing an interior compartment with open ends (24) during launch and configured to contain a rocket (18), the rocket (18) being ejectable from said interior compartment (24); and traction thrusters (26, 193, 386) for driving said carriage (20) along said primary power and transport cables (27), said traction thrusters (26, 193, 386) comprising: electrically actuated reversible energizer apparatus to derive electrical energy from said set of electrical power lines when said traction thrusters (26, 193, 386) lift said carriage (20) along said set of primary power and transport cables (27), and said energizer apparatus reversible electrically actuated supplying electric power to said set of electric power lines when said traction thrusters (26, 193, 386) move said carriage (20) reversibly under the influence of gravity to control the descent of said set of primary power cables and transport (27); and a set of traction drive wheels (26A) associated with said carriage (20) for engaging said power and transport cable assembly for transporting said carriage (20) along the primary power and transport cable assembly (27), said set of traction drive wheels (26A) being operatively connected to said electrically driven reversible energizer apparatus, said traction drives (26A) serving as regenerative brakes when the carriage (20) moves along and in a controlled manner lowers said primary cables and transport (27) under the influence of gravity to provide electrical power supply to the array of electrical power lines.
[0003]
3. Rocket launching system (1), according to claim 2, characterized in that the respective operational structures comprise: a docking station (166) operatively connected to said set of primary power and transport cables (27) in a position terminal along the length of said set of primary power and transport cables (27), said docking station (166) being structured to receive said car (20) as part of the preparation for the launch of a rocket (18) being transported on said car (20); and said secondary power lines comprise secondary power and steering cables (184) operatively connected to said docking station (166) and extendable at an altitude greater than the altitude of said docking station (166); and said operating structures further comprise: a lifting ring assembly (182) operatively engaged with said secondary power and steering cables (184) for deriving electrical energy and being guided by said secondary power and steering cables (184), said assembly of lifting ring (182) being positionable above said docking station (166) and being operatively engageable with a carriage (20) placed in said docking station (166) to lift said carriage (20) from the docking station (166 ) and having a carriage rotation assembly (189) to be tilted at the angle of the desired rocket launch; a lower winch assembly (200) located above said lifting ring assembly (182) when said rocket launch system (1) is in operation; a tertiary support cable assembly (186) extending from said lower winch assembly (200) to be operably connectable to and supporting said lifting ring assembly (182); and a rocket carrier device end gripper (196) placed between said lower winch assembly (200) and said lifting ring assembly (182) and being operatively connected to said lower winch assembly (200), said gripper being (196) attachable so that it can be released and locked onto a carriage (20) on said lifting ring assembly (182), said lower winch assembly (200) lifting said end gripper (196) to lift a rocket carrier device and coupling with said car rotation assembly (189) prior to launching a rocket from a car (20) placed on said lifting ring assembly (182); said lighter-than-air tensioning balloons (160) comprise: lighter-than-air primary tensioning balloons (160) operatively connected to said secondary power and steering cables (184) to tension both of said primary power and transport cables ( 27) and power and steering cables (184).
[0004]
A rocket launching system (1), according to claims 2 to 3, characterized in that it further incorporates: a launcher (119) for launching said respective cars (20), said launcher (119) including a platform mechanism ( 63) for receiving respective carriages (20) for release to said docking station (166), said platform mechanism (63) comprising: a platform base (122); and a tower assembly (123) mounted to said platform base (122), the lower end portion of said primary power and transport cable assembly (27) being connected to said tower assembly (123), and the frame transport for transporting respective carriages (20) to and from said tower assembly (123); said tower assembly (123) comprising: a rotating platform (72) rotatable relative to the base of said platform base (122), said rotating platform (72) having a platform hole (73) for receiving respective carriages (20 ); a lower guide tube (124) mounted on said rotating platform (72), said lower guide tube (124) having a lower guide tube hole (71) capable of alignment with and having a size corresponding to said platform hole ( 73), said lower guide tube (124) receiving respective carriages (20), said lower guide tube (124) comprising lower guide tube guide structure (133) for locating respective carriages (20) in said tube hole lower guide (71); a secondary guide frame (125) comprising an integral tube (143) having an integral tube hole (143) and secondary guide frames (125) capable of alignment with said lower guide tube guide frame (124), and frame primary cable connector (132) for connecting said primary power and transport cables (27) to said secondary guide structure (125); and a rotatable assembly (128) for rotating said lower guide tube (124) with respect to said secondary guide structure (125) to align said lower guide tube hole (71) and said integral tube hole (143), and to align said lower guide tube guide structure (124) and said secondary guide structure (125); said rotating platform (72) rotating said lower guide tube (124) and said secondary guide structure (125) in a desired direction for movement of a respective carriage (20).
