Satellite separation device and stacked satellite group

Abstract

This application relates to a satellite separation device and a stacked satellite assembly. The satellite separation device includes: a housing with a cavity open at both ends; a support base disposed in the cavity of the housing; a piston slidably disposed on the support base; a first elastic element disposed in the cavity of the housing, the first elastic element being capable of pushing the piston to slide; and a locking assembly disposed on the support base, the locking assembly being capable of locking the piston under pressure. The satellite separation device of this application is connected to the satellite body. The piston of the upper satellite separation device can apply pressure to the locking assembly of the adjacent lower satellite separation device, so that the locking assembly can lock the piston under pressure. When releasing the satellite, the locking assembly unlocks the piston, and the piston can push the satellite body to move, facilitating the step-by-step release of stacked satellites.

Description

Technical Field

[0001] This application relates to the field of aerospace equipment, and more particularly to a satellite separation device and a stacked satellite assembly. Background Technology

[0002] Flat-panel satellites are communication satellites that utilize flat-panel antenna technology, offering high flexibility, rapid deployment, and low cost. They are suitable for mobile communications, broadband internet, and military communications, and have broad application prospects.

[0003] When launching flat-panel satellites, multiple flat-panel satellites can be stacked on the rocket. The existing satellite-rocket separation method is mainly rotational separation, which may cause collisions between flat-panel satellites, resulting in poor safety. Summary of the Invention

[0004] To address the aforementioned issues, this application provides a satellite separation device and a stacked satellite group, which facilitates the separation of stacked satellites.

[0005] In a first aspect, this application provides a satellite separation device, comprising:

[0006] A shell having cavities open at both ends;

[0007] A support base is disposed in the cavity of the housing;

[0008] The piston is slidably mounted on the support seat;

[0009] A first elastic element is disposed in the cavity of the housing, and the first elastic element is capable of pushing the piston to slide;

[0010] A locking assembly is disposed on the support base, and the locking assembly can lock the piston when pressed.

[0011] According to some embodiments of this application, the piston includes:

[0012] The piston rod is slidably disposed on the support seat, and the first elastic element abuts against the piston rod;

[0013] A screw is threaded to one end of the piston rod, and the locking assembly can engage the screw.

[0014] According to some embodiments of this application, the piston further includes a locking nut, which is threadedly connected to the screw.

[0015] According to some embodiments of this application, the piston rod includes:

[0016] The piston rod body has one end connected to the screw;

[0017] The top sleeve is threadedly connected to the other end of the piston rod body.

[0018] According to some embodiments of this application, the support base includes:

[0019] The base is connected to the housing, and the piston is slidably disposed on the base;

[0020] A bracket is disposed on the base, and the locking assembly is disposed on the bracket.

[0021] According to some embodiments of this application, the locking assembly includes:

[0022] The first connecting rod is rotatably connected at one end to the support base;

[0023] The second link is rotatably connected at one end to the other end of the first link;

[0024] The third link is rotatably mounted on the support base. One end of the third link is rotatably connected to the other end of the second link, and the other end of the third link can engage with the piston.

[0025] According to some embodiments of this application, the locking assembly further includes:

[0026] A push rod is slidably disposed on the support base, and the push rod is located below the first connecting rod;

[0027] A second elastic element is disposed on the support base, and the second elastic element pushes the push rod to abut against the first connecting rod.

[0028] According to some embodiments of this application, the locking assembly further includes:

[0029] A limiting beam is provided on the support base, and the first connecting rod can abut against the limiting beam to limit the first connecting rod from continuing to rotate.

[0030] According to some embodiments of this application, the housing is provided with weight-reducing holes.

[0031] Secondly, this application provides a stacked satellite array comprising at least two stacked satellites, each of which includes:

[0032] Satellite body;

[0033] The satellite separation device described above is wherein the satellite body is connected to the satellite separation device;

[0034] In the at least two stacked satellites, the piston of the upper stacked satellite can apply pressure to the locking assembly of the adjacent lower stacked satellite.

[0035] The satellite separation device of this application is connected to the satellite body. The piston of the upper satellite separation device can apply pressure to the locking component of the adjacent lower satellite separation device so that the locking component can lock the piston under pressure. When the satellite is released, the locking component unlocks the piston, and the piston can push the satellite body to move, realizing the step-by-step release of stacked satellites. Attached Figure Description

[0036] To more clearly illustrate the technical solutions of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without exceeding the scope of protection claimed by this application.

