Cubesat on-orbit deployment device

Abstract

The application discloses a kind of on-orbit deployment devices of CubeSat, belong to aerospace technology field.The device includes: main frame assembly, hatch, hatch unlocking mechanism, push plate assembly, lateral compression assembly and hatch compression assembly, the main frame assembly shell is square semi-enclosed body, the hatch is rotatably connected on shell by hatch unfolding locking assembly and can form closed body with shell;The hatch unlocking mechanism is installed in the left frame outside;The push plate assembly is arranged in the shell inside and is connected on the bottom plate, for pushing out CubeSat;The lateral compression assembly is arranged in the shell inside right upper corner guide rail support frame, for lateral compression CubeSat;The hatch compression assembly is fixedly installed in the inside of hatch, for CubeSat in the direction perpendicular to bottom plate is compressed.The device has high reliability, low separation angular velocity, ultra-high vacuum environment unlocking and has satellite lateral compression and the like characteristics.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, and in particular to a CubeSat on-orbit deployment device. Background Technology

[0002] CubeSats are picosatellites that adopt internationally accepted standards and represent a major direction in the development of microsatellites. Due to their advantages such as short development cycles, low manufacturing costs, and low R&D expenses, CubeSats have experienced rapid development. Consequently, the necessary deployment devices for on-orbit deployment of CubeSats have also seen significant development, with an increasing number of research institutions and commercial aerospace companies beginning to design and research CubeSat deployment devices. Stanford University and Caltech jointly developed CubeSat standards and designed and manufactured a CubeSat deployer. This deployer has advantages such as low cost and minimal impact, but it still has some shortcomings that need improvement and optimization. For example, it has a relatively high separation angular velocity, can only adapt to short-term deployments in low-Earth orbit high-vacuum environments, and lacks satellite lateral clamping functionality. Therefore, this invention provides an on-orbit deployment device with high reliability, low separation angular velocity, ultra-high vacuum environment unlocking, and a satellite lateral clamping mechanism. Summary of the Invention

[0003] The purpose of this invention is to solve the technical problems existing in the prior art by providing an on-orbit deployment device with vibration reduction function, hatch locking function and CubeSat lateral clamping function.

[0004] To achieve the above objectives, the present invention provides a CubeSat on-orbit deployment device, the specific technical solution of which is as follows:

[0005] A CubeSat on-orbit deployment device, the device comprising:

[0006] The main frame assembly includes a shell, which is a square semi-enclosed body. The shell includes a base plate and an upper frame, a lower frame, a left frame, and a right frame fixed above the base plate. A cube star installation space is provided in the middle of the shell. Guide rail support frames are fixed at the four corners of the shell. Each guide rail support frame is equipped with a guide rail. The guide rail in the upper right corner is a sliding guide rail, and the other triangular ones are fixed guide rails.

[0007] The hatch is rotatably connected to the right frame via a hatch opening and locking assembly and is located at the top opening of the housing. The hatch size matches the top opening of the housing and can form a square closed body with the housing. The hatch opening and locking assembly can lock the hatch to restrict its movement after the hatch is opened to a preset angle.

[0008] A hatch unlocking mechanism is installed on the outside of the left frame and is used to lock and unlock the hatch after it is closed;

[0009] A pusher assembly is arranged inside the housing and connected to the base plate for launching the CubeSat. The pusher assembly includes a pusher plate, a separation spring, four pusher plate triangular blocks, and four separation blocks. One end of the separation spring is fixed to the base plate, and the other end is fixed to the pusher plate. The pusher plate is square, and pusher plate triangular blocks are fixed at each of its four corners. The four separation blocks are respectively fixed to the upper frame and the lower frame on the side near the hatch, and their positions correspond one-to-one with the triangular blocks. They are used to block the triangular blocks when the pusher plate is running close to the hatch to prevent the pusher plate from separating from the CubeSat deployment device.

