• 专利附录
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    • 专利摘要:
    The invention relates to a method for launching an aerostatic device (20) comprising: - a load, called load (22), - an elevation device (21) comprising: ○ an aerostat, said aerostat (23) main , adapted to support the aerostatic device (20), ○ a hanger (26) connecting the main aerostat (23) to the load (22), - an aerostat, said aerostat (28) auxiliary, adapted to sustain at least one part of the weight of the useful load (22), in which process: - the auxiliary balloon (28) is connected to the useful load (22), keeping the load (22) useful captive with respect to the ground, - then the main aerostat (23) is raised, - then the useful load (22) is released, characterized in that the auxiliary aerostat (28) is irremovably associated with the aerostatic device (20) so as to be captive of the lifting device (21) during flight of the aerostatic device (20).
    公开号:FR3052437A1
    申请号:FR1655489
    申请日:2016-06-14
    公开日:2017-12-15
    发明作者:Jean Evrard；Ghislaine Facon；Thomas Huens
    申请人:Centre National dEtudes Spatiales CNES；
    IPC主号:
    专利说明:

    The invention relates to a method for launching an aerostatic device comprising a load and at least two aerostats for sustaining this load. The invention extends to an aerostatic device for implementing a launching method according to the invention.
    The aerostatic devices comprise at least one aerostat, that is to say a device levitated in an atmosphere through the use of one (or more) gaseous fluid (s) lighter (s) that the atmospheric gas composition - especially the air- by their nature or by their physical conditions (temperature for example). An aerostat comprises in particular at least one balloon formed by a closed or semi-closed inflated envelope (that is to say having at least one lower opening of dimension much smaller than a total surface of this envelope).
    The aerostatic devices can be used to transport charges, called payloads, especially in the context of scientific missions, these payloads making it possible, for example, to carry out measurements in the atmosphere and / or in the stratosphere, in the fields of including meteorology, atmospheric chemistry and astronomy. For example, atmospheric and / or stratospheric aerostats can fly up to 45 kilometers in the Earth's atmosphere by carrying payloads of over one tonne.
    The first phase of flight of an aerostatic device is the launch of taking off the aerostatic device. More particularly, it consists in placing the entire aerostatic device in a vertical position, by raising at least one aerostat of the aerostatic device, so that it sustains the entire aerostatic device. This launching phase is particularly difficult to achieve with some high-performance aerostatic devices, especially with stratospheric aerostatic devices. Indeed, the payload may include expensive scientific equipment, it is important not to risk damaging it during launch. However, when the aerostat rises and suspends the payload, it still in the vicinity of the ground, may be subject to horizontal movements and / or pendulum may cause it to hit the ground. In addition, this risk increases considerably in case of bad weather on the ground. To avoid any risk of contact of the payload with the ground at launch, it is necessary to maintain it several meters above the ground during the vertical deployment of the aerostat, before its release.
    Moreover, the aerostatic devices being able to cross air corridors during their ascent and descent, must comply with safety and security rules, and must not in particular represent any risk of collision with aircraft or environmental risk .
    Several known solutions make it possible to maintain the payload several meters above the ground. A known solution is to use a crane lifting the payload and moving it horizontally to the aerostat during the launch phase. However, such a solution is insufficient in the case of strong winds and / or oriented laterally with respect to the direction of movement of the crane. Indeed, such winds can generate a pendulum movement of the payload and are likely to unbalance the crane. Such a solution can also be difficult to implement when the launch is carried out on a ground with reduced space or difficult of access for the crane, such as an island or a forest.
    Another known solution consists in using an aerostatic device comprising a main aerostat adapted to sustain the entire aerostatic device and an auxiliary aerostat adapted to at least partially sustain only the payload in the launching phase. Thus, the main balloon is used to raise the entire aerostatic device and the payload in the atmosphere and the auxiliary balloon is only used to lift the payload by a sufficient height during the launch phase in order to avoid that the payload hits the ground. More particularly, the payload is maintained close to the ground so that it does not fly before the main balloon is mounted to a sufficient height. The auxiliary aerostat is releasably connected to the payload by a hook connected to a line parallel to a main line connecting the main balloon to the payload. The hook is arranged such that the auxiliary balloon is automatically disconnected from the payload and released from the aerostatic device into the atmosphere when the main balloon is mounted at a height sufficient to sustain the payload after launch. This solution also has many disadvantages. The auxiliary aerostat, free to move into the atmosphere after launch, may fly out of control into the atmosphere. As a result, it can interfere with the flight of aircraft and / or fall back on inhabited areas. Such auxiliary aerostat does not respect the rules of safety and security and requires to be able to identify the movement and organize its recovery after its fallout. Such auxiliary aerostat also presents a risk of interference with the aerostatic device, including the payload, after its release. The invention aims to overcome these disadvantages.
    It is more particularly to provide an aerostatic device whose launch is easy, safe, and perfectly controlled. The invention also aims at providing such an aerostatic device whose different flight phases are well controlled. The invention also relates to a method for launching such an aerostatic device that can be performed in the presence of wind. The invention also aims at providing such an aerostatic device and such a launch method complying with the rules of backup and security, and the constraints of respect for the environment. The invention also aims at providing such an aerostatic device and such a launching method that does not create any risk for the transported payload. The invention also aims at providing such an aerostatic device and such a launching method that do not impose significant constraints with respect to the launch site, and which can therefore be implemented from a wide variety of launch sites, especially on islands.
    Throughout the text, "vertical" means any direction or axis parallel to the direction of gravity.