[0037] Figure 1 This is a schematic diagram of a stacked satellite array according to an embodiment of this application;

[0038] Figure 2 This is a schematic diagram of stacked satellites according to an embodiment of this application;

[0039] Figure 3 This is a schematic diagram of the satellite separation device according to an embodiment of this application;

[0040] Figure 4 This is a cross-sectional view of the satellite separation device according to an embodiment of this application;

[0041] Figure 5 This is a cross-sectional view of the housing according to an embodiment of this application;

[0042] Figure 6 This is a schematic diagram of the support base according to an embodiment of this application;

[0043] Figure 7 This is a schematic diagram of two satellite separation devices stacked according to an embodiment of this application;

[0044] Figure 8 This is a schematic diagram of the separation of the two satellite separation devices in an embodiment of this application;

[0045] Figure 9 This is a schematic diagram of the piston in an embodiment of this application;

[0046] Figure 10 This is a cross-sectional view of the piston in an embodiment of this application;

[0047] Figure 11 This is a partial schematic diagram of the piston rod according to an embodiment of this application;

[0048] Figure 12 This is an exploded view of the support base according to an embodiment of this application;

[0049] Figure 13 This is a schematic diagram of the locking component according to an embodiment of this application;

[0050] Figure 14 This is an exploded view of the linkage assembly according to an embodiment of this application;

[0051] Figure 15 This is a schematic diagram of the push rod according to an embodiment of this application;

[0052] Figure 16 This is a schematic diagram of the limiting beam in an embodiment of this application. Detailed Implementation

[0053] The technical solutions of this application will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some, not all, of the embodiments of this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application.

[0054] like Figure 1 and Figure 2 As shown, an embodiment of this application provides a stacked satellite array, including at least two stacked satellites 300, which are stacked sequentially. Each stacked satellite 300 includes a satellite separation device 100 and a satellite body 200. Optionally, the satellite body 200 is a flat-panel satellite. The satellite body 200 is connected to the satellite separation device 100, for example, the satellite separation device 100 is provided at each of the four corners of the satellite body 200.

[0055] The stacked satellite group is mounted on the rocket's carrier 400. In this embodiment, the satellite separation device 100 facilitates the step-by-step release of multiple stacked satellites 300, safely achieving satellite-rocket separation.

[0056] like Figure 3 and Figure 4 As shown, the satellite separation device 100 includes: a housing 1, a support base 2, a piston 3, a first elastic element 4, and a locking assembly 5.

[0057] like Figure 5 As shown, the housing 1 is generally cylindrical, and a cavity 11 is provided inside the housing 1, with openings at both ends. A bearing ring 12 is provided in the cavity 11, and the axis of the bearing ring 12 is collinear with the axis of the housing 1. Connecting ears 13 are provided at the top and bottom of the outer wall of the housing 1. The connecting ears 13 are used to connect to the satellite body 200, for example, the connecting ears 13 are connected to the satellite body 200 by screws.

[0058] like Figure 6 As shown, the support base 2 is disposed in the cavity 11 of the housing 1, for example, the support base 2 is disposed on the bearing ring 12. The support base 2 is provided with a sliding hole 211 extending along the axis of the support base 2.

[0059] One end of the piston 3 passes through the sliding hole 211 of the support 2, allowing the piston 3 to slide on the support 2. Figure 4 As shown, piston 3 can slide up and down parallel to the axis of housing 1. Optionally, the bottom end of piston 3 is located outside housing 1.

[0060] The first elastic element 4 is disposed in the cavity 11 of the housing 1. The top end of the first elastic element 4 abuts against the support seat 2, and the bottom end of the first elastic element 4 abuts against the piston 3. The first elastic element 4 can push the piston 3 to slide downward. Optionally, the first elastic element 4 is a spring.

[0061] The locking component 5 is located on the top of the support base 2. When the locking component 5 is pressed, it can lock the piston 3 to restrict the piston 3 from sliding downward.

[0062] like Figure 7 As shown, with multiple stacked satellites 300 sequentially stacked on the rocket, the piston 3a of the upper satellite separation device 100a enters the cavity 11 of the lower satellite separation device 100b and presses against the locking component 5b of the lower satellite separation device 100b. The locking component 5b, under pressure, engages with the piston 3b of the lower satellite separation device 100b, while simultaneously, the first elastic element 4b of the lower satellite separation device 100b is compressed and deformed. The topmost satellite separation device 100 in the stacked satellite group applies pressure to the locking component 5b using a pressure-applying device. Optionally, the pressure-applying device is a rotatable cover (not shown in the figure), which is mounted on the rocket. When the satellite and rocket are not separated, the cover applies pressure to the topmost satellite separation device 100; when the satellite and rocket separate, the cover rotates and opens.

