• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
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    • 专利摘要:
    There is provided a method and apparatus for deploying a spatial structure (102). The spatial structure (102) is attached to a base (108) with release mechanisms (110) when the base (108) is at a first position. The base (108) is moved from the first position to a second position to deploy the spatial structure (102). The release mechanisms (110) are moved substantially at the same time to release the spatial structure (102) of the base (108) without applying a transverse load to the spatial structure (102) when the base (108) moves from the first position at the second position to deploy the spatial structure (102).
    公开号:FR3025783A1
    申请号:FR1556767
    申请日:2015-07-17
    公开日:2016-03-18
    发明作者:Thomas E Robles；Trevor Scott Howard
    申请人:Boeing Co；
    IPC主号:
    专利说明:

    [0001] This disclosure relates, in general, to spatial structures and, in particular, the deployment of spatial structures. More particularly, the present disclosure relates to a method and apparatus for deploying a spatial structure, such as a satellite.
    [0002] Launch vehicles can be used to carry payloads, human beings or both of the Earth in outer space. For example, a launch vehicle may carry a payload, such as a satellite, in outer space. When the launch vehicle has reached a desired distance from the Earth for deployment of the satellite, the satellite is separated from the launch vehicle by the operation of one or more deployment mechanisms. Depending on the conditions and systems used during deployment, the satellite may fall after separation from the launch vehicle. For example, some satellite deployment systems use explosive bolts or multiple push springs to separate the satellite from the launch vehicle. These types of deployment systems release the satellite at several points. The unequal force distribution potential applied to separate the satellite from the launch vehicle at these different points may be such that the satellite falls. Some satellites may include a propulsion system to reduce or stop the fall, as well as to change the orientation of the satellite or perform other maneuvers. However, smaller satellites may not have these types of systems to reduce size, weight, or both in the satellite. Smaller satellites with limited or no attitude control are classified from the category of microsatellites to femtosatellites. The satellites of the category of microsatellites have a mass up to 100 kg and the satellites of the category of femtosatellites have a mass of 0,001 kg to 0,01 kg. For example, a cubesat is a type of miniaturized satellite. A cubesat has a volume of one liter and a mass less than or equal to 1.33 kg. The dimensions of a cubesat 1U are 10 cm x 10 cm x 10 cm. The dimensions of a cubesat 3U are 30 cm x 10 cm x 10 cm.
    [0003] 3025783 2 A cubesat usually carries one or two scientific instruments. Nevertheless, a cubesat does not generally comprise a propulsion system. Consequently, the fall that may occur during deployment may exceed the torque capacity of other attitude control actuators, such as reaction wheels, which can therefore lead to falling speeds that can not be effectively reduced or reduced. eliminated by cubesat subsystems. It would therefore be desirable to provide a method and apparatus that takes into account at least some of the above-mentioned problems as well as other potential problems. An embodiment of the present disclosure provides an apparatus comprising a base and release mechanisms. The base is mobile. The release mechanisms are associated with the base. The release mechanisms engage elements of a spatial structure to fix the spatial structure at the base when the base is at a first position and the release mechanisms move substantially at the same time to move out of control. 15 elements and release the spatial structure of the base during an acceleration without applying a transverse load to the spatial structure when the base moves to a second position by causing the deployment of the spatial structure. Advantageously, with the apparatus, at least one of a fall of spatial structure or shock applied to the spatial structure can be reduced when the spatial structure is deployed. Preferably, the spatial structure is selected from one of a satellite, a space station and a spacecraft. In preferred embodiments of the present disclosure, one or more of the following arrangements may be used: the apparatus further comprises: a biasing system which moves the base from the first position to the second position; the apparatus further comprises: a housing having an opening, wherein the base and the release mechanisms are within the housing and wherein the spatial structure is within the housing when the spatial structure is fixed at the base; and a door that moves between a closed position and an open position and covers the opening when in the closed position; the apparatus further comprises: a vibration reduction structure associated with the door, wherein the vibration reduction structure is in contact with the spatial structure so as to reduce vibrations in the spatial structure when the spatial structure is fixed to the base by the release mechanisms and the door is in the closed position; the apparatus further comprises: a locking system which holds the base at the first position when the door is in the closed position; the release mechanisms are at closed positions when the base is in the first position and move substantially at the same time to open positions to release the spatial structure of the base without applying the transverse load to the spatial structure when the base moves from the first position to the second position to deploy the spatial structure; the apparatus further comprises: a restraint system which prohibits the movement of the release mechanisms to release the spatial structure when the base is in the first position; a release mechanism in the release mechanisms comprises: a contact point associated with the base, wherein the contact point supports an element on the spatial structure; a lever that is movable and secures the element to the point of contact when the lever is in a closed position; and a biasing device which moves the lever from the closed position to an open position as the base moves from the first position to the second position such that the member is out of engagement with the point of contact; the contact point comprises: a structure extending from a surface of the base and having a shape that engages with the element on the spatial structure; the release mechanisms comprise: three release mechanisms. Another embodiment of the present disclosure provides a method for deploying a spatial structure. The spatial structure is attached to a base with release mechanisms that engage with elements of the spatial structure when the base is in a first position. The base is moved from the first position to a second position to deploy the spatial structure. The release mechanisms are moved substantially at the same time to disengage the elements and to release the spatial structure of the base 5 without applying a transverse load to the spatial structure as the base moves from the first position to the second position to deploy the spatial structure. Advantageously, the spatial structure comprises elements that are engaged with the release mechanisms when the base is at the first position, wherein the displacement of the release mechanisms comprises the rotation of levers in the release mechanisms of the positions closed to open positions as the base moves from the first position to the second position. Displacement of the release mechanisms further includes applying an axial force, perpendicular to the base, to the spatial structure to elements on the spatial structure engaged with contact points in the release mechanisms while the base moves from the first position to the second position so that the spatial structure accelerates in a direction of the axial force during the deployment of the spatial structure, and placing the elements of the spatial structure out of engagement with the contact points when at least one of the deceleration of the base or the reaching of the second position by the base occurs.