    To do this, the invention relates to a method of launching an aerostatic device comprising: a load, called a payload, an elevation device comprising: an aerostat, said main aerostat, adapted to sustain the aerostatic device, o a line connecting the main balloon to the payload, - an aerostat, said auxiliary balloon, adapted to support at least part of the payload weight, in which process: - the auxiliary balloon is connected to the payload by keeping the payload captive with respect to the ground, - then raising the main balloon, - then the payload is released from the ground, characterized in that the auxiliary balloon is irremovably associated with the aerostatic device so as to be captive of the elevating device during flight of the aerostatic device. The invention also extends to an aerostatic device for implementing a launching method according to the invention. It therefore also relates to an aerostatic device comprising: a load, called a payload, an elevation device comprising: an aerostat, said main aerostat, adapted to sustain the aerostatic device, a suspension connecting the main aerostat to the payload, - an aerostat, said auxiliary aerostat adapted to support at least a portion of the payload weight, characterized in that the auxiliary aerostat is irremovably associated with the aerostatic device so as to be and remain captive of the elevation device. The invention also extends to a launching method implemented with an aerostatic device according to the invention.
    The payload is attached to one end of the line which is the lower end of the latter during the flight. Such a payload may be a load that is not necessary to ensure the flight of the aerostatic device, and may be dedicated to other functions, such as a scientific mission.
    An aerostatic device according to the invention makes it possible to maintain the auxiliary aerostat attached to the lifting device during all the flight phases of the aerostatic device, thus making it possible to comply with the safety and security rules relating to aerostatic devices. In addition, maintaining the captive auxiliary aerostat of the aerostatic device during all phases of flight makes it possible to respect the environment.
    An aerostatic device according to the invention is also easily transportable and can be brought on a terrain with difficult access, such as an island, a forest or other. Thus, the launch of such a device according to the invention can be performed on a small space, for example of the order of 500 m 2.
    In particular, the payload is connected to the auxiliary balloon so that the auxiliary balloon exerts a force on the payload opposite the weight direction of the payload. Thus, the force exerted on the payload makes it possible to support the weight of the payload - in general the weight of the payload increased by several kilograms, for example by about 50 kg -, and to take it off the ground so that the latter does not risk hitting the ground when launching the aerostatic device.
    Furthermore, advantageously and according to the invention, the payload is held off the ground at a non-zero distance before raising the main balloon.
    More particularly, the maintenance of the near payload but at a distance from the ground between the steps of raising and releasing the payload can be exercised by individuals (human operators), and / or by holding devices holding the load useful.
    In addition, in certain advantageous embodiments, the payload is released when the main balloon and / or a portion of the hanger, extending between a top of the auxiliary balloon and the main balloon, is at a height. relative to the ground greater than the height of the apex of the auxiliary aerostat.
    Advantageously and according to the invention, the auxiliary balloon is irremovably associated with the hanger of the lifting device, so as to extend above the payload, during the flight of the aerostatic device.
    More particularly, the auxiliary balloon is placed between the main balloon and the payload and has a base assembled to the hanger and a top held by the hanger. The auxiliary aerostat comprises at least one balloon defining an internal volume containing a gaseous fluid lift, generally bubble-especially pseudo-spherical or spherical-when inflated. Advantageously and according to the invention, the auxiliary aerostat is associated with the aerostatic device so that at least a portion of at least one balloon of the auxiliary aerostat extends along and around the suspension so that the hanger extends in at least a portion of the internal volume of the aerostat, the auxiliary aerostat remaining captive of the aerostatic device during the flight.
    More particularly, a section of the hanger extends from the base to the top of a balloon of the auxiliary aerostat in a volume delimited by this balloon of the auxiliary aerostat. The base and the top of the balloon of the auxiliary balloon being connected to the hanger, the auxiliary balloon is captive of the lifting device.
    Furthermore, each balloon auxiliary aerostat is adapted to receive in its internal volume a gaseous fluid lift, particularly lighter than air. In order to inject the gaseous lift fluid, the auxiliary aerostat can be assembled to an inflation sleeve adapted to transmit a gaseous fluid lift to the balloon of the auxiliary aerostat.
    Moreover, in certain advantageous embodiments, at least one balloon of the auxiliary aerostat is formed of an envelope comprising spindles fixed on tapes ensuring mechanical strength of these spindles.
    In certain advantageous embodiments, the base of a balloon auxiliary aerostat is open allowing the hanger to extend between the payload and the internal volume of the balloon auxiliary aerostat. In addition, the open base of the balloon also allows the gaseous fluid lift out through the base of the balloon during the ascent of the aerostatic device in the atmosphere.
    In addition, a gaseous lift fluid present in the auxiliary balloon is automatically discharged after raising the main balloon.
    More particularly, the auxiliary aerostat comprises a drain device adapted to discharge a gaseous fluid lift included in each balloon auxiliary aerostat.
    Thus, when the ball (s) of the auxiliary balloon is at least substantially empty of gaseous fluid lift, only the main balloon can raise the payload and the entire aerostatic device.
    A method according to the invention also makes it possible to maintain the auxiliary aerostat attached to the elevating device without this being a problem for the payload. Indeed, the top of a balloon of the auxiliary balloon being maintained at the hanger, the balloon does not fall on the payload when the auxiliary balloon is deflated.
    More particularly, advantageously and according to the invention, the gaseous lift fluid present in the auxiliary balloon is automatically discharged when the main balloon rises, relative to the ground, to a height greater than the payload.
    More particularly, the gaseous lift fluid present in the auxiliary balloon is automatically discharged when the main balloon rises, relative to the ground, to a height greater than the height at which a top of a balloon of the auxiliary balloon is placed.