[0010] A lateral clamping assembly is arranged on the guide rail support frame in the upper right corner inside the housing. It is used to generate a lateral clamping force on the CubeSat inside the housing when the hatch is closed, thereby pressing it against the fixed guide rail.

[0011] A hatch clamping assembly is installed and fixed on the inside of the hatch to clamp the CubeSat in a direction perpendicular to the base plate.

[0012] Furthermore, the main frame assembly also includes a main frame skin, which is respectively installed on the upper frame, lower frame, left frame and right frame to cover the observation window and reduce the structural weight.

[0013] Furthermore, two pairs of pivot lugs are fixed on one side of the hatch for connecting with the hatch opening and locking assembly; a pair of hatch lock pins are installed and fixed on the other side of the hatch, and the hatch lock pins cooperate with the hatch unlocking mechanism.

[0014] Furthermore, the hatch deployment and locking assembly includes a pair of hatch deployment and locking mechanisms. Each hatch deployment and locking mechanism is coaxially connected to and cooperates with a pair of the aforementioned pivot lugs. Each hatch deployment and locking mechanism includes: a pivot seat, a pivot, a torsion spring, and a spring pin. The pivot seat is mounted and fixed on the right frame. The pair of pivot lugs are arranged inside the pivot seat and are movably connected by the pivot. The torsion spring is sleeved on the pivot and located inside the pivot seat. The spring pin is mounted and fixed on the pivot seat. The bottom of the spring pin contacts the surface of the pivot lug. A locking hole is opened on the surface of the pivot lug near the spring pin. After the hatch drives the pivot lug to rotate to a preset angle, the locking hole coincides with the position of the spring pin, and the pin inside the spring pin pops out into the locking hole, restricting the movement of the hatch.

[0015] Furthermore, the hatch unlocking mechanism includes: an unlocking mechanism frame, a de-energized electromagnet, a suction cup, and a hook lock. The unlocking mechanism frame is fixed outside the left frame. The de-energized electromagnet is installed inside the unlocking mechanism frame. The suction cup is installed on one side of the output end of the de-energized electromagnet. The hook lock is connected to the other end of the suction cup via a linkage mechanism. The hook lock works in conjunction with a pair of hatch lock pins. In the locked state, the de-energized electromagnet is not energized and attracts the suction cup by its own magnetic force. The hook lock locks the hatch lock pins. When unlocking, the de-energized electromagnet is energized and demagnetized. The suction cup drives the hook lock to rotate and release the hatch lock pins via the linkage mechanism.

[0016] Furthermore, the lateral clamping assembly includes a sliding shaft, on which multiple sets of lateral clamping mechanisms are sleeved. Each lateral clamping mechanism includes a guide sleeve, a clamping spring, a clamping sleeve, and a linkage rod. The guide sleeve and the clamping spring are respectively sleeved on the sliding shaft, and the clamping sleeve is fixed on the sliding shaft. The guide sleeve and the clamping sleeve are respectively arranged at both ends of the clamping spring. The top of the guide sleeve is fixed to the upper frame, and the clamping sleeve is connected to a sliding guide rail located at a 45-degree angle to its lower left corner via the linkage rod. The sliding shaft can slide within the guide sleeve when under pressure.

[0017] Furthermore, guide rail support frames are provided on the upper and right sides of the sliding guide rail, respectively, arranged perpendicularly to each other, to support and restrict the movement trajectory of the sliding guide rail.

[0018] Furthermore, the hatch clamping assembly includes: a hatch clamping block, a hatch positioning cone, a pair of conical clamping blocks, and a pair of hatch slide rails. The hatch clamping block is fixed at a position corresponding to the sliding shaft. When the hatch is closed, the hatch clamping block is used to clamp the sliding shaft. A conical hole is opened on the front side of the left frame. The hatch positioning cone is fixed at a position corresponding to the conical hole. The two work together to limit the lateral displacement of the hatch when the hatch is closed and locked. The pair of conical clamping blocks and the pair of hatch slide rails contact the end of the cubestar frame and clamp the cubestar in a direction perpendicular to the base plate.

