Micro-nano satellite deployment mechanism

Abstract

This invention discloses a micro / nano satellite deployment mechanism, comprising a satellite body, a solar array assembly, a data transmission antenna assembly, an electronic reconnaissance antenna assembly, a first rope limiting member, a first binding rope, and a first cutting mechanism. The solar array assembly includes a solar panel swing mechanism, a solar panel, and a 180-degree deployment mechanism. The first rope limiting member is provided on the solar panel, the data transmission base bracket, and the electronic reconnaissance linkage. The first binding rope is wound around the outside of the satellite body through the first rope limiting member, keeping the solar array assembly, data transmission antenna assembly, and electronic reconnaissance antenna assembly in a folded state. The first cutting mechanism is disposed on the satellite body, and is correspondingly arranged with the first binding rope. This invention enables rapid folding and unfolding of the solar array, data transmission antenna, and electronic reconnaissance antenna. It has a wide overall scope, simple structure, low cost, is easy to mass-produce, convenient to assemble and disassemble, has a stable and reliable structure, can adapt to complex environments such as high and low temperatures, and saves space.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, and more specifically to a micro / nano satellite deployment mechanism. Background Technology

[0002] With the development of microsatellites and aerospace technology, microsatellites have been widely used in various fields such as communication, remote sensing, and scientific research due to their advantages such as low cost, multiple satellites launched on a single rocket, and rapid launch. To facilitate rapid and centralized launches and the formation of a satellite constellation network in space, microsatellites have strict requirements regarding their size and weight.

[0003] Deploying solar panels and antennas directly outside the satellite increases the satellite's envelope, thus increasing launch costs. Therefore, these structures that need to be deployed must be retracted and fixed before the satellite enters orbit, and then unlocked and deployed after the satellite separates from the launch vehicle. Existing satellite deployment mechanisms are complex in structure, expensive to manufacture, and cumbersome to operate. Therefore, providing a simple, low-cost, easily mass-producible, and convenient micro / nano satellite deployment mechanism and method involving solar panels, data transmission antennas, and electronic reconnaissance antennas is one of the urgent technical problems to be solved in this field. Summary of the Invention

[0004] In view of this, the present invention provides a micro-nano satellite deployment mechanism, the purpose of which is to solve the problems in the prior art.

[0005] To solve the above-mentioned technical problems, the present invention adopts the following technical solution:

[0006] A micro / nano satellite deployment mechanism, comprising:

[0007] Satellite body;

[0008] A solar array assembly; the solar array assembly includes a solar panel oscillation mechanism, a solar panel, and a 180-degree deployment mechanism for the solar panel; the solar panel oscillation mechanism is disposed on the satellite body; multiple solar panels are sequentially connected to the solar panel oscillation mechanism; adjacent solar panels are connected to each other through the 180-degree deployment mechanism for the solar panel;

[0009] A data transmission antenna assembly; the data transmission antenna assembly includes a 90-degree data transmission deployment mechanism, a first data transmission link, a second data transmission link, a 180-degree data transmission deployment mechanism, a data transmission base bracket, and a data transmission drive mechanism; the 90-degree data transmission deployment mechanism is disposed on the satellite body; one end of the first data transmission link is connected to the 90-degree data transmission deployment mechanism, and the other end of the first data transmission link is connected to the second data transmission link through the 180-degree data transmission deployment mechanism; the data transmission base bracket is disposed at the other end of the second data transmission link; the data transmission drive mechanism is disposed on the data transmission base bracket;

[0010] An electronic reconnaissance antenna assembly; the electronic reconnaissance antenna assembly includes an electronic reconnaissance antenna support, an electronic reconnaissance 90-degree deployment mechanism, an electronic reconnaissance connecting rod, an electronic reconnaissance antenna base, and an electronic reconnaissance antenna; the electronic reconnaissance antenna support is mounted on the satellite body; one end of the electronic reconnaissance connecting rod is connected to the electronic reconnaissance antenna support via the electronic reconnaissance 90-degree deployment mechanism, and the other end of the electronic reconnaissance connecting rod is connected to the electronic reconnaissance antenna base; the electronic reconnaissance antenna is mounted on the electronic reconnaissance antenna base;

[0011] First rope limiting component; the first rope limiting component is provided on the solar panel, the data transmission base bracket and the electric detection link;

[0012] The first binding rope; the first binding rope is wrapped around the outside of the satellite body through the first rope limiting member and keeps the solar panel assembly, data transmission antenna assembly and electronic reconnaissance antenna assembly in a folded state;

[0013] A first cutting mechanism; the first cutting mechanism is disposed on the satellite body and is disposed corresponding to the first binding rope.

[0014] Preferably, the solar panel assembly further includes a solar panel limiting assembly for supporting and limiting the solar panel.