    [0004] Preferably, the rotation of the levers comprises rotating the levers with biasing devices to move the release mechanisms from the closed positions to the open positions as the base moves from the first position to the second position so that the levers do not fix. plus the elements at the points of contact. Advantageously, with the method of deploying a spatial structure, at least one of a fall in spatial structure or shock applied to the spatial structure can be reduced when the spatial structure is deployed. Preferably, the spatial structure is selected from one of a satellite, a space station and a spacecraft. The other embodiment of the present disclosure provides a method for deploying a spatial structure, the method comprising: attaching the spatial structure to a base with release mechanisms that engage with elements of the spatial structure when the base is in a first position; Moving the base from the first position to a second position to deploy the spatial structure; and moving the release mechanisms substantially at the same time to disengage the elements and release the spatial structure of the base without applying a transverse load to the spatial structure as the base moves from the first position to the second position to deploy the spatial structure. In preferred embodiments of the present disclosure, one or more of the following arrangements may be used: the base and the spatial structure are located in a housing when the base is in the first position and the method further comprises: opening a door for the housing to expose an opening in the housing for deploying the spatial structure from the housing, wherein the spatial structure moves out of the housing through the opening as the base moves from the first position in the second position; The method further comprises: contacting the spatial structure with a vibration reduction structure associated with the door in the housing in which the spatial structure is located, wherein the vibration reduction structure reduces vibrations in the the spatial structure when the door is closed; The movement of the base comprises: moving the base from the first position to the second position with a biasing system after opening the door; the spatial structure comprises elements which are engaged with the release mechanisms when the base is in the first position, and the movement of the release mechanisms comprises: the rotation of levers in the closed position release mechanisms; open positions as the base moves from the first position to the second position; applying an axial force, perpendicular to the base, to the spatial structure to elements on the spatial structure engaged with contact points in the release mechanisms as the base moves from the first position to the second position so that the spatial structure accelerates in a direction of the axial force during the deployment of the spatial structure; and placing the non-engaging spatial structure elements of the contact points when at least one of the deceleration of the base or the reaching of the second position by the base occurs. The features and functions can be realized independently in various embodiments of the present disclosure or they can be combined in other embodiments, the details of which can be better appreciated by reading the following description with reference. in the accompanying drawings. The novel features considered to be specific to the illustrative embodiments are defined in the appended claims. The illustrative embodiments, as well as the preferred mode of use and other objects and features thereof, will be better understood upon reading the following detailed description of an illustrative embodiment of the present invention. This disclosure is with reference to the accompanying drawings in which: FIG. 1 is an illustration of a block diagram of a spatial structure deployment environment according to an illustrative embodiment; Fig. 2 is an illustration of a block diagram of a release mechanism according to an illustrative embodiment; Fig. 3 is an illustration of a space structure deployment system according to an illustrative embodiment; Figure 4 is an illustration of a space structure deployment system according to an illustrative embodiment; Fig. 5 is an illustration of a space structure deploying system moving a satellite for deployment according to an illustrative embodiment; Figure 6 is an illustration of a space structure deploying system moving a satellite for deployment according to an illustrative embodiment; Fig. 7 is an illustration of a space structure deploying system moving a satellite for deployment according to an illustrative embodiment; Fig. 8 is an illustration of a release mechanism according to an illustrative embodiment; Figure 9 is an illustration of a space structure deployment system according to an illustrative embodiment; Fig. 10 is an illustration of a space structure deployment system according to an illustrative embodiment; Fig. 11 is an illustration of a platform with a plurality of spatial structure deployment systems according to an illustrative embodiment; Fig. 12 is an illustration of a flowchart of a process for deploying a spatial structure according to an illustrative embodiment; and Fig. 13 is an illustration of a flowchart of a process for moving release mechanisms according to an illustrative embodiment. The illustrative embodiments recognize and consider one or more different considerations. For example, the illustrative embodiments recognize and recognize that deployment systems currently in use with devices may apply different amounts of force to the satellite. For example, explosive bolts, springs, dampers, and other devices may provide different amounts of force when used to release a satellite from a platform for deployment of the satellite. These types of devices can generate different amounts of force, speeds or both occurring at different parts of the satellite and potentially at slightly different times. This situation can lead to an unwanted fall of the satellite. The illustrative embodiments provide a solution to the technical problem involving an unwanted fall of a spatial structure, such as a satellite. In addition, the illustrative embodiments provide a method and apparatus for deploying a spatial structure. In an illustrative embodiment, an apparatus includes a base and release mechanisms. The base is mobile. The release mechanisms are associated with the base. The release mechanisms fix a spatial structure at the base when the base is at a first position. The release mechanisms move substantially at the same time to release the spatial structure of the base during acceleration without applying a transverse load to the spatial structure as the base decelerates to a second position causing the deployment of the structure. Space. The apparatus has a technical effect of reducing or eliminating the fall of the spatial structure. Fig. 1 is an illustration of a block diagram of a spatial structure deployment environment according to an illustrative embodiment. In a spatial structure deployment environment 100, a spatial structure 102 is deployed from a platform 104 using a spatial structure deployment system 106. This deployment takes place in outer space. In this illustrative example, the spatial structure 102 is a structure used in outer space. Outer space is a space or void that exists between celestial bodies, including the Earth. For example, outer space may be a space having a particle density and a pressure constituting the closest approximation to a perfect vacuum. Outer space can be defined by the Karman line at an altitude of 100 kilometers above sea level. The Karman line is conventionally used as the beginning of outer space in space and aerospace records. The spatial structure 102 can take various forms. For example, the spatial structure 102 may be selected from a satellite, a cubesat, a space station, a spacecraft or other suitable structure.