[0019] Furthermore, the upper frame, lower frame, left frame, and right frame are designed to be lightweight while ensuring that the structure meets the adaptability requirements of the deployer to the ground and space environments. The materials used are one of aluminum alloy, magnesium-lithium alloy, and magnesium-aluminum alloy.

[0020] Furthermore, the guide rail surface is coated to lubricate and prevent vacuum cold welding between the guide rail and the CubeSat slide rail; the bottom surface of the push plate is coated with molybdenum disulfide to prevent vacuum cold welding between the push plate and the base plate; the surfaces of each part in the lateral clamping assembly are coated to prevent cold welding; the material of the hatch locking block is a high molecular polymer material, namely polyimide, polyoxymethylene, and polyetheretherketone.

[0021] Beneficial effects of the present invention

[0022] Compared with the prior art, the present invention has the following advantages:

[0023] 1. When the hatch is fully pressed by the unlocking mechanism, the satellite is pressed and restricted in movement by the lateral pressing mechanism and the hatch pressing mechanism. At the same time, the separation spring at the pressing end can effectively suppress the impact of vibration on the CubeSat.

[0024] 2. The lateral clamping mechanism can prevent the CubeSat from being ejected immediately when the hatch is fully unlocked. At the same time, in conjunction with the torque of the hatch torsion spring on the hatch, it can ensure that the hatch will not come into contact with the CubeSat during the separation process, which can significantly reduce the ejection angular velocity of the CubeSat. In addition, if the speed of the hatch is slower than the ejection speed of the CubeSat, the hatch rail on the hatch will contact the end of the CubeSat rail, preventing the CubeSat from hooking or colliding with the deployer.

[0025] 3. The four triangular blocks evenly distributed on the push plate and the four separation blocks on the corresponding frame prevent the push plate from separating from the deployer along with the cubesat. At the same time, the evenly distributed layout at the four corners can reduce the separation angular velocity at the moment of cubesat separation.

[0026] 4. Sufficient measures for preventing cold welding and lubrication have been taken. Molybdenum disulfide coating is applied between metals that move relative to each other. Structures with large stress and small load-bearing areas adopt a replaceable structure. These measures can ensure that the deployer can be unlocked smoothly in an ultra-high vacuum environment.

[0027] 5. The deployer adopts a frame splicing configuration. Each structural component has been improved with lightweight design while ensuring strength and vibration requirements, which effectively reduces the weight of the deployer and reduces manufacturing costs.

[0028] 6. The hatch locking mechanism uses a locking spring pin to lock the hatch. On the one hand, the hatch locking mechanism can prevent the hatch from rebounding after colliding with the pivot seat and colliding with the cube star during the separation process; on the other hand, this locking pin locking method has a simple structure, low cost, and high reliability. Attached Figure Description

[0029] Figure 1 A frontal view of the CubeSat deployment device with the hatch retracted, provided by the present invention.

[0030] Figure 2 A reverse view of the CubeSat deployment device with the hatch retracted, provided by the present invention.

[0031] Figure 3 A front view of the CubeSat deployment device with the hatch open and satellite released, provided by the present invention.

[0032] Figure 4 A schematic diagram of the push plate structure of the CubeSat deployment device provided by the present invention;

[0033] Figure 5 A schematic diagram of the hatch opening and locking mechanism of the CubeSat deployment device provided by the present invention;

[0034] Figure 6 A partial structural diagram of the hatch unfolding and locking mechanism of the CubeSat deployment device provided by the present invention;

[0035] Figure 7 A schematic diagram of the unlocking mechanism component of the CubeSat deployment device provided by the present invention;

[0036] Figure 8 A schematic diagram of the lateral clamping assembly of the CubeSat deployment device provided by the present invention;

[0037] Figure 9 A schematic diagram of the lateral clamping assembly structure of the CubeSat deployment device provided by the present invention;

[0038] Figure 10 A partial structural diagram of the lateral clamping assembly of the CubeSat deployment device provided by the present invention;

[0039] Figure 11 A schematic diagram of the door clamping mechanism of the CubeSat deployment device provided by the present invention.