[0005]
A rocket launching system (1) according to claim 4, further comprising: a lift assembly (60) for lifting a car (20) into said tower assembly (123); where said rotating platform (72) has an orifice for receiving respective carriages, and said lifting assembly (60) comprises: a hydraulic cylinder (69); a hydraulic piston (67) operatively disposed within said hydraulic cylinder (69); a hydraulic piston rod (68) connected to said hydraulic piston (67) and being axially movable with respect to said hydraulic cylinder (69); an upper swivel assembly (61) operatively mounted on said hydraulic piston (67) for receiving respective carriages (20) and aligning a respective carriage (20) with said platform hole (73), where said upper swivel assembly (61) includes a table portion (141) for receiving respective carriages of side transport devices (46) having a set of side transport wheels, and said table portion (141) is associated with rails (17) in line with the wheel set. of side transport devices to allow side transport devices (46) to be received in said table portion (141), where side transport devices (46) and said table portion (141) have fastening structure for securing, of so that they can be released, the lateral transport devices (46) to said table portion (141); a track (15) having a set of rails (17) engageable by the wheel set of the side transport device (46) for transporting the respective carriages to said table portion (141) for transfer to said lifting assembly (60 ). a rocket storage structure (7) for storing cars loaded with rockets to be launched from said rocket launch system (1); a rotary drive (134) for rotating said upper swivel assembly (61).
[0006]
A rocket launch system (1), according to claim 5, characterized in that said path (15) is a closed path and said rocket launch system (1) further includes: a rocket loading system ( 38, 39) to remove respective cars (20) each loaded with a rocket (18) from said rocket storage structure (7); assembly compartment assembly (10) placed in said track (15) closed at ground level or below ground level to receive cars loaded with a rocket, said rocket loading system (38, 39) moving respective cars loaded with a rocket (18) for the respective mounting housing assemblies (10); a transverse loader (50) which moves with respect to said respective assembly compartment assemblies (10), said transverse loader (50) comprising an elevator assembly (100) which moves both transversely and vertically to receive respective carriages (20) at a relatively high elevation and to lower respective carriages into said respective assembly housing assemblies (10); a set of tracks (90) arranged on said closed track (15) on which said loader (50) moves; and a guide assembly (94) for guiding said cross loader (50) and components of said cross loader (50), said guide assembly (94) comprising: trucks with wheels (92) moving on said rail assembly ( 90) and carrying said transverse loader (50) along said set of tracks (90); and tracks (97) extending through said transverse loader (50), said lift assembly (100) being movable along said tracks (97); a wheeled truck assembly (98) for transporting said elevator assembly (100) along said rails (97), said elevator assembly (100) including: a support guide apparatus (101) mounted on said wheeled truck ( 92) and extending in a vertical direction; and an elevator (102) operatively coupled to said support guide apparatus (101), said elevator (102) having electromechanical structures for moving said elevator (102) on said support guide apparatus (101); said elevator assembly (100) lifting rockets and carriages from said rocket storage structure (7) and lowering respective rockets (18) and carriages (20) into respective mounting compartment assemblies (10); transfer by moving respective rockets (18) and carriages (20) between said rocket storage structure (7) and said mounting compartment assemblies (10).
[0007]
7. Rocket launching system (1), according to claim 6, characterized in that said assembly compartment assemblies (10) are located below the level of the ground surface, and have the shape of an inverted conical trunk ( 12) and are made of a concrete material to limit harmful effects due to the detonation of rocket propellant deflecting the explosion.
[0008]
A rocket launching system (1), according to claims 2 to 7, characterized in that said lighter-than-air support balloons (164) are operatively connected to said set of primary power and transport cables (27 ) intermittently along the length of said set of primary power and transport cables (27) to cumulatively support said set of primary power and transport cables (27) and any other operating structures supported by said set of primary power and transport cables (27); and that said rocket launching system (1) further includes: groups of spacer assemblies (158) intermittently located along said assembly of primary power and transport cables (27), each of said group of spacer assemblies ( 158) having cable-engaging structure (161) for engaging respective ones of said set of primary power and transport cables (27) to maintain a spaced separation between said respective primary cables (27), and wherein said support balloons plus lighter than air (164) are respectively operatively connected to at least one of said spacer assemblies (158).