    [0005] In this illustrative example, the platform 104 may take various forms. For example, the platform 104 may be selected from a space station, rocket, shuttle, asteroid, or other suitable type of platform. In this illustrative example, the spatial structure deployment system 106 is associated with the platform 104. When a component is "associated" with another component, the association is a physical association in the examples shown. For example, a first component, namely the spatial structure deployment system 106, can be considered to be physically associated with a second component, namely the platform 104, by at least one of a fixation at the second component, of a connection to the second component, of a mounting on the second component, a welding on the second component, an attachment to the second component or a connection to the second component in another suitable manner . The first component can also be connected to the second component using a third component. The first component may also be considered to be physically associated with the second component as an integral part of the second component, by constituting an extension of the second component or both. In this illustrative example, the spatial structure deployment system 106 has a number of different components. As shown, the spatial structure deployment system 106 includes the base 108, the release mechanisms 110 and the biasing system 112. The base 108 is a movable structure. In particular, the base 108 may be movable between a first position 114 to which the spatial structure may be attached and a second position 116 to which the spatial structure may be deployed by the deployment system. In the illustrative example, the guide 117 is a structure which guides the movement of the base 108 between the first position 114 and the second position 116. The guide 117 may be, for example, a rail, several rails, or other structure appropriate. The guide 117 reduces the transverse load 118 that may occur on the spatial structure 102. In the illustrative example, the transverse load 118 is a load relative to the base 108. For example, the transverse load 118 is an orthogonal load in the direction 120 the force 122 generated by the movement of the base 108 from the first position 114 to the second position 116. As shown, the release mechanisms 110 are structures associated with the base 108. The release mechanisms 110 set the spatial structure 102 at the base 108 when the base 108 is in the first position 114. As shown, the release mechanisms 110 can attach elements 123 to the spatial structure 102. The elements 123 are components of the structure space with which the release mechanisms 110 engage to attach to the base 108. For example, the elements 123 may comprise at least one of a stud, protrusion, groove, opening, rod, shaft or other suitable element which may be on the spatial structure 102. As used herein, the term "at least one of", used with a list of elements, means that different combinations of one or more elements of the list may be used and only one of each element. in 3025783 10 the list may be necessary. In other words, "at least one of" means any combination of elements and a number of elements of the list can be used but not necessarily all the elements of the list are needed. The element can be a particular object, a thing or a category.
    [0006] For example, without limitation, "at least one of element A, element B or element C" may include element A, element A and element B, or element B. This example may also include element A, element B and element C or element B and element C. Of course, any combination of these elements may be present. In some illustrative examples, "at least one of" may be, for example, without limitation, two of the element A; one of the element B; and ten of the element C; four of element B and seven of element C; or any other appropriate combination. The elements 123 are locations at which the force 122 may be applied to the spatial structure 102 through the release mechanisms 110 associated with the base 108. With selected locations to which the force 122 is applied to the spatial structure 102, the transverse load 118 and other unwanted loads applied to the spatial structure 102 may be reduced. In the illustrative example, a constant amount of force 122 may be applied to each of the elements 123 to each of the release mechanisms 110.
    [0007] In this illustrative example, the release mechanisms 110 move substantially at the same time to release the spatial structure 102 from the base 108 during the acceleration of the base 108 without applying a transverse load 118 to the spatial structure 102 when the The base 108 decelerates to the second position 116, causing the spatial structure 102 to deploy. In another illustrative example, the base 108 may not decelerate before reaching, or just before reaching, the second position 116. As shown, the biasing system 112 is one or more devices that move the base 108 from the first position 114 to the second position 116. In the illustrative example, the biasing system 112 may be selected from at least one One of a spring, a hydraulic actuator, a linear actuator, a solenoid, or other suitable biasing device. As shown, the release mechanisms 110 are at closed positions 124 when the base 108 is in the first position 114 and they move substantially at the same time to open positions 125 to release the spatial structure 102 from the base 108 without applying a transverse load 118 to the spatial structure 102 when the base 108 moves from the first position 114 to the second position 116 to deploy the spatial structure 102. In the illustrative example 5, the release mechanisms 110 are biased to move substantially at the same time to release the spatial structure 102 of the base 108. The spatial structure deployment system 106 may also include a restraint system 126. As shown, the restraint system 126 prohibits the movement of the mechanisms. release 110 to release the spatial structure 102 when the base 108 is at the first positi 114. In the illustrative example, the spatial structure deployment system 106 may comprise other components, such as a housing 127 and a door 128. As shown, the housing 127 includes the opening 130. In the As an illustrative example, the base 108 and the release mechanisms 110 are located in the interior 132 of the housing 127. The spatial structure 102 is also located in the interior 132 of the housing 127 when the spatial structure 102 is attached to the base 108 The door 128 moves between the closed position 134 and the open position 136. The door 128 covers the opening 130 when it is in the closed position 134.