[0040] In the picture,

[0041] 1. Main frame assembly; 2. Hatch door; 3. Hatch door unfolding and locking assembly; 4. Hatch door unlocking mechanism; 5. Push plate assembly; 6. Lateral clamping assembly; 7. Hatch door clamping assembly;

[0042] 11. Base plate; 12. Upper frame; 13. Lower frame; 14. Left frame; 15. Right frame; 16. Main frame skin; 17. Fixed guide rail; 18. Sliding guide rail; 19. Guide rail support frame;

[0043] 141. Tapered hole;

[0044] 21. Cabin door lock pin; 22. Rotary hinge lug;

[0045] 211. Locking hole;

[0046] 31. Shaft seat; 32. Shaft; 33. Torsion spring; 34. Spring pin;

[0047] 41. Unlocking mechanism frame; 42. Power-off electromagnet; 43. Suction cup; 44. Hook lock;

[0048] 51. Push plate; 52. Separation spring; 53. Push plate triangular stop; 54. Separation stop;

[0049] 61. Sliding shaft; 62. Guide sleeve; 63. Compression spring; 64. Compression sleeve; 65. Linkage rod;

[0050] 71. Door clamping block; 72. Conical clamping block; 73. Door slide rail; 74. Door positioning cone. Detailed Implementation

[0051] To enable those skilled in the art to better understand the technical solution of the present invention, the present invention will be further described in detail below with reference to the accompanying drawings.

[0052] It should be noted that the terms "upper," "front," "side," etc., used herein indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the purpose of describing the invention and simplifying the description. Similar expressions are for illustrative purposes only and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the invention.

[0053] See Figures 1-11 ;

[0054] A CubeSat on-orbit deployment device, the device comprising:

[0055] The main frame assembly 1 includes a housing, which is a square, semi-enclosed body. The housing includes a base plate 11 and upper frame 12, lower frame 13, left frame 14, and right frame 15 fixed above the base plate 11. A cubestar mounting space is provided in the center of the housing. Guide rail support frames 19 are fixed at the four corners of the housing, each with a guide rail. The guide rail at the upper right corner is a sliding guide rail 18, while the others at the other corners are fixed guide rails 17. Furthermore, the main frame assembly 1 also includes a main frame skin 16, which is installed on the upper frame 12, lower frame 13, left frame 14, and right frame 15 to cover the observation window and reduce structural weight. Since the skin can be easily removed, the location where the skin is removed can be used as an observation window to observe the working status of the internal mechanisms of the deployer or to pass test cables through that location during testing.

[0056] The hatch 2 is rotatably connected to the right frame 15 via a hatch opening and locking assembly 3 and is located at the top opening of the housing. The size of the hatch 2 matches the top opening of the housing and can form a square closed body with the housing. The hatch opening and locking assembly 3 can lock the hatch 2 to restrict its movement when the hatch 2 is opened to 120°. Furthermore, two pairs of pivot lugs 22 are fixed on one side of the hatch 2 for connecting with the hatch opening and locking assembly 3. A pair of hatch lock pins 21 are installed and fixed on the other side of the hatch 2, and the hatch lock pins 21 are used in conjunction with the hatch unlocking mechanism 4.

[0057] Furthermore, the hatch deployment and locking assembly 3 includes a pair of hatch deployment and locking mechanisms. Each hatch deployment and locking mechanism is coaxially connected to and cooperates with a pair of pivot lugs 22. Each hatch deployment and locking mechanism includes: a pivot seat 31, a pivot 32, a torsion spring 33, and a spring pin 34. The pivot seat 31 is mounted and fixed on the right frame 15. The pair of pivot lugs 22 are arranged inside the pivot seat 31 and are movably connected by the pivot 32. The torsion spring 33 is sleeved on the pivot 32 and located inside the pivot seat 31. The spring pin 34 is mounted and fixed on the pivot seat 31. The bottom of the spring pin 34 contacts the surface of the pivot lug 22. A locking hole 211 is opened on the surface of the pivot lug 22 near the spring pin 34. When the hatch 2 drives the pivot lug 22 to rotate to 120°, the locking hole 211 coincides with the position of the spring pin 34, and the pin inside the spring pin 34 pops out into the locking hole 211, restricting the movement of the hatch 2. After the hatch 2 is unlocked, it mainly relies on the torque of the torsion spring 33 to rotate around the pivot 32.