[0015] Preferably, the solar panel limiting assembly includes a solar panel support base and a solar panel limiting component; the solar panel support base is disposed on the satellite body; the solar panel limiting component is disposed on the innermost solar panel; the solar panel limiting component is provided with a solar panel slot; and the solar panel support base is provided with a solar panel insert block adapted to the solar panel slot.

[0016] Preferably, the outermost solar panel is provided with a second rope limiting member; the innermost solar panel is provided with a second cutting mechanism; a second binding rope is wound between the second rope limiting member and the second cutting mechanism to keep the solar panel assembly in a folded state.

[0017] Preferably, the data transmission antenna assembly further includes a data transmission limiting component for supporting and limiting the data transmission antenna assembly.

[0018] Preferably, the data transmission limiting component includes a data transmission support base and a data transmission limiting member; the data transmission support base is disposed on the satellite body; the data transmission limiting member is disposed on the first data transmission link; the data transmission limiting member is provided with a data transmission slot; and the data transmission support base is provided with a data transmission plug that is adapted to the data transmission slot.

[0019] Preferably, the electronic reconnaissance antenna assembly further includes an electronic reconnaissance limiting component for supporting and limiting the electronic reconnaissance antenna assembly.

[0020] Preferably, the electronic reconnaissance limiting assembly includes an electronic reconnaissance support base and an electronic reconnaissance limiting member; the electronic reconnaissance support base is disposed on the satellite body and / or the solar array assembly; the electronic reconnaissance limiting member is disposed on the electronic reconnaissance link; the electronic reconnaissance limiting member is provided with an electronic reconnaissance slot; and the electronic reconnaissance support base is provided with an electronic reconnaissance plug adapted to the electronic reconnaissance slot.

[0021] Preferably, the number of electronic reconnaissance antenna assemblies is seven; wherein, the electronic reconnaissance antenna assembly located on the same side as the data transmission antenna assembly is limited by a third binding rope, and the solar array assembly, the data transmission antenna assembly and the remaining electronic reconnaissance antenna assemblies are limited by a fourth binding rope; the satellite body is provided with a third cutting mechanism corresponding to the third binding rope and a fourth cutting mechanism corresponding to the fourth binding rope.

[0022] Preferably, the 180-degree deployment mechanism of the sailboard, the 90-degree deployment mechanism of the data transmission, and the 180-degree deployment mechanism of the data transmission are all equipped with locking mechanisms.

[0023] Compared with the prior art, the present invention has achieved the following technical effects: the present invention can realize the rapid folding and unfolding of solar array, data transmission antenna and electronic reconnaissance antenna, with a large overall scope, simple structure, low cost, easy mass production, convenient disassembly and assembly, stable and reliable structure, and can adapt to complex environments such as high and low temperatures, and save space. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of a micro-nano satellite deployment mechanism before deployment, according to the present invention.

[0025] Figure 2 This is a schematic diagram from another perspective before the micro-nano satellite deployment mechanism of the present invention is deployed;

[0026] Figure 3a , Figure 3b , Figure 3c , Figure 3d This is a schematic diagram of the unfolding process of the present invention;

[0027] Figure 4 This is a schematic diagram of the solar array assembly before deployment;

[0028] Figure 5 This is a schematic diagram of the solar panel assembly deployment process;

[0029] Figure 6 This is a schematic diagram of the solar array assembly after deployment;

[0030] Figure 7 This is a schematic diagram of the data transmission antenna assembly before it is deployed.

[0031] Figure 8 This is a schematic diagram of the data transmission antenna assembly deployment process;

[0032] Figure 9 This is a schematic diagram of the data transmission antenna assembly after it has been unfolded.

[0033] Figure 10 A schematic diagram of the electronic reconnaissance antenna assembly before deployment, which corresponds to the solar array assembly;

[0034] Figure 11 A schematic diagram of the deployment process of the electronic reconnaissance antenna assembly corresponding to the solar array assembly;

[0035] Figure 12 A schematic diagram of the deployed electronic reconnaissance antenna assembly, which corresponds to the solar array assembly.

[0036] Figure 13 This is a schematic diagram of one of the electronic reconnaissance antenna components located on the same side as the data transmission antenna component before it is deployed;

[0037] Figure 14 This is a schematic diagram of the deployment process of one of the electronic reconnaissance antenna components located on the same side as the data transmission antenna component;

[0038] Figure 15 This is a schematic diagram of one of the electronic reconnaissance antenna components located on the same side as the data transmission antenna component after being unfolded.

[0039] Figure 16 This is a schematic diagram showing the positions of the first cutting mechanism, the third cutting mechanism, and the fourth cutting mechanism;

[0040] Figure 17 This is a schematic diagram showing the location of the second cutting mechanism;

[0041] Figure 18 A schematic diagram showing the electronic reconnaissance 90-degree deployment mechanism before and after deployment;

[0042] Figure 19 A schematic diagram showing the data transmission 90-degree unfolding mechanism before and after unfolding;

[0043] Figure 20 This is a schematic diagram showing the windsurfing board's 180-degree deployment mechanism before and after deployment.