[0009]
A rocket launching system (1), according to claims 3 to 8, characterized in that it additionally includes: a balloon tensioning fixture structure (162) connected to said secondary power and steering cables (184), said lighter-than-air primary tensioning balloons (160) being affixed to said balloon tensioning fixture structure (162) to provide sufficient tension to cumulatively support at least one of said respective carriages (20), secondary power and steering cables (184) and any other operating structures supported on said balloon tensioning fixture structure (162) below said balloon tensioning fixture structure (162); a lower winch assembly (200) operatively connected to said balloon tensioning fixture structure (162) located above said lifting ring assembly (182) when said rocket launch system (1) is in operation, an assembly of tertiary support cables (186) extending from said lower winch assembly (200) to be operably connectable to and supporting said lifting ring assembly (182), and a carriage end claw (196) disposed between said lower winch assembly (200) and said lifting ring assembly (182) and being operatively connected to said lower winch assembly (200), said car end claw (196) being the hitch capable of being released and locked with a respective carriage on said lifting ring assembly (182), said lower winch assembly (200) lifting said carriage end claw (196) to lift said carriage (20) into its engagement with the swivel assembly. car (1 89) prior to launching a rocket (18) from said car (20) disposed on said lifting ring assembly (182); and an upper winch assembly (168) connected to said balloon tensioning fixture structure (162) and being operatively connected to said lower winch assembly (200) and said secondary power and steering cables (184); upper winch (168) using power from said secondary power and steering cables (184) to selectively lift and assist in lifting said respective carriage (20) into and out of engagement with said lifting ring assembly (182) ; wherein said coupling station (166) has connected thereto an upper ring portion (172) having an axis of rotation, a lower ring portion (174) coaxial with said upper ring portion (172), said ring portion upper (172) and said lower ring portion (174) being connected together by a lower bearing ring (176), said upper ring portion (172) and said lower ring portion (174) being capable of rotation therebetween , and a lower rotation drive system (147) for driving said upper ring portion (172) and said lower ring portion (174) in counter rotation about said lower bearing ring (176) and wherein said The tensioning balloon attachment structure (162) has connected thereto an upper ring (145) having an axis of rotation, a lower ring (146) coaxial with said upper ring (145), said upper ring (145) and said ring lower (146) being connected together by an upper rotating bearing ring (149), and a drive system. upper rotation then (177) to drive said upper ring (145) and said lower ring (146) in counter-rotation about said upper rotatable bearing ring (149); said upper rotation drive system (177) and said lower drive system (147) being operatively connected together to coordinate the rotation of said upper ring portion (172) and said lower ring (146) to rotate as a unit for prevent said associated cables from tangling together, said lower ring portion (146) and said upper ring (145) rotating as a unit against wind induced rotation and rotation resulting from rotation of one of said respective carriages (20) when the lower end of said carriage (20) is attached to said upper ring portion (172) and said respective carriage (20) is being rotated for launching.
[0010]
A rocket launching device (1) according to claim 9, characterized in that said cars (20) have a triangular cross section with corner edges with radially accessible longitudinal recesses (130) extending along said edges corner; said lifting ring assembly (182) being supported by said tertiary cables (186), said lifting ring assembly (182) comprising a tubular lifting ring (183) with a triangular cross section for receiving one of said respective carriages ( 20), said tubular lifting ring (183) having inwardly extending inner carriage guides (188) engageable with said radially extending longitudinal recesses of said respective carriages (20) to maintain the orientation of said respective carriages (20) ) in said tubular lifting ring (183), said tubular lifting ring (183) having a longitudinal axis coincident with the longitudinal axis of said carriage (20), the angle of said longitudinal axis with respect to the ground is the elevation angle of said tubular lifting ring (183).
[0011]