[0058] The hatch unlocking mechanism 4 is installed outside the left frame 14 and is used to lock and unlock the hatch 2 after it is closed. Further, the hatch unlocking mechanism 4 includes: an unlocking mechanism frame 41, a de-energized electromagnet 42, a suction cup 43, and a hook lock 44. The unlocking mechanism frame 41 is fixed outside the left frame 14. The de-energized electromagnet 42 is installed inside the unlocking mechanism frame 41. The suction cup 43 is installed on one side of the output end of the de-energized electromagnet 42. The hook lock 44 is connected to the other end of the suction cup 43 via a linkage mechanism. The hook lock 44 works in conjunction with a pair of hatch lock pins 21. In the locked state, the de-energized electromagnet 42 is not energized and attracts the suction cup 43 using its own magnetic force. The hook lock 44 locks the hatch lock pins 21. When unlocking, the de-energized electromagnet 42 is energized and demagnetized. The suction cup 43 drives the hook lock 44 to rotate via the linkage mechanism and release the hatch lock pins 21.

[0059] The pusher assembly 5 is arranged inside the housing and connected to the base plate 11 for launching the cubesat. The pusher assembly 5 includes: a pusher plate 51, a separation spring 52, four pusher plate triangular stops 53, and four separation stops 54. One end of the separation spring 52 is fixed to the base plate 11, and the other end is fixed to the pusher plate 51. The pusher plate 51 is square, and pusher plate triangular stops 53 are fixed at each of its four corners. The four separation stops 54 are respectively fixed to the upper frame 12 and the lower frame 13 near the cabin. On one side of door 2, the position corresponds one-to-one with the triangular stop 53, which is used to block the triangular stop 53 when the push plate 51 moves close to the door 2, preventing the push plate 51 from separating from the CubeSat deployment device; specifically, when the door 2 is released by the unlocking mechanism 4, the CubeSat and the push plate 51 move along the guide rail under the elastic force of the separation spring 52. When the push plate 51 moves to a position that is close to being completely separated from the guide rail, the triangular stops evenly distributed on the push plate 51 are blocked by four separation stops, preventing the push plate from separating from the deployer along with the CubeSat.

[0060] A lateral clamping assembly 6 is arranged on the upper right corner guide rail support frame 19 inside the housing. It is used to generate a lateral clamping force on the cubesat inside the housing when the hatch 2 is closed, thereby pressing it against the fixed guide rail 17. Further, the lateral clamping assembly 6 includes a sliding shaft 61, on which multiple sets of lateral clamping mechanisms are sleeved. Each lateral clamping mechanism includes a guide sleeve 62, a clamping spring 63, a clamping sleeve 64, and a linkage rod 65. The guide sleeve 62 and the clamping spring 63 are respectively sleeved on the sliding shaft 61, and the clamping sleeve 64 is fixed on the sliding shaft 61. The guide sleeve 62 and the clamping sleeve 64 are respectively arranged at both ends of the clamping spring 63. The top of the guide sleeve 62 is fixed to the upper frame 12, and the clamping sleeve 64 is connected to the sliding guide rail 18 located at a 45-degree angle to its lower left corner via the linkage rod 65. The sliding shaft 61 can slide within the guide sleeve 62 when under pressure. Furthermore, the sliding guide rail 18 is provided with guide rail support frames 19 arranged perpendicularly to each other on its upper and right sides to support and restrict the movement trajectory of the sliding guide rail 18. Specifically, the interface of the guide rail support frame 19 has a wedge-shaped groove, and the sliding guide rail 18 is arranged in the wedge-shaped groove. As the hatch 2 closes, the lateral pressing assembly 6 converts the axial movement of the sliding shaft 61 into the lateral pressing movement of the sliding guide rail 18 against the cube star, and the cube star is gradually pressed against the fixed guide rail 17 in the lower left corner; when the hatch 2 is fully closed and locked by the unlocking mechanism 4, the cube star is also firmly pressed against the fixed guide rail 17 by the lateral pressing assembly 6.