    [0008] In this illustrative example, the spatial structure deployment system 106 also includes the locking system 138. The locking system 138 prohibits the biasing system 112 from moving the base 108 from the first position 114. For example, the locking system 138 holds base 108 at first position 114 when door 128 is in closed position 134.
    [0009] As shown, the locking system 138 allows the biasing system 112 to move the base 108 when the door 128 is in the open position 136. The spatial structure deployment system 106 may also include the vibration reduction system. 140. The vibration reduction system 140 is a structure associated with the gate 128 in this illustrative example. The vibration reduction system 140 is in contact with the spatial structure 102 so that the vibrations 142 in the spatial structure 102 are reduced when the spatial structure 102 is attached to the base 108 by the release mechanisms 110 and the door 128 is in the closed position 134. The vibration reduction system 140 may be, for example, a structure consisting of one or more materials selected from aluminum, elastomeric material, rubber, titanium, plastic or another suitable type of material. In another illustrative example, the vibration reduction system 140 may be implemented using various types of devices. For example, the vibration reduction system 140 may be implemented using one or more shock absorbers.
    [0010] With the spatial structure deployment system 106, the undesirable movement of the spatial structure 102 can be reduced. For example, the fall of the spatial structure 102 when deployed by the spatial structure deployment system 106 may be reduced compared to currently deployed deployment systems. In an illustrative example, the guide 117 and / or the release mechanisms 110 reduce the fall or other undesirable movement of the spatial structure 102 when deployed from the spatial structure deployment system 106. FIG. an illustration of a block diagram of a release mechanism according to an illustrative embodiment. In this illustrative example, the release mechanism 200 is an example of an implementation for a release mechanism among the release mechanisms 110 of FIG. 1. In this illustrative example, the release mechanism 200 comprises a number of different components. As shown, the release mechanism 200 includes the contact point 202, the lever 204, and the biasing device 206. The point of contact 202 is a structure associated with the base. In this illustrative example, the contact point 202 supports one of the elements 123 of the spatial structure 102 in Figure 1. As shown, the lever 204 is movable and secures the element to the contact point 202 when the Lever 204 is at the closed position 208. In this illustrative example, the lever 204 is rotated. When the lever 204 rotates to the open position 210, the element can be moved away from the point of contact 202.
    [0011] In the illustrative example, the biasing device 206 moves the lever 204 from the closed position 208 to the open position 210. This movement of the lever 204 occurs when the base 108 moves from the first position 114 to the second position 116 so that the elements 123 shown in block form in FIG. 1 can be out of engagement with the contact point 202. In the illustrative example, the biasing device 206 may be a linear spring, a torsion spring, a rotary spring, an elastomeric strip or other suitable device or system. The illustration of the spatial structure deployment environment 100 and 10 of the various components of the spatial structure deployment environment 100 in FIG. 1 is not meant to imply physical or architectural limitations in the manner in which a mode illustrative embodiment can be implemented. Other components in addition to those illustrated or in place of these may be used. Some components may not be necessary. Blocks 15 are shown to illustrate certain functional components. One or more of these blocks may be combined, divided or combined and divided into different blocks when implemented in an illustrative embodiment. For example, the spatial structure deployment environment 100 may include one or more additional deployment systems in addition to or instead of the spatial structure deployment system 106. Each of the deployment systems can deploy spatial structures of the same type as that of the platform 104 or of a different type. Figures 3 to 7 are illustrations of a deployment sequence of a satellite according to an illustrative embodiment. Figure 3 is an illustration of a space structure deployment system according to an illustrative embodiment. In this illustrative example, the spatial structure deployment system 300 is an example of an implementation of the spatial structure deployment system 106 shown in block form in FIG. 1. In this example, the structure deployment system Spatial 300 is a satellite deployment system. As shown, the spatial structure deployment system 300 contains the satellite 302. The satellite 302 is an example of a physical implementation of the spatial structure 102 shown in block form in FIG.
    [0012] As shown, the satellite 302 may be a cubesat 1U with a length 303, a width 304, and a height 305. In this illustrative example, the length 303 may be about 10 cm; the width 304 may be about 10 cm and the height 305 may be about 10 cm.
    [0013] In this particular example, the satellite 302 is shown as being located within the housing 306 of the spatial structure deployment system 300. The housing 306 is shown in an exposed view to clearly illustrate the various features of the deployment system. spatial structure 300. As shown, the housing 306 has a length 307, a width 308 and a height 309. In this illustrative example, the length 307 may be about 18 cm; the width 308 may be about 12 cm and the height 309 may be about 12 cm. The door 310 is connected to the housing 306 at the hinge 311. The door 310 is shown in a closed position in this figure.