[0044] Figure 21 This is a schematic diagram of a standard electrical detection support base and electrical detection limiting component;

[0045] In the diagram: 1. Satellite body; 2. Solar array assembly; 201. Solar panel swing mechanism; 202. Solar panel; 203. Solar panel 180-degree deployment mechanism; 204. Solar panel support; 205. Second rope limiting component; 206. Second cutting mechanism; 3. Data transmission antenna assembly; 301. Data transmission 90-degree deployment mechanism; 302. First data transmission link; 303. Second data transmission link; 304. Data transmission 180-degree deployment mechanism; 305. Data transmission base bracket; 306. Data transmission drive mechanism; 307. Data transmission support; 308. Data transmission limiting component; 309. Heat insulation pad; 4. Electronic reconnaissance antenna assembly; 401. Electronic reconnaissance antenna support; 402. 90-degree deployment mechanism for electronic reconnaissance; 4021. First fixed joint; 4022. Second fixed joint; 4023. First movable joint; 4024. Second movable joint; 403. Electronic reconnaissance linkage; 404. Electronic reconnaissance antenna base; 405. Electronic reconnaissance support base; 406. Electronic reconnaissance limiting component; 407. Electronic reconnaissance antenna; 5. First rope limiting component; 6. First binding rope; 7. First cutting mechanism; 8. Second binding rope; 9. Third binding rope; 10. Fourth binding rope; 11. Third cutting mechanism; 12. Fourth cutting mechanism; 13. Fourth rope limiting component; 14. Stop block; 15. Locking shaft; 16. Locking groove; 17. Cable clamp. Detailed Implementation

[0046] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0047] Reference Figure 1-21 As shown, the present invention provides a micro / nano satellite deployment mechanism, comprising:

[0048] Satellite body 1;

[0049] Solar wing assembly 2; Solar wing assembly 2 includes a solar panel swing mechanism 201, a solar panel 202, and a solar panel 180-degree deployment mechanism 203; The solar panel swing mechanism 201 is located on the left side panel of the satellite body 1 and is used to control the rotation of the solar panel 202 connected to the solar panel swing mechanism 201; Three solar panels 202 are connected to the solar panel swing mechanism 201 from the inside to the outside to provide energy for the satellite; The innermost solar panel 202 is connected to the solar panel swing mechanism 201 through a solar panel connecting rod; Adjacent solar panels 202 are connected by two solar panel 180-degree deployment mechanisms 203, so that the solar panels 202 can not only be folded together, but also rotate and deploy 180 degrees;

[0050] Data transmission antenna assembly 3; the data transmission antenna assembly 3 includes a data transmission 90-degree deployment mechanism 301, a first data transmission link 302, a second data transmission link 303, a data transmission 180-degree deployment mechanism 304, a data transmission base bracket 305, and a data transmission drive mechanism 306; the data transmission 90-degree deployment mechanism 301 is disposed on the right side of the satellite body 1 and is used to control the data transmission link to rotate 90 degrees; one end of the first data transmission link 302 is connected to the data transmission 90-degree deployment mechanism 301 through a first data transmission link fixing member, and the other end of the first data transmission link 302 is connected to the data transmission 90-degree deployment mechanism 301 through a data transmission 180-degree deployment mechanism 304. The 80-degree unfolding mechanism 304 is connected to the second data transmission link 303. By setting the 180-degree unfolding mechanism 304, the second data transmission link 303 can rotate and unfold 90 degrees relative to the first data transmission link 302. The data transmission base bracket 305 is set at the other end of the second data transmission link 303. The data transmission drive mechanism 306 is set on the data transmission base bracket 305, which can further unfold the data transmission antenna after the data transmission antenna assembly 3 is unfolded. The distance between the data transmission antenna and the satellite can be extended by setting the first data transmission link 302 and the second data transmission link 303.

[0051] The electronic reconnaissance antenna assembly 4 includes an electronic reconnaissance antenna support 401, an electronic reconnaissance 90-degree deployment mechanism 402, an electronic reconnaissance connecting rod 403, an electronic reconnaissance antenna base 404, and an electronic reconnaissance antenna 407. The electronic reconnaissance antenna support 401 is mounted on the top panel of the satellite body 1, fixing the entire electronic reconnaissance antenna assembly 4 to the satellite body 1. One end of the electronic reconnaissance connecting rod 403 is connected to the electronic reconnaissance antenna support 401 via the electronic reconnaissance 90-degree deployment mechanism 402, and the other end of the electronic reconnaissance connecting rod 403 is connected to the electronic reconnaissance antenna base 404. The electronic reconnaissance antenna 407 is mounted on the electronic reconnaissance antenna base 404. The electronic reconnaissance antenna assembly 4 can be deployed 90 degrees outward from the satellite via the electronic reconnaissance 90-degree deployment mechanism 402.