[0061] A hatch clamping assembly 7 is installed and fixed inside the hatch 2 to clamp the CubeSat in a direction perpendicular to the base plate 11. Further, the hatch clamping assembly 7 includes: a hatch clamping block 71, a hatch positioning cone 74, a pair of conical clamping blocks 72, and a pair of hatch slide rails 73. The hatch clamping block 71 is fixed at a position corresponding to the sliding shaft 61, and when the hatch 2 is closed, the hatch clamping block 71 clamps the sliding shaft 61. A conical hole 141 is opened on the front side of the left frame 14, and the hatch positioning cone 74 is fixed at a position corresponding to the conical hole 141. The two work together to limit the lateral displacement of the hatch 2 when it is closed and locked. The pair of conical clamping blocks 72 and the pair of hatch slide rails 73 contact the ends of the CubeSat frame and clamp the CubeSat in a direction perpendicular to the base plate 11. The main function of the hatch clamping assembly 7 is to clamp the cubesat and restrict its movement along the guide rail direction, while suppressing the cubesat's vibration along the guide rail direction.

[0062] Furthermore, the upper frame 12, lower frame 13, left frame 14 and right frame 15 are designed to be lightweight while ensuring that the structure meets the adaptability of the deployer to the ground and space environment. The material is one of aluminum alloy, magnesium-lithium alloy and magnesium-aluminum alloy.

[0063] Furthermore, the guide rail surface is coated to lubricate and prevent vacuum cold welding between the guide rail and the CubeSat slide rail; the bottom surface of the push plate 51 is coated with a molybdenum disulfide coating to prevent vacuum cold welding between the push plate and the bottom plate; the surfaces of each part in the lateral clamping assembly 6 are coated to prevent cold welding; the material of the hatch clamping block 71 is selected from high molecular polymer materials, namely polyimide, polyoxymethylene and polyetheretherketone.

[0064] The working principle of this invention is as follows: When the CubeSat is in the state of being pressed by the hatch 2, the hatch unlocking mechanism 4 locks the hatch lock pin 21 on the hatch 2. The de-energized electromagnet 42 remains in the adsorption state before receiving the unlocking signal. A pair of conical pressing blocks 72 and a pair of hatch slide rails 73 contact the end of the CubeSat frame and press the CubeSat along the direction perpendicular to the base plate 11. The separation spring 52 is in the compressed state. The hatch pressing block 71 contacts and presses the end of the sliding shaft 61. The lateral pressing assembly 6 converts the axial movement of the sliding shaft 61 into the lateral pressing movement of the sliding guide rail 18 on the CubeSat. The CubeSat is gradually pressed onto the fixed guide rail 17 in the lower left corner. The pressing spring 63 is in the compressed state.

[0065] When the de-energized electromagnet 42 receives the separation signal, it loses its magnetism. The suction cup 43 drives the hook lock 44 to rotate through the linkage mechanism and releases the hatch lock pin 21. The hatch 2 unfolds under the action of the torsion spring 33. The push plate 51 moves under the push of the separation spring. At the same time, the sliding shaft 61 moves along the pop-out direction of the push plate assembly 5 under the action of the compression spring 63, causing the sliding guide rail 18 to retract, thereby releasing the cubesat and the push plate assembly.