    [0014] As shown, the spatial structure deployment system 300 includes the base 312. As shown, release mechanisms are associated with the base 312 and attach the satellite 302 to the base 312. In this illustrative example, three release mechanisms are present. In this view, the release mechanism 313 and the release mechanism 314 are shown. The third release mechanism is not visible in this view. As shown, the release mechanism 313 includes the lever 316, the contact point 318 and the spring 320. The release mechanism 314 includes the lever 322, the contact point 324 and the spring 326. In this illustrative example, the spring 320 biases the lever 316 to rotate in the direction of the arrow 328. In addition, the spring 316 biases the lever 322 to rotate in the direction of the arrow 328. In this view, the rotation lever 316 and lever 322 is prohibited by a restraint system. As shown, the restraint system includes the elongated structure 329 and the elongate structure 330.
    [0015] In the illustrative example shown in this figure, the elongated structure 329 and the elongate structure 330 may be posts extending from the surface 332 of the housing 306. The elongated structure 329 contacts the lever 316 and The lever 316 is prevented from moving in the direction of the arrow 328. Similarly, the elongated structure 330 contacts the lever 322 and prevents the lever 322 from moving in the direction of the arrow 328. In this illustrative example, the elongated structure 334 is also shown and is in contact with another lever which is not visible in this view. The elongate structure 334 also prohibits the lever from moving in the direction of the arrow 328. As shown, the satellite 302 includes the element 342 and the element 344. The element 342 and the element 344 are on the satellite 302 which can be attached to the base 312. In this example, another element is present or not shown on the side 348 of the satellite 302. The contact point 318 supports the element 342 and the point contact 324 supports element 344 in this illustrative example. As shown, the point of contact 318 is a structure extending from the surface 349 of the base 312. The point of contact 324 is also a structure extending from the surface 349 of the base 312. contact 318 has a shape that engages with the element 342, and the contact point 324 has a shape that engages the element 344. A more detailed view of the release mechanism 313 and the point of contact 318 in section 350 are shown and described in FIG. 8. The spatial structure deployment system 300 also includes the biasing system 352. The biasing system 352 includes a spring. The biasing system 352 biases the base 312 in the direction of the arrow 354. As shown, the biasing system 352 may be a spring, a linear actuator, a solenoid, or any other type of device capable of applying a force at the base 312. In other words, the biasing system 352 applies a force to move the base 312 in the direction of the arrow 354. In this illustrative example, the spatial structure deployment system 300 also includes In this example, the vibration reduction structure 356 is an example of an implementation of a physical structure that can be used to implement a vibration reduction system 140 shown In the form of blocks in Fig. 1. As shown, the vibration reduction structure 356 is associated with the gate 310. The vibration reduction structure 356 is in contact with the satellite 302 so as to reduce vibrations in the satellite 302 when the satellite 302 is attached to the base 312 by the release mechanisms and the gate 310 is in the closed position as can be seen in this figure . Fig. 4 is an illustration of a space structure deployment system according to an illustrative embodiment. In this figure, the gate 310 is moved in the direction of the arrow 400 and from a closed position to the open position as shown in this figure. The gate 310 exposes the opening 402 in the housing 306. When exposed, the opening 402 allows the satellite 302 to be deployed from the housing 306. In this view, a locking mechanism (not shown) allows the biasing system 352 to move the base 312 in the direction of the arrow 354 when the door 310 is open. When the door 310 is closed, the locking mechanism prohibits the biasing system 352 from moving the base 312. In the illustrative example, the locking mechanism secures the base 312. In other illustrative examples, the locking mechanism can prohibiting the biasing system 352 from applying a force to move the base 312. In this illustrative example, the locking mechanism may be, for example, a fire wire, an actuator or other suitable mechanism that is activated to enable the biasing system 352 to move the base 312 from the first position to a second position when the door 310 is in the open position. Figure 5 is an illustration of a space structure deploying system moving a satellite for deployment according to an illustrative embodiment. In this view, the base 312 is moved from the first position to the second position. This displacement applies a force to the satellite 302 to the element 342, to the element 344 and to another element on the side 348 that is not visible in this view, which are connected to the point of contact 318, at the point contact 324 and another contact point that is not visible in this view. In this illustrative example, base 312 moves in the direction of arrow 354 along guide rail 504. Guide rail 504 constrains movement of base 312 along axis 506. Guide rail 504 helps to reduce the transverse displacement in a direction orthogonal to the arrow 354. As the base 312 moves in the direction of the arrow 354, the base 312 decelerates. In this illustrative example, a deceleration occurs before reaching the second position. In this example shown, a spring is used as a biasing system and the maximum acceleration occurs when the base 312 begins to move from the first position. It is at this first position that the spring force is maximum. When a linear actuator 5 or a solenoid is used as a biasing system, the maximum acceleration can be set to a desired location between the first position and the second position. Figure 5 also shows a change in the position of the lever 316 and the lever 322. The movement of the base 312 in the direction of the arrow 354 moves the lever 316 away from the elongate structure 329 and the lever 322 to As a result, the lever 316 and the lever 322 move in the direction of the arrow 328 to the position shown in this figure. In this illustrative example, this movement of the lever 316 and the lever 322 is a rotational movement. The other lever, which is not visible in this view, also rotates in a similar manner. Figure 6 is an illustration of a space structure deploying system moving a satellite for deployment according to an illustrative embodiment. In this figure, the base 312 has reached the second position. In this view, the lever 316 and the lever 322 have moved to allow the member 342 to move away from the point of contact 318, and the member 344 to move apart. from the point of contact 324 without touching the lever 316 or the lever 322. FIG. 7 is an illustration of a space structure deployment system moving a satellite to deploy it according to an illustrative embodiment. In this figure, the satellite 302 moves away from the base 312 and other components in the spatial structure deployment system 300. In this view, the release mechanism 700 is shown. The release mechanism 700 includes the lever 702 and the contact point 704. The spring which biases the lever 702 is not visible in this view. With the space structure deployment system 300, the fall or other undesirable movement of the satellite 302 is reduced or eliminated. Therefore, when the satellite 302 does not include a propulsion system or other mechanism to reduce the fall, the satellite 302 may be deployed to reduce or eliminate the fall.