    In certain advantageous embodiments, the device for emptying a balloon of the auxiliary aerostat is a discharge sleeve comprising: a first end assembled in communication of the gaseous fluid that is slidable with an upper light of this balloon, link, adapted to allow a passage of gaseous fluid lift from the internal volume of the balloon to the exhaust sleeve, - a second end assembled to the hanger between the balloon auxiliary aerostat and the main balloon.
    More particularly, the evacuation sleeve extends around the hanger so that the evacuation sleeve remains captive of the aerostatic device during the flight.
    Such an evacuation sleeve thus guides the gaseous lift fluid present in a balloon of the auxiliary aerostat to the second end of the evacuation sleeve, and thus to the outside of the evacuation sleeve, when the latter is positioned at least substantially vertically, so as to empty the auxiliary aerostat.
    In addition, in some embodiments of the invention, a section of the hanger extends in at least a portion of a volume defined by a wall of a discharge sleeve. In particular, the connecting lumen is traversed by the hanger.
    Moreover, such a discharge sleeve is simple to manufacture. In addition, the use of an evacuation sleeve makes it possible not to damage the balloon of the auxiliary aerostat by emptying it of the lifting fluid that it contains. Indeed, it is not necessary to tear the ball of the auxiliary aerostat to empty the latter. Thus, the balloon of the auxiliary aerostat and the evacuation sleeve can be reused at the end of the flight, if they are not destroyed on the descent.
    The second end of the evacuation sleeve is assembled to the hanger so as to allow the passage of the gaseous fluid out of the evacuation sleeve. More particularly, the second end of the exhaust sleeve is folded down to the ground at a height less than its first end before raising the main balloon. Thus, the gaseous fluid lift present in the auxiliary balloon can not escape before raising the main balloon. When the main balloon rises, it suspends the hanger, thus allowing the evacuation sleeve to be positioned upwards, that is to say with the second end of the evacuation sleeve that s raises to be positioned above the first end of the evacuation sleeve and the top of the balloon of the auxiliary aerostat. In this upward position of the discharge sleeve, the gaseous lift fluid present in the auxiliary aerostat can escape from the auxiliary aerostat and the evacuation sleeve through the second end of the evacuation sleeve.
    In some embodiments, the second end of the exhaust sleeve is assembled to a balloon of the main balloon. Thus, the gaseous lift fluid present in the auxiliary aerostat can be transferred to the balloon of the main balloon when the evacuation sleeve is positioned upwards. The gaseous lift fluid present in the auxiliary balloon is therefore used to sustain at least a portion of the payload before the ascent of the entire aerostatic device and then to sustain at least part of the aerostatic device during flight phases. this last. The dual functionality of the gaseous lift fluid present in the auxiliary aerostat reduces the amount of gaseous fluid lift injected into the main balloon before the launch of the aerostatic device and thus reduces the cost of a flight of an aerostatic device according to the invention.
    Advantageously and according to the invention, such a discharge sleeve provides a drain device whose operation is automatic, simple and easy to implement.
    In certain embodiments according to the invention, the auxiliary balloon comprises at least one central balloon extended by a central evacuation sleeve, the line passing through this central balloon and this evacuation sleeve. Nothing prevents the provision of other balls, in particular reported on the side of the central balloon and / or associated with the line in parallel with the central balloon, each balloon being also extended by an evacuation sleeve to allow it to be emptied. second end is fixed the hanger. Preferably, the auxiliary balloon consists exclusively of a central balloon extended by a central evacuation sleeve.
    In a preferred embodiment and according to the invention, the central discharge sleeve comprises a first wall extending around the hanger and a second wall extending around and along the first wall and having ends assembled to the first wall. The first wall has, at least at one end of the exhaust handle, at least one passage allowing the introduction of the gaseous fluid into the radial space between the first wall and the second wall for inflating this radial space , and deflating this radial space during the evacuation of gaseous fluid lift from the auxiliary aerostat.
    The volume of gaseous fluid between the first wall and the second wall allows to sustenter the section of the suspension passing through the evacuation sleeve so that the hanger does not come to split by its own weight the balloon of the auxiliary aerostat, before the launch and during the launch.
    In addition, the auxiliary aerostat comprises an assembly device assembling the central balloon of the auxiliary aerostat at the first end of the central evacuation sleeve, the assembly device having a light forming the connecting light of the central balloon. so that the hanger can extend into the auxiliary aerostat and into the central exhaust sleeve through the connecting light of the central balloon of the auxiliary aerostat.
    More particularly, the assembly device comprises: a polar ring having a light forming the connecting light of the central balloon so that the hanger can extend into the auxiliary aerostat and into the central evacuation sleeve while passing through the light connecting the central balloon of the auxiliary aerostat, - a ferrule facing the light of the polar ring and assembled to the pole ring, the central evacuation sleeve being assembled to the ferrule. The invention also relates to a launching method and an aerostatic device characterized in combination by all or some of the characteristics mentioned above or below. Other objects, features and advantages of the invention will become apparent on reading the following description of one of its embodiments given in a non-limiting manner and which refers to the appended figures in which: FIG. 1 is a diagram of principle (not corresponding to a real state of the device) of an aerostatic device according to the invention, - Figure 2 is a diagram of the assembly between the central balloon of the auxiliary aerostat and the central evacuation sleeve - Figures 3 to 10 are schematic representations of the steps of a method of launching an aerostatic device according to the invention.
    An aerostatic device, shown in FIG. 1, comprises an elevating device 21 adapted to sustain a load 22 of this aerostatic device.
    The payload 22 may, for example, include vehicles or devices for performing measurements in the stratosphere, in the fields of meteorology, atmospheric chemistry and astronomy in the context of scientific missions. These measuring devices can be placed on a nacelle.