A rocket launching system (1) according to claims 8 to 10, characterized in that it further comprises: at least one large safety belt (206) having interconnected arms (222) and tensioning balloon supports (208) for attaching said lighter-than-air tensioning balloons (160), said tensioning balloon supports (208) being attached to said primary power and transport cables (27) to provide said tension; said at least one large safety belt (206) having three arms (211) forming an equilateral triangle, and said groups of spacer assemblies (210) comprise at least one lower spacer assembly (210), said at least one lower spacer assembly ( 210) comprising three-sided lower spacer arms (211) forming an equilateral triangle parallel to the respective arms of the respective large safety belt (206), said at least one lower spacer assembly (210) having a lower spacer assembly-connector structure (214 ) at the junction of the respective lower spacer arms (211); and lower spacer harness conductors (215) connecting said connector structure-spacer assembly (214) with said respective tensioning balloon supports (208).
[0012]
A rocket launching system (1), according to claims 3 to 11, characterized in that said car rotation assembly (189) is in free fall condition after launching a rocket (18), and in that said secondary cables (184) are of sufficient length to safely allow a period of time of sufficient duration in local acceleration due to gravity of said lower winch assembly (200) with a car having a rocket (18) disposed therein for safely decelerate in the event of a failure while said carriage slewing assembly (189) is in a free-fall condition.
[0013]
A rocket launching system (1), according to claims 2 to 12, characterized in that said primary power and transport cable (27) is a cable body (240) composed of wire filaments (242) having outer loop portions (244) extending from said cable body (240) to secure items to said primary cable (27), each outer loop portion (244) exiting and returning to said body (240) of said primary cable (27); and wherein said rocket launching system (1) further includes: an adaptive connector (247) having wall holes aligned therein, and a connector for extending through a pair of said aligned holes (250) and one of said wall holes. external loops (254) for connecting said adaptive connector (247) to said primary power and transport cables (27); and wherein said carriage (20) for transporting a rocket (18) along said primary power and transport cables (27) includes traction wheels for engaging said respective primary power and transport cables (27) to rotate about said respective ones. primary power and transport cables (27) without contacting said portions of outer loops (244) to drive said carriages (20) along said primary power and transport cables (27).
[0014]
A rocket launching system (1), according to claims 3 to 13, characterized in that said docking station (166) is structured to receive a telescope carrier car, and an operatively connected telescope fixing system to the docking station (166), said telescope clamping system including: a rotating turntable (404); a mount (399) constructed to hold a telescope (408); a telescope clamp structure (408) for securing a telescope (408) on said rotating turntable (404); and a telescope tilt structure (411).
[0015]
A rocket launching system (1) according to claim 14, characterized in that said operating structure further includes: a riser tube (396) to provide a transport path for a telescope carrier car (408) for transporting a telescope (408) for said assembly (399), said assembly (399) being constructed to hold said telescope carrier carriage (408) to place the telescope (408) in operational (operational) position(s), wherein said tube lift (396) further includes electricity conveyor cables or wheels for energizing the telescope carriage (20A) in said lift tube (396); and wherein said coupling station (166) has a lower part (378) and an upper part (376) rotatable with respect to said lower part (378), and a rotational drive system (147) for compensating the relative rotation of said bottom (378) and said top (376); and wherein said rocket launch system (1) further includes: a bearing ring (850) located between said lower portion (378) and said upper portion (376) to reduce friction between said lower portion (378) and said upper (376) and wherein said rotational drive system (147) comprises thrusters (800) to provide said compensation; secondary electrical power cables (184) extending upwardly from said docking station (166) when said docking station (166) is lifted under the influence of said lighter-than-air support balloons (164); a lifting ring (382) which is driven up and down on said secondary cables (184), said lifting ring (382) including traction units (386) and carriage clamping structures (387) (20) for securing a telescope carriage carriage, said carriage securing structure (387) being pivotable and rotatable with respect to said secondary cables (184) for orienting a telescope carriage carriage secured to said carriage securing structure (387) for entry into said carriage tube. elevation (396); and an upper docking station (388) connected to said secondary cables (184), said upper docking station (388) comprising an upper part (390), a lower part (392), this latter upper part (390) and this above-mentioned last lower part (392) being rotatable in opposite directions about an imaginary vertical axis, a rotational drive system (381) for rotating this above-mentioned last upper part (390) and this last lower part (392), and an upper coupling station bearing ring (394) to reduce friction between this latter upper part (390) and this latter lower part (392) mentioned above.