    [0016] Figure 8 is an illustration of a release mechanism according to an illustrative embodiment. FIG. 8 shows a more detailed view of sectional release mechanism 313 350 of FIG. 3. In this view, lever 316 is in a closed position so that release mechanism 313 secures member 302 to secure the The contact point 318 has a groove 800 and the lever 316 has a groove 802. When the lever 316 is in a closed position, the element 342 is held in the slot 804 consisting of the groove 800. on the point of contact 318 and the groove 802 on the lever 316. In this configuration, the element 342 is fixed by the release mechanism 313. When the lever 316 rotates to an open position, the element 342 is supported in the groove 800 of the point of contact 318. In this configuration, a force may be applied to the element 342 as the base 312 moves. In addition, the element 342 can move away from the point of contact 318 as the displacement of the base 312 decreases or ceases. Fig. 9 is an illustration of a space structure deployment system according to an illustrative embodiment. In this figure, the spatial structure deployment system 300 is shown in the direction of the lines 9-9 of FIG. 3.
    [0017] In this view, the fire wire 900 is a locking mechanism used to hold the base 312 at the first position. When the satellite 302 is to be deployed, the wire 900 is activated and releases the base 312 so that the biasing system 352 (not shown) moves the satellite 302 in the direction of the arrow 354.
    [0018] Fig. 10 is an illustration of a space structure deployment system according to an illustrative embodiment. In this figure, an exploded view of the spatial structure deployment system 300 is shown without satellite 302. The spatial structure deployment systems shown in FIGS. 3 to 10 are of modular design. In other words, several space structure deployment systems can be arranged to form a system that deploys multiple satellites. Fig. 11 is an illustration of a platform with a plurality of spatial structure deployment systems according to an illustrative embodiment. In this illustrative example, the platform 1100 comprises the spatial structure deployment system 1102, the spatial structure deployment system 1104, the spatial structure deployment system 1106, the spatial structure deployment system 1108, the space structure deployment system 1110, space system deployment system 1112, space structure deployment system 1114, and space structure deployment system 1116. These space structure deployment systems are used to deploy the satellite, respectively. 1118, the satellite 1120, the satellite 1122, the satellite 1124, the satellite 1126, satellite 1128, satellite 1130 and the satellite 1132. These different satellites can be deployed together with the various space structure deployment systems or at different locations. different times. The illustration of the spatial structure deployment system 300 in FIGS. 3 to 11 is an example of a physical implementation of a spatial structure deployment system 106 in FIG. 1 and is not intended to be to limit the manner in which other embodiments can be implemented. For example, it is shown that the door 310 is attached by the hinge 311 to open and close. In other illustrative examples, the gate 310 may be an iris that opens and closes. In another illustrative example, the door 310 may be separated from the housing 306.
    [0019] In another example, although three release mechanisms are shown, other numbers of release mechanisms may also be used depending on the particular implementation. For example, four release mechanisms, two release mechanisms, or other numbers of release mechanisms may be used to apply force to elements of a satellite. In another illustrative example, a space structure deployment system may be deployed using a space ship as a housing. For example, the various components of the spatial structure deployment system can be placed in a bay of a space shuttle without any housing 306 or 30 door 310. In another example, it can be deployed satellites of different sizes from those of cubesat 1U described in the illustrative example above. In addition, satellites may have other shapes that may be irregular.
    [0020] The various components shown in Figures 3 to 11 may be combined with components in Figures 1 and 2, used with components in Figures 1 and 2, or a combination of both. In addition, some of the components in Figs. 3 to 11 may be illustrative examples of how components shown in block form in Figs. 1 and 2 may be implemented as physical structures. Fig. 12 is an illustration of a flowchart of a process of deploying a spatial structure according to an illustrative embodiment. The process illustrated in FIG. 12 can be implemented in the spatial structure deployment environment 100 of FIG. 1. In particular, the various operations can be implemented using the spatial structure deployment system 106 of FIG. Figure 1. The process begins with fixing a spatial structure to a base with release mechanisms when the base is in a first position (operation 1200). The base and the spatial structure are in a housing at operation 1200. The process opens a housing door to expose an opening in the housing to deploy the spatial structure from the housing (operation 1202). The opening allows the spatial structure to move out of the housing through the opening as the base moves from the first position to the second position. Then, the process moves the base from the first position to a second position to deploy the spatial structure (operation 1204). The process then moves the release mechanisms substantially at the same time to release the spatial structure of the base without applying a transverse load to the spatial structure (operation 1206), and then the process is terminated. Operation 1200 takes place as the base moves from the first position to the second position to deploy the spatial structure. Fig. 13 is an illustration of a flowchart of a process for moving release mechanisms according to an illustrative embodiment. The process illustrated in Fig. 13 is an example of operations that can be performed at operation 1206 of Fig. 12. In this example, the spatial structure includes elements that are engaged with the release mechanisms when the base is in the first position.