    The lifting device 21 comprises a main aerostat 23 for sustaining the entire aerostatic device 20 in the atmosphere. More particularly, the main balloon 23 comprises a balloon 24 defining an internal volume that may contain a gaseous fluid lift, particularly lighter than air. The main aerostat 23 is connected to the useful load 22 by a hanger 26 of the lifting device 21. More particularly, in the embodiment shown, a first end of the hanger 26 is assembled to the payload 22 and a second end of the hanger 26 is assembled to a base of a parachute 27. The main aerostat 23 is assembled at the top of the parachute 27 so as to be connected to the hanger 26. Thus, at the end of a mission, the main aerostat 23 can be detached from the rest of the aerostatic device 20 in order to be able to recover the useful load 22 from the ground the fall into the atmosphere is slowed down by the parachute 27. Nevertheless, nothing prevents the hanger 26 from being directly assembled to the main balloon 23 without using a parachute 27 in the aerostatic device 20. The hanger 26 comprises at least one strap, in particular two parallel straps held spaced from each other by rigid crosspieces regularly distributed along the hanger 26. Advantageously, each strap has orifices, said eyelets, distributed along its length . In certain embodiments, the hanger may be formed of one or more cables, one or more chains or any other mechanical connection member including flexural flexibility and rigid traction.
    The aerostatic device 20 also includes an auxiliary aerostat 28. The auxiliary balloon 28 is held at the hanger 26 of the lifting device 21 between the payload 22 and the main balloon 23. More particularly, in the embodiment shown, the auxiliary aerostat 28 is placed between the payload 22 and the parachute 27. The auxiliary aerostat 28 comprises at least one balloon 29 defining an internal volume that may comprise a gaseous fluid that is slidable, especially lighter than air. In the embodiment shown, the auxiliary aerostat 28 has a single central balloon 29.
    The balloon 29 of the auxiliary aerostat 28 may be formed of any aerostatic balloon. For example, it consists of an envelope comprising spindles 34 fixed on tapes 35 ensuring mechanical strength of these spindles 34. More particularly, each strip 35 extends from a base 31 to an apex 33 of the balloon 29. the auxiliary aerostat 28. The balloon 29 is in the general shape of a pseudo-spherical bubble.
    More particularly, the envelope of the balloon 29 is made of a light polymeric material. For example, the envelope of the balloon 29 is made of polyethylene. More particularly, the envelope of the balloon 29 has a thickness between 10pm and 50pm, for example of the order of 25pm.
    The balloon 29 of the auxiliary balloon 28 is dimensioned so as to be able to lift the payload 22 while being able to be held close to the ground.
    The balloon 29 of the auxiliary aerostat 28 includes a so-called connection light 36 at its apex 33.
    The base 31 of the balloon 29 of the auxiliary aerostat 28 is connected to the payload by an assembly member, for example as described by FR 2 472 971. In addition, the base 31 of the balloon 29 of the aerostat 28 auxiliary, more particularly spindles 34, has an opening 32 between the tapes 35 possibly allowing the gaseous lift fluid to exit through the base 31 of the auxiliary aerostat 28 after the launch during the ascent of the aerostatic device 20 in the atmosphere.
    Furthermore, the balloon 29 of the auxiliary aerostat 28 has a skirt 55 assembled close to the base 31 of the balloon 29. In the embodiment shown, the skirt 55 has a shape of a cylinder of revolution, one end of which is assembled by balloon spindle welding 29. The skirt 55 makes it possible to prevent the wind from infiltrating the balloon 29 of the auxiliary balloon 28.
    In order to connect the main aerostat 23 to the useful load 22 and to hold the balloon 29 of the auxiliary aerostat 28 captive of the aerostatic device 20, the hanger 26 passes through the light 36 connecting the balloon 29 and the opening 32 on the balloon 29. the base 31 of the balloon 29 so that a section of the hanger extends into the internal volume of the balloon 29 of the auxiliary balloon 28. The balloon 29 of the auxiliary balloon 28 is thus captive of the hanger 26.
    Thus, in the embodiment shown, the hanger 26 connects the load 22 useful to the parachute 27 through the auxiliary balloon 28, and in particular the light 36 connecting the balloon 29. The auxiliary balloon 28 also comprises a handle 38 discharging the gaseous fluid lift present in the auxiliary balloon 28 to the outside of the auxiliary balloon 28. The exhaust sleeve 38 thus makes it possible to empty the gaseous lift fluid present in the balloon 29 of the auxiliary aerostat 28. The evacuation sleeve 38 is held at the hanger 26 of the elevating device 21, and extends the balloon 29 from and above the connecting lumen 36.
    The evacuation sleeve 38 comprises a first wall 39, a first end 40 of which is connected to the top 33 of the balloon 29 of the auxiliary aerostat 28 by means of an assembly device 37.
    The balloon 29 comprises in particular an upper pole ring 59, assembling the upper ends of the spindles 34 of the balloon 29, and having a central lumen forming the balloon connection slot 36.
    In addition, the central lumen of the polar ring 59 is adapted to allow the passage of the hanger 26 between the internal volume of the balloon 29 and the sleeve 38 of evacuation of the auxiliary aerostat 28. In certain advantageous embodiments, the central lumen of the polar ring 59 has a circular shape.
    The assembly device 37 comprises a ferrule 60 having a cylindrical sleeve of revolution extending axially upwardly a crown forming the base of the ferrule 60. The ferrule is centered on the central lumen of the ring 59 polar. The ring of the shell 60 is assembled to the ring 59 polar, for example by screws or bolts, above the latter. The ferrule 60 may be made of a metallic material.