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同族专利:

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公开号 | 公开日

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SG183205A1|2012-09-27|

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CN102933932B|2016-03-09|

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EP3196587B1|2019-10-30|

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JP2015145234A|2015-08-13|

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WO2011100053A8|2012-03-15|

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US9739567B2|2017-08-22|

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RU2551047C2|2015-05-20|

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US20170284768A1|2017-10-05|

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WO2011100053A2|2011-08-18|

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KR20130019380A|2013-02-26|

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JP2013528766A|2013-07-11|

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IL221422A|2018-03-29|

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EP3196587A1|2017-07-26|

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KR101805134B1|2017-12-06|

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JP6074821B2|2017-02-08|

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IL257445D0|2018-04-30|

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EP2534438A4|2015-07-01|

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CN102933932A|2013-02-13|

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US10443976B2|2019-10-15|

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AU2011215552B2|2015-07-23|

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WO2011100053A3|2011-11-10|

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AU2011215552A1|2012-09-06|

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BR112012020262A2|2020-09-01|

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CA2789506C|2015-07-21|

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EP2534438A2|2012-12-19|

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KR20130086263A|2013-07-31|

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KR101579567B1|2015-12-22|

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KR101505444B1|2015-03-30|

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US20130007935A1|2013-01-10|

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EP2534438B1|2016-10-05|

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JP2016222241A|2016-12-28|

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JP6458956B2|2019-01-30|

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KR20130085064A|2013-07-26|

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JP5817739B2|2015-11-18|

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CA2789506A1|2011-08-18|

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IL257445A|2021-05-31|

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法律状态:
2020-09-15| B06F| Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]|

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2020-10-20| B06U| Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]|

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2021-02-02| B09A| Decision: intention to grant [chapter 9.1 patent gazette]|

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2021-04-20| B16A| Patent or certificate of addition of invention granted|Free format text: PRAZO DE VALIDADE: 10 (DEZ) ANOS CONTADOS A PARTIR DE 20/04/2021, OBSERVADAS AS CONDICOES LEGAIS. |

优先权:

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申请号 | 申请日 | 专利标题

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US33764510P| true| 2010-02-11|2010-02-11|

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US61/337,645|2010-02-11|

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PCT/US2011/000237|WO2011100053A2|2010-02-11|2011-02-10|Rocket launch system and supporting apparatus|

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