    [0021] The process begins with the rotation of the levers in the release mechanisms from the closed positions to the open positions as the base moves from the first position to the second position (operation 1300). In operation 1300, the levers no longer fix the elements at the contact points when the levers are in the open position. In the open position, the levers are no longer in contact with the elements or with other portions of the spatial structure when the spatial structure moves away from the base after the base has reached the second position. The process applies an axial force, perpendicular to the base, to the spatial structure to elements on the satellite engaged with contact points in the release mechanisms as the base moves from the first position to the second position. (operation 1302). In operation 1302, the spatial structure accelerates in the direction of the force during the deployment of the spatial structure.
    [0022] The process places the elements of the spatial structure out of the contact points when at least one of the deceleration of the base or the reaching of the second position by the base occurs (operation 1304), and then the process end. At operation 1304, the elements move away from the contact points. In addition, in the open position, the levers are not in contact with the elements or with other portions of the spatial structure when the spatial structure moves away from the base in deceleration and after the base has reaches the second position. The flow diagrams and block diagrams in the various embodiments shown illustrate the architecture, functionality, and operation of some possible implementations of apparatus and methods in an illustrative embodiment. In this respect, each block in the flowcharts or schematic diagrams can represent at least one of a module, a segment, a function or a portion of an operation or a step. In some alternative implementations of an illustrative embodiment, the function or functions noted in the blocks may occur in a different order than that shown in the figures. For example, in some cases, two blocks represented in succession may be executed substantially simultaneously, or the blocks may sometimes be performed in reverse order, depending on the features involved. Likewise, other blocks can be added in addition to the blocks illustrated in a flowchart or in a block diagram. For example, operation 1204 and operation 1206 can be performed substantially at the same time and not in the sequential order shown. Operation 1204 can begin and then operation 1206 can begin after the start of operation 1204. In another illustrative example, an operation may be included to unlock the base or to allow it to move after the door is located. in the open position.
    [0023] One or more illustrative embodiments provide a method and apparatus for deploying a spatial structure by reducing or overcoming a technical problem involving unwanted rotation, such as a fall, of a spatial structure after deployment. An illustrative embodiment employs a spatial structure deployment system having the technical effect of reducing the fall or other unwanted movement of a spatial structure deployed by the spatial structure deployment system. In the illustrative examples, a guide rail and / or release mechanisms reduce transverse loads or other unwanted loads during movement of the base from a first position to a second position to deploy the spatial structure. In this way, at least one of a fall of the spatial structure or of a shock applied to the spatial structure is reduced during the deployment of the spatial structure. Through the use of a space structure deployment system according to an illustrative embodiment, smaller satellites, such as a cubesat, may be deployed to avoid a fall or other undesirable movement of the satellite. Therefore, a satellite does not require a propulsion system or other system to correct a fall using a space structure deployment system according to an illustrative embodiment for deploying the satellite. The various illustrative examples describe components that perform actions or operations. In an illustrative embodiment, a component is configured to perform the action or operation described. For example, the component may have a configuration or design that makes it capable of performing the action or operation that is described in the illustrative examples as executable by the component. The various illustrative embodiments have been described for purposes of illustration and description. Their description is not intended to be exhaustive or limiting of the embodiments in the disclosed form. Many modifications and variations will be apparent to those skilled in the art. For example, the space structure deployment system has been described for a particular size of a cube-shaped satellite. Other illustrative embodiments may be applied to other sizes and forms of satellite or other types of spatial structures. In addition, various illustrative embodiments may provide features different from those of other desirable embodiments. The embodiment or embodiments selected are selected and described to provide the best explanation of the principles of the embodiments and their application in practice, as well as to enable those skilled in the art to understand disclosure for various purposes. embodiments with various modifications corresponding to the particular use envisaged.
    权利要求:
    Claims (15)
    [0001]
    REVENDICATIONS1. An apparatus comprising: a base (108) which is movable; and release mechanisms (110) associated with the base (108), wherein the release mechanisms (110) engage with elements (123) of a spatial structure (102) to secure the spatial structure (102). ) at the base (108) when the base (108) is at a first position (114) and the release mechanisms (110) move substantially at the same time to disengage the elements (123) and release the structure the space (102) of the base (108) during acceleration without applying a transverse load (118) to the spatial structure (102) as the base (108) moves to a second position (116) causing the deployment spatial structure (102).
    [0002]
    The apparatus of claim 1, further comprising: a biasing system (112) which moves the base (108) from the first position (114) to the second position (116).
    [0003]
    The apparatus of claim 1, further comprising: a housing (127) having an opening (130), wherein the base (108) and the release mechanisms (110) are within the housing (127) and wherein the spatial structure (102) is within the housing (127) when the spatial structure (102) is attached to the base (108); and a door (128) that moves between a closed position (134) and an open position (136) and covers the opening (130) when in the closed position (134).