[0063] like Figure 8 As shown, during satellite-rocket separation, the pressure on the locking component 5a of the satellite separation device 100a disappears, the locking component 5a unlocks the piston 3a, and the support seat 2a is pushed by the first elastic element 4a. The support seat 2a transmits the pushed force to the satellite body 200 connected to it through the housing 1a. The piston 3a gradually extends from the bottom end of the housing 1a, so that the upper satellite body gradually moves away from the lower satellite body. After the upper piston 3a disengages from the lower locking component 5b, the upper satellite body moves out of the rocket's carrying space, realizing satellite-rocket separation.

[0064] After the upper piston 3a disengages from the lower locking assembly 5b, the pressure on the lower locking assembly 5b disappears, and the locking assembly 5b unlocks the piston 3b, initiating the release of the lower stacked satellites. This process is repeated sequentially to release multiple stacked satellites in stages. Because multiple stacked satellites are released one by one, collisions between different satellites are effectively avoided, improving the safety of satellite release.

[0065] like Figure 9 and Figure 10As shown, in some embodiments, the piston 3 includes a piston rod 31 and a screw 32. The piston rod 31 is slidably disposed in the sliding hole 211 of the support base 2. The outer wall of the piston rod 31 is provided with a first flange 311, and the bottom end of the first elastic member 4 abuts against the first flange 311. The screw 32 is threadedly connected to the top end of the piston rod 31, and the top end of the screw 32 is provided with a second flange 321. The locking assembly 5 can engage the second flange 321 of the screw 32 to restrict the piston 3 from sliding downward.

[0066] The screw 32 is threadedly connected to the piston rod 31, which makes the length of the piston 3 adjustable, and facilitates the adjustment of the compression of the first elastic element 4 when the piston 3 is locked.

[0067] Optionally, a connecting nut 312 is provided at the top of the piston rod 31, and the external thread of the screw 32 is threadedly connected to the connecting nut 312.

[0068] In some embodiments, the piston 3 further includes a locking nut 33, which is threadedly connected to the screw 32. The locking nut 33 is located above the connecting nut 312. Tightening the locking nut 33 can lock the screw 32 and prevent the screw 32 from moving relative to the piston rod 31.

[0069] As above Figure 11 As shown, in some embodiments, the piston rod 31 includes a piston rod body 313 and a clamping sleeve 314. A screw 32 is connected to the top end of the piston rod body 313, and the clamping sleeve 314 is disposed at the bottom end of the piston rod body 313. Optionally, the clamping sleeve 314 is threadedly connected to the piston rod body 313, facilitating better adjustment of the piston 3's length.

[0070] like Figure 12 As shown, the support 2 includes a base 21 and a bracket 22. The base 21 is disposed on the bearing ring 12 of the housing 1, and a sliding hole 211 is disposed on the base 21. The piston 3 is slidably disposed on the base 21. The base 21 is generally T-shaped and includes a base plate 212 and an extension post 213. The extension post 213 is disposed on the bottom surface of the base plate 212, and the sliding hole 211 passes through the base plate 212 and the extension post 213. The extension post 213 helps to increase the length of the sliding hole 211, so as to better guide the piston 3. The bracket 22 is disposed on the base 21 and is located above the base 21. The bracket 22 is generally cylindrical and hollow inside, and the piston 3 passes through the bracket 22.

[0071] The support frame 22 includes a support column 221, a lower flange 222, and an upper flange 223. The support column 221 is disposed between the lower flange 222 and the upper flange 223, and multiple support columns 221 are evenly distributed circumferentially around the axis of the support frame 22. The lower flange 222 is connected to the base 21, for example, by bolts. A locking assembly 5 is disposed at the top of the support frame 22. The gap formed between adjacent support columns 221 helps to reduce the weight of the support frame 22.

[0072] like Figure 13 and Figure 14 As shown, in some embodiments, the locking assembly 5 includes a linkage assembly, which includes a first linkage 51, a second linkage 52, and a third linkage 53.

[0073] One end of the first connecting rod 51 is rotatably connected to the support base 2. For example, one end of the first connecting rod 51 is provided with a first hinge hole 512, and the first rotating shaft is respectively connected to the first hinge hole 512 and the first adapter ear 224 on the top of the upper flange 223 of the bracket 22.