[0052] First rope limiting component 5; the outermost solar panel 202, data transmission base bracket 305 and electric detection linkage 403 are all provided with first rope limiting component 5; each first rope limiting component 5 is provided with a first rope limiting groove;

[0053] First binding rope 6; The first binding rope 6 is wrapped around the outside of the satellite body 1 through the first rope limiting groove on the first rope limiting member 5 to fix and limit the solar array assembly 2, data transmission antenna assembly 3 and electronic reconnaissance antenna assembly 4, so that the solar array assembly 2, data transmission antenna assembly 3 and electronic reconnaissance antenna assembly 4 are kept in a folded state.

[0054] The first cutting mechanism 7 is disposed on the cabin plate of the satellite body 1 and is correspondingly disposed with the first binding rope 6, and is used to cut the first binding rope 6; the first cutting mechanism 7 and the first binding rope 6 cooperate to realize the folding and unfolding of the solar array assembly 2, the data transmission antenna assembly 3 and the electronic reconnaissance antenna assembly 4 in the unfolding mechanism.

[0055] In this embodiment, the solar array assembly 2 also includes a solar panel limiting assembly for supporting and limiting the solar panel 202. This assembly not only supports the solar array assembly 2, keeping it at a certain distance from the satellite body 1 to avoid collisions, but also limits the degrees of freedom of the solar array assembly 2 in all directions except the outward deployment direction, thereby resisting loads in the three directions of mechanical vibration.

[0056] In this embodiment, the solar panel limiting assembly includes a solar panel support base 204 and a solar panel limiting component; the solar panel support base 204 is disposed on the satellite body 1; the solar panel limiting component is disposed on the innermost solar panel 202; the solar panel limiting component is provided with a solar panel slot; the solar panel support base 204 is provided with a solar panel plug that is compatible with the solar panel slot; when the solar wing assembly 2 is in a folded state, the solar panel plug is inserted into the solar panel slot to achieve the purpose of supporting and limiting the solar wing assembly 2; when the solar wing assembly 2 needs to be deployed, the solar panel plug can be disengaged from the solar panel slot without affecting the deployment operation.

[0057] In this embodiment, adjacent solar panels 202 are also provided with mutually cooperating solar panel support seats 204 and solar panel limiting members, which are used to support and limit the solar panels 202.

[0058] In this embodiment, the outermost solar panel 202 is provided with a second rope limiting member 205; the second rope limiting member 205 is designed as a hook structure to hook the second binding rope 8 and serve as a limiting device; the innermost solar panel 202 is provided with a second cutting mechanism 206; the second binding rope 8 is wound between the second rope limiting member 205 and the second cutting mechanism 206 to keep the three solar panels 202 in the solar wing assembly 2 in a folded state. The second rope limiting member 205 limits the second binding rope 8, and the second rope limiting member 205 cooperates with the second cutting mechanism 206 to realize the folding and unfolding of the solar panel 202.

[0059] In this embodiment, the data transmission antenna assembly 3 also includes a data transmission limiting assembly for supporting and limiting the data transmission antenna assembly 3. This not only supports the data transmission antenna assembly 3, keeping it at a certain distance from the satellite body 1 to avoid collision, but also limits the degrees of freedom of the data transmission antenna assembly 3 in all directions except the outward expansion direction. That is, it will not translate or rotate on a plane that is commensurate with the distance from the upper panel of the satellite body 1, in order to resist loads in the three directions of mechanical vibration.

[0060] In this embodiment, the data transmission limiting component includes a data transmission support base 307 and a data transmission limiting member 308. The data transmission support base 307 is disposed on the satellite body 1. The data transmission limiting member 308 is disposed on the first data transmission link 302. The data transmission limiting member 308 is provided with a data transmission slot. The data transmission support base 307 is provided with a data transmission plug that is compatible with the data transmission slot. When the data transmission antenna assembly 3 is in a folded state, the data transmission plug is inserted into the data transmission slot to achieve the purpose of supporting and limiting the data transmission antenna assembly 3. When the data transmission antenna assembly 3 needs to be unfolded, the data transmission plug can be disengaged from the data transmission slot without affecting the unfolding operation.

[0061] In this embodiment, one end of the data transmission 180-degree unfolding mechanism 304 is connected to the first data transmission link 302 through the first data transmission link fixing member, and the other end of the data transmission 180-degree unfolding mechanism 304 is connected to the second data transmission link 303 through the second data transmission link fixing member.