    The ferrule sleeve 60 is introduced into the first end 40 of the discharge sleeve 38 and the first wall 39 of the exhaust sleeve 38 is fixed, for example by gluing, to the ferrule sleeve 60.
    The hanger 26 passes through the ferrule 60 so as to extend longitudinally in the balloon 29 and in the evacuation sleeve 38.
    The ferrule 60 comprises at least one internal projection in the form of a loop forming a passage through which at least one-in particular a single-strap of the hanger 26 and allowing to allow relative axial sliding of the assembly device 37 with respect to the hanger 26 while maintaining the suspension 26 radially. In some embodiments, the shell 60 comprises an internal projection for the passage of each strap of the hanger 26. The top 33 of the balloon 29 can thus slide along the hanger in a function of the volume of gaseous fluid present in the balloon 29 during the ascent of the aerostatic device. Indeed, the height of the top 33 of the balloon 29 relative to the hanger varies with the volume of the gaseous fluid in the balloon 29, the height of the top 33 being lower when the balloon 29 is filled with a gaseous fluid lift that when it empties itself. Straps may be provided knotted internal projections and attached to the hanger 26 (passage to an eyelet of the latter) to limit the downward sliding of the top 33 balloon 29 relative to the hanger 26.
    Thus, the first wall 39 of the exhaust sleeve 38 is of tubular shape and extends around the hanger 26, from the auxiliary aerostat 28 to the main aerostat 23. The first wall 39 of the evacuation sleeve 38 then extends from the first end 40 to a second end 41, assembled to the hanger 26, the sleeve 38 of evacuation.
    The second end 41 is formed of at least one strap 57, for example four strips 57, fixed to the hanger 26, to prevent it from sliding along the hanger so that the handle 38 of evacuation is held at the hanger 26 and can not fall on the balloon 29 of the auxiliary balloon 28. The straps 57 may be attached to the hanger 26 by knotting in an eyelet of a strap of the hanger 26, or otherwise, for example by a seam.
    The straps 57 have a length chosen to ensure the proper operation of the evacuation sleeve 38 as a function of the distance over which the top 33 of the balloon 29 can slide along the hanger 26 during the ascent of the aerostatic device.
    When the auxiliary aerostat 28 is empty of lift gaseous fluid, the straps 57 make it possible to keep the top 33 of the balloon 29 of the auxiliary aerostat 28 at the same height with respect to the hanger 26. The auxiliary aerostat 28 therefore does not fall back. not on the load 22 useful when it is deflated. There is then no risk of attachment of the auxiliary aerostat 28 on the payload 22. The auxiliary aerostat 28 does not interfere with the load 22 useful in the exercise of its mission.
    The evacuation sleeve 38 makes it possible to guide the lifting gaseous fluid present in the auxiliary aerostat 28 to the outside, the gaseous fluid of the balloon 29 passing through the connecting lumen 36 when the second end 41 of the evacuation sleeve 38 is positioned higher than the first end 40 of the exhaust sleeve 38. Thus, FIG. 1 is a schematic diagram for visualizing the arrangement of the elements of the aerostatic device with respect to each other, but is not representative of a real state of the aerostatic device when the auxiliary aerostat and the main balloon are aligned along a vertical axis, because in this position the balloon 29 of the auxiliary balloon is at least partially deflated, and not inflated as shown in Figure 1.
    In addition, the discharge sleeve 38 also makes it possible to prevent the evacuation of the lift gaseous fluid from the auxiliary aerostat 28 when the second end 41 of the evacuation sleeve 38 is positioned lower than the first end 40 of the 38 exhaust sleeve and the second end 41 of the exhaust sleeve 38 is oriented downwards (towards the ground).
    The discharge sleeve 38 further comprises a second wall 42 extending around the first wall 39 and having a length less than the first wall 39. More particularly, the second wall 42 has ends joined to the first wall. 39 by welding or by an adhesive, or by any other means of assembly.
    The second wall 42 delimits a radial space that can be inflated gaseous lift fluid to sustain the hanger 26 so that the latter does not come into contact with the balloon 29 of the aerostat 28 auxiliary. In addition, the inflated gaseous fluid radial space maintains the tubular shape of the exhaust sleeve 38 to facilitate the evacuation of the gaseous fluid present in the balloon 29 of the auxiliary aerostat 28. Preferably, the first wall 39 has a thickness sufficient to not be damaged and / or pierced by the hanger 26, during inflation of the evacuation sleeve 38 for example. Furthermore, the first wall 39 and the second wall 42 are made of polymer material. In some embodiments, the first wall 39 and the second wall 42 are made of polyethylene. Such an exhaust sleeve 38 is thus simple to manufacture.
    In addition, the first wall has openings 58 for a gaseous fluid to circulate in the radial space between the first wall 39 and the second wall 42 of the exhaust sleeve 28. Such lights 58 are placed at least near the end of the second wall 42 closest to the second end 41 of the first wall 39, to allow evacuation of the gaseous fluid from this radial space when the sleeve 38 discharge is in the evacuation position of the gaseous fluid (second end 41 higher than the first end 40). Other lights may be provided near the first end to allow or facilitate inflation of the radial space of the exhaust sleeve 38.