[0074] The other end of the first connecting rod 51 is rotatably connected to one end of the second connecting rod 52. For example, the first connecting rod 51 is approximately rectangular, and both ends of the first connecting rod 51 are provided with rounded corners. The first connecting rod 51 is provided with a receiving cavity 511, which extends through the upper and lower surfaces of the first connecting rod 51. The other end of the first connecting rod 51 is provided with a second hinge hole 513, which connects to the receiving cavity 511. One end of the second connecting rod 52 is provided with a third hinge hole 521, and a second rotating shaft is connected to the second hinge hole 513 and the third hinge hole 521 respectively. The second connecting rod 52 can enter the receiving cavity 511, which helps to reduce the space occupied by the locking assembly 5.

[0075] Optionally, the second link 52 is generally T-shaped, including a first cylindrical portion 523 and a swing arm 524, the swing arm 524 being disposed on the side wall of the cylindrical portion 523. A third hinge hole 521 is disposed in the cylindrical portion 523, extending along the axis of the cylindrical portion 523. A fifth hinge hole 522 is provided at the end of the swing arm 524 away from the cylindrical portion 523.

[0076] The third link 53 is rotatably mounted on the support base 2. For example, a fourth hinge hole 532 is provided in the middle of the third link 53, and a second adapter ear 225 is provided on the top of the inner wall of the bracket 22. The third rotating shaft is connected to the fourth hinge hole 532 and the second adapter ear 225 on the bracket 22. The third link 53 is located below the first link 51 and is located in the cavity of the bracket 22. One end of the third link 53 is rotatably connected to the other end of the second link 52. For example, a sixth hinge hole 531 is provided at one end of the third link 53, and the fourth rotating shaft is connected to the fifth hinge hole 522 and the sixth hinge hole 531. The other end of the third link 53 is a hook 533. The hook 533 can be rotated towards the axis of the piston 3 to engage the piston 3, and can be rotated away from the axis of the piston 3 to unlock the piston 3.

[0077] Optionally, the third link 53 further includes a second cylindrical portion 534 and a connecting lug 535, both of which are disposed on the side wall of the second cylindrical portion 534. A fourth hinge hole 532 is disposed in the second cylindrical portion 534 and extends along the axis of the second cylindrical portion 534. A sixth hinge hole 531 is disposed in the connecting lug 535.

[0078] In the locked state, the hook 533 engages with the screw 32 to restrict the piston 3 from sliding downward. After the pressure on the locking assembly 5 is released, the first elastic element 4 applies a downward sliding force to the piston 3. As the piston 3 moves downward, the third connecting rod 53 rotates. As the third connecting rod 53 rotates, the second connecting rod 52 and the first connecting rod 51 move accordingly. The hook 533 rotates away from the axis of the piston 3, the piston 3 is unlocked, and the end of the first connecting rod 51 where the second hinge hole 513 is located rotates upward.

[0079] Pressurize the first connecting rod 51 so that the end of the first connecting rod 51 with the second hinge hole 513 rotates downward. The first connecting rod 51 drives the second connecting rod 52 and the third connecting rod 53 to move. The hook 533 of the third connecting rod 53 rotates towards the axis of the piston 3 to lock the piston 3. The second connecting rod 52 enters the receiving cavity 511 of the first connecting rod 51.

[0080] Optionally, the number of linkage assemblies is two sets, and the two sets of linkage assemblies are arranged symmetrically.

[0081] like Figure 15 As shown, in some embodiments, the locking assembly 5 further includes a push rod 54 and a second elastic member 55. The push rod 54 is slidably disposed on the bracket 22 of the support base 2, and the push rod 54 is located below the first connecting rod 51. Optionally, a stepped hole 226 is provided on the top surface of the bracket 22, and the push rod 54 is slidably disposed in the stepped hole 226.

[0082] The second elastic element 55 is disposed in the stepped hole 226 of the support base 2. One end of the second elastic element 55 abuts against the push rod 54, and the other end abuts against the shoulder of the stepped hole 226. The second elastic element 55 can push the push rod 54 to abut against the first connecting rod 51 and provide an upward rotational thrust for the first connecting rod 51. When the first connecting rod 51 is subjected to downward pressure, the third connecting rod 53 engages with the piston 3, and the second elastic element 55 is compressed and deformed. When the piston 3 is unlocked, the pressure on the first connecting rod 51 disappears, and the second elastic element 55 pushes the push rod 54 upward, providing an upward rotational thrust for the first connecting rod 51, facilitating the unlocking of the piston 3.