[0062] In this embodiment, a heat insulation pad 309 is provided between the first rope limiting member 5 on the data transmission antenna assembly 3 and the data transmission base bracket 305 to insulate against heat.

[0063] In this embodiment, the electronic reconnaissance antenna assembly 4 also includes an electronic reconnaissance limiting assembly for supporting and limiting the electronic reconnaissance antenna assembly 4. This assembly not only supports the electronic reconnaissance antenna assembly 4, keeping it at a certain distance from the satellite body 1 to avoid collision, but also limits the degrees of freedom of the electronic reconnaissance antenna assembly 4 in all directions except the outward expansion direction. That is, it will not translate or rotate on a plane that is commensurate with the distance from the upper panel of the satellite body 1, in order to resist the loads in the three directions of mechanical vibration.

[0064] In this embodiment, the electronic detection linkage 403 is connected to the electronic detection 90-degree deployment mechanism 402 via the electronic detection linkage connector.

[0065] In this embodiment, the electronic reconnaissance limiting assembly includes an electronic reconnaissance support base 405 and an electronic reconnaissance limiting member 406. The electronic reconnaissance support base 405 is disposed on the satellite body 1 and / or the solar array assembly 2. The electronic reconnaissance limiting member 406 is disposed on the electronic reconnaissance connecting rod 403. The electronic reconnaissance limiting member 406 is provided with an electronic reconnaissance slot. The electronic reconnaissance support base 405 is provided with an electronic reconnaissance plug that is compatible with the electronic reconnaissance slot. When the electronic reconnaissance antenna assembly 4 is in a folded state, the electronic reconnaissance plug is inserted into the electronic reconnaissance slot to achieve the purpose of supporting and limiting the electronic reconnaissance antenna assembly 4. When the electronic reconnaissance antenna assembly 4 needs to be unfolded, the electronic reconnaissance plug can be disengaged from the electronic reconnaissance slot without affecting the unfolding operation.

[0066] In this embodiment, there are seven electronic reconnaissance antenna assemblies 4. One of the seven electronic reconnaissance antenna assemblies 4 is folded and installed on the left side of the satellite body 1, corresponding to the middle position of the solar array assembly 2. The remaining six electronic reconnaissance antenna assemblies 4 are divided into three groups of two, and the three groups of electronic reconnaissance antenna assemblies 4 are folded and installed on the front, rear and right sides of the satellite body 1, respectively. Among them, the two electronic reconnaissance antenna assemblies 4 located on the same side as the data transmission antenna assembly 3 are limited by the third binding rope 9, and the solar array assembly 2, the data transmission antenna assembly 3 and the remaining electronic reconnaissance antenna assemblies 4 are limited by the fourth binding rope 10. The satellite body 1 is provided with a third cutting mechanism 11 corresponding to the third binding rope 9 and a fourth cutting mechanism 12 corresponding to the fourth binding rope 10.

[0067] In this embodiment, the electronic reconnaissance support 405 corresponding to the electronic reconnaissance antenna assembly 4 arranged in relation to the solar array assembly 2 is arranged on the outermost solar panel 202; the electronic reconnaissance support 405 of the remaining electronic reconnaissance antenna assemblies 4 are all arranged on the satellite body 1.

[0068] In this embodiment, the outermost solar panel 202 and the data transmission drive mechanism 306 are both provided with a fourth rope limiting member 13; the fourth rope limiting member 13 and the electronic reconnaissance antenna assembly 406 which is not located on the same side as the data transmission antenna assembly 3 are both provided with a fourth rope limiting groove for restraining the fourth binding rope 10; the fourth binding rope 10 wraps around the satellite body 1 to gather the solar panel assembly 2, the data transmission antenna assembly 3 and the five electronic reconnaissance antenna assemblies which are not located on the same side as the data transmission antenna assembly 3, and limits the fourth binding rope 10 through the fourth rope limiting groove on the fourth rope limiting member 13.

[0069] In this embodiment, a variety of fourth rope limiting members 13 are configured. Depending on the installation position of the fourth rope limiting member 13, a suitable fourth rope limiting member 13 can be selected. At the same time, the fourth rope limiting grooves on the fourth rope limiting members 13 of different specifications are adapted to the corresponding fourth rope limiting members 13.

[0070] In this embodiment, there are two fourth rope limiting members 13 on the data transmission drive mechanism 306.

[0071] In this embodiment, various specifications of electrical detection limiting components 406 are configured. Depending on the installation position of the electrical detection limiting component 406, the appropriate specification of electrical detection limiting component 406 can be selected.

[0072] In this embodiment, various specifications of electrical detection support bases 405 are provided. Depending on the installation position of the electrical detection support base 405, the appropriate specification of electrical detection support base 405 can be selected.