    In addition, the auxiliary aerostat 28 comprises an inflation sleeve 43 for injecting a gaseous fluid lift into the balloon 29 of the auxiliary aerostat 28 to inflate it. The inflation sleeve 43 thus has a first end assembled to an inflation orifice of the balloon 29 and a second end for injecting the gaseous fluid lift into the inflation sleeve 43 and then into the internal volume of the balloon 29. Furthermore, when the balloon 29 is inflated, the second end of the inflation sleeve 43 is closed and attached to the hanger, below the balloon 29. Furthermore, the inflation sleeve 43 is made of polymer material. In some embodiments, such as that shown in Figure 1, the inflation sleeve 43 is made of polyethylene. In addition, the gaseous lift fluid injected into the auxiliary aerostat 28 is selected from the group consisting of gaseous compositions lighter than atmospheric air, comprising at least one gas lighter than atmospheric air. For example, the gaseous fluid lift is made of helium, hydrogen or hot air.
    Furthermore, the balloon 29 of the auxiliary aerostat 28 also comprises aerodynamic braking devices 44 placed on an outer surface of the envelope of the balloon 29, preferably in the vicinity of the equator of the balloon (wider part of the balloon). inflated state). The aerodynamic braking devices 44 have, for example, a trapezoidal shape whose three sides are joined to the spindles 34 of the balloon 29 by welding and a side oriented towards the top of the balloon is free of these spindles 34. These braking devices 44 make it possible to limit the rate of climb of the auxiliary balloon 28 so that it rises less rapidly than the main balloon 23 so as not to hinder the elevation of the latter.
    A method of launching an aerostatic device according to the invention is shown in FIGS. 3 to 9. During a step shown in FIG. 3, a first halyard 53 is passed through the evacuation sleeve 38 so as to pass through it entirely. and a second halyard 56 is placed in the balloon 29 of the auxiliary balloon 28 so as to pass completely. A first end of the first halyard 53 is assembled to the hanger 26 so that by pulling on an opposite end of the first halyard 53, the hanger 26 is introduced into the evacuation sleeve 38 and crosses it longitudinally. . Then, a first end of the second halyard 56 is assembled to the hanger 26 so that by pulling on an opposite end of the second halyard 56, the hanger 26 is introduced inside the balloon 29 and crosses it longitudinally.
    The discharge sleeve 38 is then assembled to the balloon 29 by the assembly device 37 during a subsequent step 46 shown in FIG. 4.
    Then, during a step 47 shown in Figure 5, the exhaust sleeve 38 is inflated by its second end 41 with a gaseous fluid lift, lighter than air. The gaseous fluid then passes through the openings 58 to inflate the radial space between the first wall 39 and the second wall 42 of the exhaust sleeve 38.
    The balloon 29 of the auxiliary balloon 28 is then inflated with a lighter gaseous fluid, lighter than air, injected into the balloon 29 by the inflation sleeve 43 during a step 48 shown in FIG. step 48 of inflation, the lower end of the skirt 55 is preferably closed and the base 31 of the balloon 29 is held on the ground by a holding device (not shown). The balloon 29 then rises in the air gradually.
    When the balloon 29 has risen vertically, the launching method then comprises a step 49 in which the assembly member of the base 31 of the balloon 29 is hooked to the hanger 26, for example to a rigid cross member of this last, and hangs the end of the portion of the hanger 26 coming out of the balloon 29 by its base 31 to the payload 22. The straps 57 are fixed from the evacuation sleeve 38 to the hanger 26 and a point is connected. of the portion of the hanger 26 coming out of the evacuation sleeve 38 to a cable 61 fixed to the ground whose length is such that the second end 41 of the evacuation sleeve 38 is kept lower than the first end 40 of this evacuation sleeve. The skirt 55 of the base 31 of the balloon 29 is opened. The base 31 is then released from the balloon 29 with respect to the ground so that the latter takes off and lifts the load 22 that is useful. The payload 22 is, however, maintained at a certain distance from the ground, for example by operators as shown in FIG. 7, this distance being sufficient to prevent this load 22 from hitting the ground during the subsequent launching of the aerostatic device. The maintenance of the useful load 22 close to the ground can be exerted by individuals or holding devices (not shown) retaining the load 22 useful.
    During this step 49, the exhaust sleeve 38 is held by the cable 61 in its initial position in which it extends from the top 33 and outside the balloon 29 of the auxiliary balloon 28 towards the ground. Thus, the first end 40 of the exhaust sleeve 38 is placed at a height greater than the height of the second end 41 of the exhaust sleeve 38 relative to the ground. Such a position of the discharge sleeve 38 makes it possible to prevent the gaseous lift fluid present in the auxiliary aerostat 28 and in the evacuation sleeve 38 from escaping through the second end 41 of the evacuation sleeve 38. and therefore to maintain the inflated auxiliary balloon 28 before the release of the main balloon 23. The main balloon is also inflated with lighter gaseous fluid lighter than air, by injecting the gaseous fluid lift into the balloon 24, during all or part of the aforementioned steps 45 to 49 and / or at the end of step 49 of lifting the payload 22 by the auxiliary aerostat 28. During this inflation, the main aerostat 23 is held relative to the ground by a holding device (not shown).
    The launching method also includes a subsequent step of releasing the main balloon 23 in which the main balloon 23 is released from a ground holding device such that the main balloon 23 is mounted in the balloon 23. atmosphere. This step 50 is performed after step 49 of lifting the load 22 useful. During this step 50, it also frees the hanger 26 of the cable 61 so that the second end 41 of the exhaust sleeve 38 can rise under the effect of the elevation of the main aerostat 23.
    In addition, the payload 22 and the auxiliary balloon 28 are maintained prior to the release of the main balloon 23 and after its release during the beginning of the elevation of the main balloon 23 at a height to prevent the Useful load 22 does not hit the ground.