[0083] like Figure 16 As shown, in some embodiments, the locking assembly 5 further includes a limiting beam 56, which is disposed on the top surface of the bracket 22. Optionally, the limiting beam 56 is located between the two sets of linkage assemblies. When the first link 51 rotates downward, it can abut against the limiting beam 56 to limit the first link 51 from continuing to rotate downward, thereby improving the safety of the satellite separation device 100. The first link 51 of both sets of linkage assemblies can abut against the limiting beam 56.

[0084] like Figure 5 As shown, in some embodiments, the housing 1 is provided with weight-reducing holes 14. The number and shape of the weight-reducing holes 14 are set according to requirements to reduce the weight of the housing 1.

[0085] In this embodiment of the stacked satellite group, the piston 3 of the upper stacked satellite can apply pressure to the locking assembly 5 of the adjacent lower stacked satellite, so that the locking assembly 5 locks the corresponding piston 3. After the upper stacked satellite separates from the lower stacked satellite, the pressure on the locking assembly 5 of the lower stacked satellite disappears, the locking assembly 5 unlocks the corresponding piston 3, and the thrust of the first elastic member 4 pushes the lower stacked satellite upward, realizing the release of the stacked satellite.

[0086] The embodiments of this application have been described in detail above. Specific examples have been used to illustrate the principles and implementation methods of this application. The descriptions of the embodiments above are only for the purpose of helping to understand the technical solutions and core ideas of this application. Therefore, any changes or modifications made by those skilled in the art based on the ideas of this application, and on the specific implementation methods and application scope of this application, are all within the scope of protection of this application. In summary, the content of this specification should not be construed as a limitation of this application.

Claims

1. A satellite separation device, characterized in that, include: The shell, having a cavity with openings at both ends, is connected to the satellite body; A support base is disposed in the cavity of the housing; The piston is slidably mounted on the support seat; A first elastic element is disposed in the cavity of the housing. The top end of the first elastic element abuts against the support seat, and the bottom end of the first elastic element abuts against the piston, and can push the piston to slide downward. A locking assembly is disposed on the top of the support base. The locking assembly can lock the piston under pressure to restrict the piston from sliding downward. Multiple satellites are stacked on the rocket in sequence. The piston of the upper satellite separation device enters the cavity of the lower satellite separation device and presses against the locking component of the lower satellite separation device. The locking component is pressed and locks the piston of the lower satellite separation device. At the same time, the first elastic element of the lower satellite separation device is compressed and deformed.

2. The satellite separation device according to claim 1, characterized in that, The piston includes: The piston rod is slidably disposed on the support seat, and the first elastic element abuts against the piston rod; A screw is threaded to one end of the piston rod, and the locking assembly can engage the screw.

3. The satellite separation device according to claim 2, characterized in that, The piston also includes a locking nut, which is threadedly connected to the screw.

4. The satellite separation device according to claim 2, characterized in that, The piston rod includes: The piston rod body has one end connected to the screw; The top sleeve is threadedly connected to the other end of the piston rod body.

5. The satellite separation device according to claim 1, characterized in that, The support base includes: The base is connected to the housing, and the piston is slidably disposed on the base; A bracket is disposed on the base, and the locking assembly is disposed on the bracket.

6. The satellite separation device according to claim 1, characterized in that, The locking assembly includes: The first connecting rod is rotatably connected at one end to the support base; The second link is rotatably connected at one end to the other end of the first link; The third link is rotatably mounted on the support base. One end of the third link is rotatably connected to the other end of the second link, and the other end of the third link can engage with the piston.

7. The satellite separation device according to claim 6, characterized in that, The locking assembly further includes: A push rod is slidably disposed on the support base, and the push rod is located below the first connecting rod; A second elastic element is disposed on the support base, and the second elastic element pushes the push rod to abut against the first connecting rod.

8. The satellite separation device according to claim 6, characterized in that, The locking assembly further includes: A limiting beam is provided on the support base, and the first connecting rod can abut against the limiting beam to limit the first connecting rod from continuing to rotate.

9. The satellite separation device according to claim 1, characterized in that, The housing is provided with weight-reducing holes.

10. A stacked satellite array, characterized in that, It includes at least two stacked satellites, each of which comprises: Satellite body; The satellite separation device as described in any one of claims 1 to 9, wherein the satellite body is connected to the satellite separation device; In the at least two stacked satellites, the piston of the upper stacked satellite can apply pressure to the locking assembly of the adjacent lower stacked satellite.

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