[0073] In this embodiment, there are two third binding ropes 9 and two third cutting mechanisms 11; the two third binding ropes 9 and the two third cutting mechanisms 11 are arranged in a one-to-one correspondence; the two third binding ropes 9 and the two cutting mechanisms cooperate to limit the two electronic reconnaissance antenna assemblies 4 located on the same side as the data transmission antenna assembly 3, so as to realize the functions of folding and unfolding.

[0074] In this embodiment, the electronic detection limiting members 406 on the two electronic detection antenna assemblies 4 located on the same side as the data transmission antenna assembly 3 are each provided with a third rope limiting groove for restraining the third binding rope 9.

[0075] In this embodiment, each of the electrical detection limiting members 406 corresponding to the third rope limiting groove is provided with a wire clamping seat 17; each wire clamping seat 17 is located above the corresponding third rope limiting groove, which further limits the third binding rope 9.

[0076] In this embodiment, a variety of first rope limiting members 5 are configured. Depending on the installation position of the first rope limiting member 5, a suitable first rope limiting member 5 can be selected. At the same time, the first rope limiting grooves on the first rope limiting members 5 of different specifications are adapted to the corresponding first rope limiting members 5.

[0077] In this embodiment, the 90-degree deployment mechanism 402 for electronic reconnaissance includes a first fixed joint 4021, a second fixed joint 4022, a first movable joint 4023, and a second movable joint 4024. The first fixed joint 4021 is fixedly connected to the electronic reconnaissance antenna support 401. The second fixed joint 4022 is rotatably connected to the first fixed joint 4021. One end of the first movable joint 4023 is rotatably connected to the first fixed joint 4021. The other end of the first movable joint 4023 is rotatably connected to one end of the second movable joint 4024. The other end of the second movable joint 4024 is rotatably connected to the second fixed joint 4022.

[0078] In this embodiment, the 180-degree deployment mechanism 203, the 90-degree data transmission deployment mechanism 301, and the 180-degree data transmission deployment mechanism 304 all include an active seat and a passive seat; the passive seat and the active seat are rotatably connected.

[0079] In this embodiment, driven seats and driving seats of different specifications are configured. Depending on the installation position of the driven seats and driving seats, the appropriate specifications of driven seats and driving seats can be selected and installed in the corresponding positions.

[0080] In this embodiment, locking mechanisms are provided on the 180-degree deployment mechanism 203, the 90-degree data transmission deployment mechanism 301, and the 180-degree data transmission deployment mechanism 304.

[0081] In this embodiment, the locking mechanism includes a stop block 14 and a locking shaft 15; the stop block 14 is rotatably connected to the driven seat; a torsion spring is provided between the stop block 14 and the driven seat; the locking shaft 15 is located on the stop block 14 away from the driven seat; the driving seat is provided with a locking groove 16 that is adapted to the locking shaft 15.

[0082] In this embodiment, different specifications of electronic reconnaissance antenna supports 401 are configured. The appropriate specifications of electronic reconnaissance antenna supports 401 can be selected according to the different installation positions of the electronic reconnaissance antenna assembly 4, so as to meet the usage requirements.

[0083] In this embodiment, the 90-degree deployment mechanism 402 for electronic detection is driven by a torsion spring; the 90-degree deployment mechanism 301 for data transmission, the 180-degree deployment mechanism 304 for data transmission, and the 180-degree deployment mechanism 203 for the sailboard are driven by spiral springs.

[0084] In this embodiment, the first cutting mechanism 7, the second cutting mechanism 206, the third cutting mechanism 11 and the fourth cutting mechanism 12 are all electrothermal knives; the electrothermal knives have a double-headed structure, which facilitates the limiting of the corresponding binding ropes.

[0085] In this embodiment, in order to ensure satellite functionality and facilitate installation and manufacturing, the numbers of the electronic reconnaissance support 405, electronic reconnaissance antenna support 401, electronic reconnaissance connecting rod 403, electronic reconnaissance limiting member 406 and electronic reconnaissance antenna base 404 in each electronic reconnaissance antenna assembly 4 correspond one-to-one with the installation position.

[0086] Methods for the folding and unfolding of micro / nano satellite deployment mechanisms:

[0087] Folding Method: 1) Assemble the solar panel assembly 2, electronic reconnaissance antenna assembly 4, and data transmission antenna assembly 3, and complete the installation of the electronic reconnaissance support 405, data transmission support 307, solar panel support 204, and all cut structures; 2) Install the solar panel assembly 2, electronic reconnaissance antenna assembly 4, and data transmission antenna assembly 3 at the designed positions on the satellite body 1; 3) Fold up the solar panel 202 and fix the solar panel assembly 2 with the second binding rope 8, so that the solar panel assembly 2 is in a folded state; 4) Fold up the electronic reconnaissance antenna assembly 4 located on the same side as the data transmission antenna assembly 3 and fix it with the third binding rope 9, so that the electronic reconnaissance antenna assembly 4 located on the same side as the data transmission antenna assembly 3 is in a folded state; 5) Fold up the remaining electronic reconnaissance antenna assembly and data transmission antenna assembly 3 and fix them with the first binding rope 6 and the fourth binding rope 10, so that all the solar panel assembly 2, electronic reconnaissance antenna assembly 4, and data transmission antenna assembly 3 are in a folded state.