    In the subsequent step 50, the payload 22 is released when the base of the main balloon 23 rises, relative to the ground, to a height sufficient to avoid any risk of subsequent contact of the payload 22 with the floor, especially at a height greater than the height of the apex 33 of the balloon of the auxiliary aerostat 28. Preferably, the useful load 22 is released when the second end 41 of the evacuation sleeve 38 and the entire portion of the hanger 26 extending between this second end 41 and the main aerostat 23 are at a height from the upper ground at the height of the apex 33 of the balloon 29 of the aerostat 28 auxiliary. Thus, the main aerostat 23 and the auxiliary aerostat 28 sustent the load 22 useful so as to rise in the atmosphere with the entire aerostatic device.
    The gaseous lift fluid present in the auxiliary aerostat 28 is evacuated from the evacuation sleeve 38 when the base of the main aerostat 23 rises to a height greater than the height of the top of the balloon 29 of the auxiliary aerostat 28 . More particularly, the elevation of the main aerostat 23 makes it possible to support the hanger 26 so as to also raise the second end 41 of the evacuation sleeve 38 to a height greater than the height of the first end 40 of the sleeve 38 evacuation assembly to the balloon 29.
    Thus, the gaseous lift fluid present in the auxiliary aerostat 28 can escape from the latter by the second end 41 of the exhaust sleeve 38, emptying the auxiliary aerostat 28 during a step 51 of the device ascension 20 aerostatic in the atmosphere. The evacuation sleeve 38 makes it possible to obtain a device for emptying the lift gas from the auxiliary aerostat 28 whose operation is automatic, simple and reliable.
    In addition, the use of such an exhaust sleeve 38 makes it possible to empty the auxiliary aerostat 28 without tearing it. Indeed, it is not necessary to tear the ball 29 of the auxiliary balloon 28 to empty it. Thus, the auxiliary aerostat 28 and the evacuation sleeve 38 can be reused at the end of the flight if they are not subsequently destroyed during their descent into the atmosphere.
    In addition, during this step 51 of ascension, the gaseous lift fluid can also escape the balloon 29 by its base 31 open (Figure 9).
    When the auxiliary aerostat 28 is at least substantially empty, in a step 52, only the main aerostat 23 raises the load 22 useful. The auxiliary aerostat 28 (balloon 29, discharge sleeve 38 and inflation sleeve 43) remains fully assembled to the hanger 26 during the entire flight, and is held captive of the lifting device 21. The invention can be the subject of numerous variants with respect to the embodiment described above and shown. For example, the aerostatic device may comprise a plurality of main aerostats and / or a plurality of auxiliary aerostats of various shapes and / or sizes. In addition, an auxiliary balloon may comprise several balloons of various shapes and / or sizes, a single central balloon being traversed by the hanger connecting the payload to the main balloon. Moreover, the central balloon and the evacuation sleeve can be held relative to the hanger by any means other than those described above, for example by elastic cables or otherwise.
    Moreover, in certain embodiments, the second end 41 of the exhaust sleeve 38 is assembled to the balloon 24 of the main aerostat 23 so that the gaseous lift fluid present in the balloon 29 of the auxiliary aerostat 28 is transferred to the balloon 24 of the main balloon 23 when the second end 41 of the evacuation sleeve 38 rises to a height greater than the height of the first end 40 of the evacuation sleeve 38 assembled to the balloon 29 when step 50 of the payload release and step 51 of ascending the aerostatic device into the atmosphere. The lift gaseous fluid present in the balloon 29 of the auxiliary aerostat auxiliary aerostat is thus used to sustain at least part of the payload before the ascent of the entire aerostatic device and then to sustain the entire aerostatic device during step 50 of the payload release and step 51 of ascending the aerostatic device. This dual functionality of the lift gaseous fluid present in the balloon 29 of the auxiliary aerostat 28 makes it possible to reduce the amount of gaseous lift fluid injected into the balloon 24 of the main balloon before the launching of the aerostatic device 20 and thus makes it possible to reduce the cost of a flight of an aerostatic device according to the invention.
    For example, a device and method for launching an aerostatic device according to the invention can be used to raise a payload into the stratosphere for measurements in the context of a scientific mission. They can be the object of all other applications for the launch of an aerostatic device.
    权利要求:
    Claims (15)
    [1" id="c-fr-0001]
    1 / - A method of launching a device (20) aerostatic comprising: - a load, called load (22) useful, - a device (21) for elevation comprising: o an aerostat, said aerostat (23) main, adapted to support the aerostatic device (20), o a hanger (26) connecting the main balloon (23) to the load (22), - an aerostat, said aerostat (28) auxiliary, adapted to sustain at least a portion the weight of the useful load (22), in which process: - the auxiliary balloon (28) is connected to the useful load (22), keeping the load (22) useful captive with respect to the ground, - then raising the main aerostat (23), - then releasing the load (22) useful relative to the ground, characterized in that the auxiliary aerostat (28) is irremovably associated with the device (20) aerostatically to be captive of the lifting device (21) during the flight of the aerostatic device (20).
    [0002]
    2 / - launching method according to claim 1, characterized in that the aerostat (28) auxiliary is irremovably associated with the hanger (26) of the device (21) of elevation, above the payload, during the flight of the aerostatic device (20).
    [0003]
    3 / - launching method according to one of claims 1 or 2, characterized in that the auxiliary aerostat (28) is associated with the device (20) aerostatic so that at least a portion of at least one balloon (29 ) of the auxiliary aerostat (28) extends along and around the hanger (26), so that the auxiliary aerostat (28) remains captive of the aerostatic device (20) during flight.
    [0004]
    4 / - Launching method according to one of claims 1 to 3, characterized in that a gaseous lift fluid present in the aerostat (28) auxiliary is automatically discharged after raising the aerostat (23) main.