[0066] The CubeSat and push plate 51 move along the guide rail under the elastic force of the separation spring 52. Simultaneously, the hatch 2 rotates around the pivot 32 under the action of the torsion spring 33. When the hatch 2 rotates to 120°, it is locked by the locking spring pin 34. When the push plate 51 moves to the top of the fixed guide rail 17, it is blocked by the separation stop 54, and the push plate 51 is confined within the deployer. At this point, the CubeSat is completely separated from the deployer, and the CubeSat separation process ends.

Claims

1. A device for on-orbit deployment of a CubeStar, the device comprising: The device includes: The main frame assembly (1) includes a shell, which is a square semi-enclosed body. The shell includes a base plate (11) and an upper frame (12), a lower frame (13), a left frame (14) and a right frame (15) fixed above the base plate (11). A cube star installation space is provided in the middle of the shell. Guide rail support frames (19) are fixed at the four corners of the shell. Each guide rail support frame (19) is provided with a guide rail. The guide rail in the upper right corner is a sliding guide rail (18), and the other triangular parts are fixed guide rails (17). The hatch (2) is rotatably connected to the right frame (15) via the hatch opening and locking assembly (3) and is located at the top opening of the shell. The size of the hatch (2) matches the top opening of the shell and can form a square closed body with the shell. The hatch opening and locking assembly (3) can lock the hatch (2) to restrict its movement after the hatch (2) is opened to a preset angle. The hatch unlocking mechanism (4) is installed on the outside of the left frame (14) and is used to lock and unlock the hatch (2) after it is closed. The push plate assembly (5) is arranged inside the housing and connected to the bottom plate (11) for launching the CubeSat. The push plate assembly (5) includes: a push plate (51), a separation spring (52), four push plate triangular blocks (53) and four separation blocks (54). One end of the separation spring (52) is fixed to the bottom plate (11) and the other end is fixed to the push plate (51). The push plate (51) is square and has push plate triangular blocks (53) fixed at each of its four corners. The four separation blocks (54) are respectively fixed to the upper frame (12) and the lower frame (13) on the side near the hatch (2). Their positions correspond one-to-one with the triangular blocks (53) and are used to block the triangular blocks (53) when the push plate (51) runs close to the hatch (2) to prevent the push plate (51) from separating from the CubeSat deployment device. Lateral clamping assembly (6), which is arranged on the upper right corner guide rail support frame (19) inside the housing, is used to form a lateral clamping force on the cube star inside the housing when the hatch (2) is closed, thereby pressing it against the fixed guide rail (17); The hatch clamping assembly (7) is installed and fixed inside the hatch (2) to clamp the CubeSat in a direction perpendicular to the base plate (11).

2. The on-orbit deployment apparatus of a cube star according to claim 1, characterized by, The main frame assembly (1) further includes a main frame skin (16), which is installed on the upper frame (12), lower frame (13), left frame (14) and right frame (15) respectively, for shielding the observation window and reducing the structural weight.

3. The on-orbit deployment apparatus of claim 1, wherein, Two pairs of pivot lugs (22) are fixed on one side of the hatch (2) for connecting with the hatch opening and locking assembly (3); a pair of hatch lock pins (21) are installed and fixed on the other side of the hatch (2), and the hatch lock pins (21) are used in conjunction with the hatch unlocking mechanism (4).

4. The on-orbit deployment apparatus of claim 3, wherein, The hatch deployment and locking assembly (3) includes a pair of hatch deployment and locking mechanisms. Each hatch deployment and locking mechanism is coaxially connected to and cooperates with a pair of pivot lugs (22). Each hatch deployment and locking mechanism includes: a pivot seat (31), a pivot (32), a torsion spring (33), and a spring pin (34). The pivot seat (31) is mounted and fixed on the right frame (15) from the side. The pair of pivot lugs (22) are arranged inside the pivot seat (31) and are movably connected by the pivot (32). The torsion spring (33) is sleeved on the pivot (32). 32) Located inside the pivot seat (31), the spring pin (34) is installed and fixed on the pivot seat (31). The bottom of the spring pin (34) is in contact with the surface of the pivot ear (22). The pivot ear (22) has a locking hole (211) on the side near the spring pin (34). After the hatch (2) drives the pivot ear (22) to rotate to a preset angle, the locking hole (211) coincides with the position of the spring pin (34). The pin inside the spring pin (34) pops out into the locking hole (211) to restrict the movement of the hatch (2).