[0088] Deployment Method: 1) The first cutting mechanism 7 and the fourth cutting mechanism 12 start working, cutting the first binding rope 6 and the second binding rope 8. The data transmission antenna assembly 3 and the electronic reconnaissance antenna assembly 4, which is not located on the same side as the data transmission antenna assembly 3, begin to deploy. Among them, the second fixed joint 4022 in the electronic reconnaissance 90-degree deployment mechanism 402 of the electronic reconnaissance antenna assembly 4, which is not located on the same side as the data transmission antenna assembly 3, rotates outward and drives the first movable joint 4023 and the second movable joint 4024 to move. When it rotates outward to 90 degrees, the first movable joint 4023 and the second movable joint 4024 can no longer rotate relative to each other, thereby fixing the deployment angle. At the same time, the driven seat in the data transmission 90-degree deployment mechanism 301 rotates outward relative to the active seat. At 90 degrees, the locking shaft 15 just rotates into the locking groove 16 on the active seat and locks, preventing the driven seat from rotating further. Then the driven seat of the data transmission 90-degree deployment mechanism 301 rotates 90 degrees relative to the active seat outwards and locks. The driven seat of the data transmission 180-degree deployment mechanism 304 also begins to rotate relative to the active seat. When the driven seat rotates 180 degrees relative to the active seat, the locking shaft 15 just rotates into the locking groove 16 on the active seat and locks, preventing the driven seat from rotating further. Then the driven seat of the data transmission 180-degree deployment mechanism 304 rotates 180 degrees relative to the active seat and locks. Finally, the data transmission antenna assembly 3 extends outwards, and the electronic reconnaissance antenna assembly 4, located on the same side as the data transmission assembly, extends outwards while keeping its center in the same plane.

[0089] 2) The third cutting mechanism 11 starts working and cuts the third binding rope 9. The electronic reconnaissance antenna assembly 4, which is located on the same side as the data transmission antenna assembly 3, begins to unfold. Its specific unfolding process is the same as the unfolding process of the electronic reconnaissance antenna assembly 4, which is not located on the same side as the data transmission antenna assembly 3 in step 1). The electronic reconnaissance antenna assembly 4, which is located on the same side as the data transmission antenna assembly 3, rotates outward by 90 degrees until it is parallel to the mounting plate and locks. At this point, all the electronic reconnaissance antenna assemblies 4 have been fully unfolded.

[0090] 3) The solar panel swing mechanism 201 controls the solar panel connecting rod to rotate 90 degrees. Then the second cutting mechanism 206 starts to work and cuts the second binding rope 8 that fixes the solar panel 202. Under the action of the solar panel swing mechanism 201 and the solar panel 180-degree deployment mechanism 203, the solar wing assembly 2 is deployed. During this process, the solar panel swing mechanism 201 rotates 90 degrees, and the outer solar panel 202 of the two adjacent solar panels 202 rotates 180 degrees relative to the inner solar panel 202. Finally, the data transmission drive mechanism 306 controls the data transmission antenna to perform the final deployment after the data transmission antenna assembly 3 is deployed. At this point, the step-by-step deployment of the satellite deployment mechanism is completed.

[0091] The above description is merely a preferred embodiment of the present invention and does not constitute any limitation on the technical scope of the present invention. Therefore, any minor modifications, equivalent changes, and alterations made to the above embodiments based on the technical essence of the present invention shall still fall within the scope of the technical solution of the present invention.