    [0005]
    5 / - launching method according to one of claims 1 to 4, characterized in that a gaseous lift fluid present in a balloon of the auxiliary aerostat (28) is automatically discharged by a sleeve (38) for evacuation of the auxiliary aerostat (28) comprising: a first connected end (40) of the gaseous lift fluid to an upper lumen of the balloon (29), referred to as a connecting lumen, adapted to allow the gaseous fluid to flow from the volume (30) internal of the balloon (29) towards the evacuation sleeve (38), - a second end (41) assembled to the hanger (26) between the balloon (29) of the auxiliary aerostat (28) and the main balloon (23).
    [0006]
    6 / - launching method according to claim 5, characterized in that the sleeve (38) of evacuation is folded towards the ground before raising the aerostat (23) main.
    [0007]
    7 / - A method of launching according to one of claims 5 or 6, characterized in that the sleeve (38) of evacuation extends around the hanger (26) so that the sleeve (38) evacuation remains captive of the aerostatic device (20) during flight.
    [0008]
    8 / - Aerostatic device (20) comprising: - a load, called load (22), - an elevation device (21) comprising: o an aerostat, said aerostat (23) main, adapted to sustain the device (20) ) aerostatic, o a line (26) connecting the main balloon (23) to the load (22) useful, - an aerostat, said auxiliary balloon (28) adapted to sustain at least a portion of the weight of the load (22) useful, characterized in that the auxiliary aerostat (28) is irremovably associated with the aerostatic device (20) so as to be captive of the elevating device (21).
    [0009]
    9 / - Device (20) aerostatic according to claim 8, characterized in that the aerostat (28) auxiliary is irremovably associated with the hanger (26) of the device (21) elevation.
    [0010]
    10 / - Device (20) aerostatic according to one of claims 8 or 9, characterized in that at least a portion of at least one balloon (29) of the aerostat (28) auxiliary extends along and around the hanger (26), so that the hanger (26) extends in at least a portion of the volume (30) internal of the auxiliary aerostat (28).
    [0011]
    11 / - Device (20) aerostatic according to one of claims 8 to 10, characterized in that the auxiliary aerostat (28) comprises a drain device adapted to discharge a gaseous fluid lift included in each balloon (29) of the auxiliary balloon (28).
    [0012]
    12 / - Device (20) aerostatic according to claim 11, characterized in that the device for emptying a balloon of the auxiliary aerostat (28) is an exhaust sleeve (38) comprising: - a first (40) assembled end in communication of the gaseous fluid lift to an upper lumen of the balloon (29), said connecting lumen, adapted to allow a passage of gaseous fluid lift from the volume (30) internal of this balloon (29) to the sleeve ( 38), - a second end (41) assembled to the hanger (26) between the balloon (29) of the auxiliary aerostat (28) and the main aerostat (23).
    [0013]
    13 / - Device (21) for elevation according to claim 12, characterized in that the sleeve (38) of evacuation extends around the hanger (26).
    [0014]
    14 / - Device (21) for elevation according to one of claims 12 or 13, characterized in that the sleeve (38) of discharge comprises a first wall (39) extending around the hanger and a second wall (42) extending around and along the first wall (39) and having ends joined to the first wall (39).
    [0015]
    15 / - Device (21) for elevation according to one of claims 12 to 14, characterized in that the aerostat (28) auxiliary comprises an assembly device (37) assembling the balloon (29) of the aerostat (28) auxiliary to the first (39) end of the discharge sleeve (38), the assembly device (37) having a light forming the balloon connecting light (29) so that the hanger (26) can extend into the auxiliary aerostat (28) and into the evacuation sleeve (38) through the connecting lumen of the balloon (29) of the auxiliary aerostat (28).
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    同族专利:
    公开号 | 公开日
    FR3052437B1|2021-05-21|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US3072367A|1961-06-28|1963-01-08|Michael O Evanick|Azimuth-stabilized balloon gondola|
    US3260480A|1964-08-18|1966-07-12|Fairchild Hiller Corp|Aerial balloon system|
    FR2136919A1|1971-05-07|1972-12-29|Nal Etu Spatiales Centre|
    WO2005081680A2|2003-09-09|2005-09-09|Universtiy Of Massachusetts|System and method for altitude control|
    US20120312919A1|2011-06-13|2012-12-13|Stephen Heppe|Lifting gas replenishment in a tethered airship system|CN111746774A|2020-06-01|2020-10-09|中国科学院空天信息创新研究院|High-altitude balloon issuing system and method|
    WO2021141945A1|2020-01-06|2021-07-15|Nanosys, Inc.|Rohs compliant mixed quantum dot films|
    US11097843B1|2020-02-03|2021-08-24|Space Perspective Inc.|Aerospace balloon system, parachute, and method of operation|
    法律状态:
    2017-06-30| PLFP| Fee payment|Year of fee payment: 2 |
    2017-12-15| PLSC| Publication of the preliminary search report|Effective date: 20171215 |
    2018-06-27| PLFP| Fee payment|Year of fee payment: 3 |
    2019-07-01| PLFP| Fee payment|Year of fee payment: 4 |
    2020-06-30| PLFP| Fee payment|Year of fee payment: 5 |
    2021-06-30| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1655489A|FR3052437B1|2016-06-14|2016-06-14|PROCESS FOR LAUNCHING AN AEROSTATIC DEVICE AND AEROSTATIC DEVICE WITH A CAPTIVE AUXILIARY AEROSTAT|FR1655489A| FR3052437B1|2016-06-14|2016-06-14|PROCESS FOR LAUNCHING AN AEROSTATIC DEVICE AND AEROSTATIC DEVICE WITH A CAPTIVE AUXILIARY AEROSTAT|
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