5. The on-orbit deployment apparatus of claim 3, wherein, The hatch unlocking mechanism (4) includes: an unlocking mechanism frame (41), a de-energized electromagnet (42), a suction cup (43), and a hook lock (44). The unlocking mechanism frame (41) is fixed outside the left frame (14). The de-energized electromagnet (42) is installed inside the unlocking mechanism frame (41). The suction cup (43) is installed on one side of the output end of the de-energized electromagnet (42). The hook lock (44) is connected to the other end of the suction cup (43) through a linkage mechanism. The hook lock (44) is used in conjunction with a pair of hatch lock pins (21). In the locked state, the de-energized electromagnet (42) is not energized and attracts the suction cup (43) by its own magnetic force. The hook lock (44) locks the hatch lock pins (21). When unlocking, the de-energized electromagnet (42) is energized and demagnetized. The suction cup (43) drives the hook lock (44) to rotate and release the hatch lock pins (21) through the linkage mechanism.

6. The on-orbit deployment apparatus of claim 2, wherein, The lateral clamping assembly (6) includes a sliding shaft (61), on which multiple sets of lateral clamping mechanisms are fitted. Each lateral clamping mechanism includes a guide sleeve (62), a clamping spring (63), a clamping sleeve (64), and a linkage rod (65). The guide sleeve (62) and the clamping spring (63) are respectively fitted on the sliding shaft (61), and the clamping sleeve (64) is fixed on the sliding shaft (61). The guide sleeve (62) and the clamping sleeve (64) are respectively arranged at both ends of the clamping spring (63). The top of the guide sleeve (62) is fixed to the upper frame (12), and the clamping sleeve (64) is connected to the sliding guide rail (18) located at 45 degrees to its lower left corner through the linkage rod (65). The sliding shaft (61) can slide inside the guide sleeve (62) when under pressure.

7. A cubic star on-orbit deployment device according to claim 6, wherein, The sliding guide rail (18) is provided with guide rail support frames (19) arranged perpendicularly to each other on the upper and right sides to support and limit the movement trajectory of the sliding guide rail (18).

8. The on-orbit deployment apparatus of claim 6, wherein, The hatch clamping assembly (7) includes: a hatch clamping block (71), a hatch positioning cone (74), a pair of conical clamping blocks (72) and a pair of hatch slide rails (73). The hatch clamping block (71) is fixed at a position corresponding to the sliding shaft (61). When the hatch (2) is closed, the hatch clamping block (71) is used to clamp the sliding shaft (61). The left frame (14) has a conical hole (141) on its front side. The hatch positioning cone (74) is fixed at a position corresponding to the conical hole (141). The two work together to limit the lateral displacement of the hatch (2) when the hatch (2) is closed and locked. The pair of conical clamping blocks (72) and the pair of hatch slide rails (73) contact the end of the cubestar frame and clamp the cubestar in a direction perpendicular to the bottom plate (11).

9. The on-orbit deployment apparatus of claim 1, wherein, The upper frame (12), lower frame (13), left frame (14) and right frame (15) are designed for lightweight construction and are made of one of aluminum alloy, magnesium-lithium alloy and magnesium-aluminum alloy.

10. The on-orbit deployment apparatus of claim 8, wherein, The guide rail surface is coated to lubricate and prevent vacuum cold welding between the guide rail and the CubeSat slide rail. The bottom surface of the push plate (51) is coated with molybdenum disulfide to prevent vacuum cold welding between the push plate and the bottom plate. The surfaces of each part in the lateral clamping assembly (6) are coated to prevent cold welding. The material of the hatch clamping block (71) is one of polyimide, polyoxymethylene and polyetheretherketone.

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