Claims

1. A micro / nano satellite deployment mechanism, characterized in that, include: Satellite body (1); Solar wing assembly (2); the solar wing assembly (2) includes a solar panel swing mechanism (201), a solar panel (202) and a solar panel 180-degree deployment mechanism (203); the solar panel swing mechanism (201) is disposed on the satellite body (1); a plurality of solar panels (202) are sequentially connected to the solar panel swing mechanism (201); adjacent solar panels (202) are connected to each other through the solar panel 180-degree deployment mechanism (203); Data transmission antenna assembly (3); the data transmission antenna assembly (3) includes a data transmission 90-degree deployment mechanism (301), a first data transmission link (302), a second data transmission link (303), a data transmission 180-degree deployment mechanism (304), a data transmission base bracket (305), and a data transmission drive mechanism (306); the data transmission 90-degree deployment mechanism (301) is disposed on the satellite body (1); one end of the first data transmission link (302) is connected to the data transmission 90-degree deployment mechanism (301), and the other end of the first data transmission link (302) is connected to the second data transmission link (303) through the data transmission 180-degree deployment mechanism (304); the data transmission base bracket (305) is disposed on the other end of the second data transmission link (303); the data transmission drive mechanism (306) is disposed on the data transmission base bracket (305); An electronic reconnaissance antenna assembly (4) includes an electronic reconnaissance antenna support (401), an electronic reconnaissance 90-degree deployment mechanism (402), an electronic reconnaissance connecting rod (403), an electronic reconnaissance antenna base (404), and an electronic reconnaissance antenna (407). The electronic reconnaissance antenna support (401) is mounted on the satellite body (1). One end of the electronic reconnaissance connecting rod (403) is connected to the electronic reconnaissance antenna support (401) through the electronic reconnaissance 90-degree deployment mechanism (402), and the other end of the electronic reconnaissance connecting rod (403) is connected to the electronic reconnaissance antenna base (404). The electronic reconnaissance antenna (407) is mounted on the electronic reconnaissance antenna base (404). The first rope limiting component (5) is provided on the solar panel (202), the data transmission base bracket (305) and the electric detection link (403). First binding rope (6); the first binding rope (6) is wrapped around the outside of the satellite body (1) through the first rope limiting member (5) and keeps the solar array assembly (2), data transmission antenna assembly (3) and electronic reconnaissance antenna assembly (4) in a folded state; First cutting mechanism (7); The first cutting mechanism (7) is disposed on the satellite body (1), and the first cutting mechanism (7) is disposed corresponding to the first binding rope (6).

2. The micro / nano satellite deployment mechanism according to claim 1, characterized in that, The solar array assembly (2) also includes a solar panel limiting assembly for supporting and limiting the solar panel (202).

3. A micro / nano satellite deployment mechanism according to claim 2, characterized in that, The solar panel limiting assembly includes a solar panel support base (204) and a solar panel limiting component; the solar panel support base (204) is disposed on the satellite body (1); the solar panel limiting component is disposed on the innermost solar panel (202); the solar panel limiting component is provided with a solar panel slot; the solar panel support base (204) is provided with a solar panel insert that is compatible with the solar panel slot.

4. A micro / nano satellite deployment mechanism according to claim 3, characterized in that, The outermost solar panel (202) is provided with a second rope limiting member (205); the innermost solar panel (202) is provided with a second cutting mechanism (206); a second binding rope (8) is wound between the second rope limiting member (205) and the second cutting mechanism (206) to keep the solar wing assembly (2) in a folded state.

5. A micro / nano satellite deployment mechanism according to claim 1, characterized in that, The data transmission antenna assembly (3) also includes a data transmission limiting component for supporting and limiting the data transmission antenna assembly (3).

6. A micro / nano satellite deployment mechanism according to claim 5, characterized in that, The data transmission limiting component includes a data transmission support base (307) and a data transmission limiting component (308); the data transmission support base (307) is disposed on the satellite body (1); the data transmission limiting component (308) is disposed on the first data transmission link (302); the data transmission limiting component (308) is provided with a data transmission slot; the data transmission support base (307) is provided with a data transmission plug that is adapted to the data transmission slot.

7. A micro / nano satellite deployment mechanism according to claim 1, characterized in that, The electronic reconnaissance antenna assembly (4) also includes an electronic reconnaissance limiting assembly for supporting and limiting the electronic reconnaissance antenna assembly (4).

8. A micro / nano satellite deployment mechanism according to claim 7, characterized in that, The electronic detection limiting assembly includes an electronic detection support base (405) and an electronic detection limiting component (406); the electronic detection support base (405) is disposed on the satellite body (1) and / or the solar array assembly (2); the electronic detection limiting component (406) is disposed on the electronic detection link (403); the electronic detection limiting component (406) is provided with an electronic detection slot; the electronic detection support base (405) is provided with an electronic detection plug adapted to the electronic detection slot.

9. A micro / nano satellite deployment mechanism according to claim 1, characterized in that, The number of the electronic reconnaissance antenna assemblies (4) is seven; among them, the electronic reconnaissance antenna assembly (4) located on the same side as the data transmission antenna assembly (3) is limited by the third binding rope (9), and the solar panel assembly (2), the data transmission antenna assembly (3) and the remaining electronic reconnaissance antenna assemblies (4) are limited by the fourth binding rope (10); the satellite body (1) is provided with a third cutting mechanism (11) corresponding to the third binding rope (9) and a fourth cutting mechanism (12) corresponding to the fourth binding rope (10).

10. A micro / nano satellite deployment mechanism according to claim 1, characterized in that, The 180-degree deployment mechanism (203), the 90-degree data transmission deployment mechanism (301), and the 180-degree data transmission deployment mechanism (304) are all equipped with locking mechanisms.

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