    [0004]
    Apparatus according to claim 3, further comprising: a vibration reduction structure (356) associated with the gate (128), wherein the vibration reduction structure (356) is in contact with the spatial structure (102) to reduce vibrations (142) in the spatial structure (102) when the spatial structure (102) is attached to the base (108) by the release mechanisms (110) and the door (128) is in the position closed (134). 3025783 25
    [0005]
    Apparatus according to claim 4, further comprising: a locking system (138) which holds the base (108) at the first position (114) when the door (128) is in the closed position (134). 5
    [0006]
    An apparatus according to claim 1, wherein the release mechanisms (110) are in closed positions (124) when the base (108) is in the first position (114) and substantially simultaneously move to positions open (125) to release the spatial structure (102) of the base (108) without applying the transverse load (118) to the spatial structure (102) as the base (108) moves from the first position (114) to the second position (116) for deploying the spatial structure (102).
    [0007]
    The apparatus of claim 1, further comprising: a restraint system (126) which prohibits the movement of the release mechanisms (110) to release the spatial structure (102) when the base (108) is at the first position (114).
    [0008]
    An apparatus according to claim 1, wherein a release mechanism (200) in the release mechanisms (110) comprises: a point of contact (202) associated with the base (108), wherein the point of contact ( 202) supports an element (342, 344) on the spatial structure (102); a lever (204) that is movable and secures the member (342, 344) to the point of contact (202) when the lever (204) is in a closed position (134); and a biasing device (206) which moves the lever (204) from the closed position (134) to an open position (136) when the base (108) moves from the first position (114) to the second position ( 116) so that the element (342, 344) is out of engagement with the point of contact (202). 30
    [0009]
    Apparatus according to claim 8, wherein the point of contact (202) comprises: a structure extending from a surface (349) of the base (108) and having a shape that engages with the element (342, 344) on the spatial structure (102). 3025783 26
    [0010]
    The apparatus of claim 1, wherein the release mechanisms (110) comprise: three release mechanisms (110). 5
    [0011]
    A method for deploying a spatial structure (102), the method comprising: attaching the spatial structure (102) to a base (108) with releasing mechanisms (110) that engage with elements (123) the spatial structure (102) when the base (108) is at a first position (114); moving the base (108) from the first position (114) to a second position (116) to deploy the spatial structure (102); and moving the release mechanisms (110) substantially at the same time to disengage the elements (123) and release the spatial structure (102) from the base (108) without applying a transverse load (118) to the spatial structure (102) as the base (108) moves from the first position (114) to the second position (116) to deploy the spatial structure (102).
    [0012]
    The method of claim 11, wherein the base (108) and the spatial structure (102) are located in a housing (127) when the base (108) is in the first position (114) and further comprising: Opening a door (128) for the housing (127) to expose an opening (130) in the housing (127) to deploy the spatial structure (102) from the housing (127), wherein the spatial structure (102) moves out of the housing (127) through the opening (130) as the base (108) moves from the first position (114) to the second position (116). 25
    [0013]
    The method of claim 12, further comprising: contacting the spatial structure (102) with a vibration reduction structure (356) associated with the door (128) in the housing (127) in which there is the spatial structure (102), wherein the vibration reduction structure (356) reduces vibrations (142) in the spatial structure (102) when the door (128) is closed. 3025783 27
    [0014]
    The method of claim 12, wherein the movement of the base (108) comprises: moving the base (108) from the first position (114) to the second position (116) with a biasing system (112) after opening the door (128). 5
    [0015]
    The method of claim 11, wherein the spatial structure (102) includes elements (123) that are engaged with the release mechanisms (110) when the base (108) is in the first position (114). and the movement of the release mechanisms (110) comprises: rotating levers in the closed position release mechanisms (110) (124) at open positions (125) as the base (108) moves from the first position position (114) at the second position (116); applying an axial force, perpendicular to the base (108), to the spatial structure (102), to elements (123) on the spatial structure (102) engaged with contact points in the releasing (110) as the base (108) moves from the first position (114) to the second position (116) so that the spatial structure (102) accelerates in a direction of the axial force during deployment of the structure spatial (102); and placing the elements (123) of the spatial structure (102) out of engagement with the contact points when at least one of the deceleration of the base (108) or the reaching of the second position (116) by the base (108) occurs.
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    同族专利:
    公开号 | 公开日
    CN105416610B|2018-06-05|
    JP6603496B2|2019-11-06|
    US20160075452A1|2016-03-17|
    DE102015114049A1|2016-04-14|
    FR3025783B1|2019-07-05|
    JP2016060483A|2016-04-25|
    CN105416610A|2016-03-23|
    US9567109B2|2017-02-14|
    DE102015114049B4|2021-11-25|
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    法律状态:
    2016-07-26| PLFP| Fee payment|Year of fee payment: 2 |
    2017-07-26| PLFP| Fee payment|Year of fee payment: 3 |
    2018-03-02| PLSC| Publication of the preliminary search report|Effective date: 20180302 |
    2018-07-26| PLFP| Fee payment|Year of fee payment: 4 |
    2019-07-25| PLFP| Fee payment|Year of fee payment: 5 |
    2020-07-27| PLFP| Fee payment|Year of fee payment: 6 |
    2021-07-26| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    US14/488,902|US9567109B2|2014-09-17|2014-09-17|Space structure deployment system|
    US14488902|2014-09-17|
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