A foldable multi-dimensional deployment mechanism for space loads

Abstract

The present invention provides a foldable multi-dimensional unfolding mechanism for space payloads, which mainly solves the problems that the existing reflector antenna needs to occupy a large envelope space, carries less payload, and has difficulty in satellite layout. The mechanism includes a folding and unfolding module, a main connecting rod, a secondary connecting rod, a secondary reflector mounting module and a main reflector mounting module, a main locking module and a secondary locking module; the folding and unfolding module is arranged at the edge of the satellite cabin plate, and is used to realize the 180° flipping of the secondary connecting rod; the secondary reflector mounting module includes a secondary reflector bracket and a secondary reflector motor, which are used to realize the rotation movement of the main connecting rod; the main reflector mounting module includes a main reflector bracket and a main reflector motor, which are used to realize the self-rotation of the main reflector antenna; the main locking module includes a main ejector, a main locking column and a main locking device pressure plate, which are used to realize the position locking of the main connecting rod; the secondary locking module includes a secondary ejector, a secondary locking column and a secondary locking device pressure plate, which are used to realize the position locking of the secondary connecting rod.

Description

Technical Field

[0001] The invention relates to a space load unfolding device, and in particular to a foldable multi-dimensional unfolding mechanism for space loads. Background Art

[0002] In recent years, with the development of satellite communication technology, in order to solve the Internet access problems in remote areas, aviation, navigation and other fields, satellite Internet technology that combines satellite communication and the Internet has gradually become one of the main trends in the development of satellite communication technology. As the requirements of satellite Internet systems for capacity, performance, and on-orbit life continue to increase, how to more efficiently meet the different application requirements of different regions and time domains during the operation of satellites in orbit, how to improve the efficiency of transponder utilization and increase revenue returns have become the focus of satellite Internet systems.

[0003] Satellite antennas are located at the forefront of satellite communication systems. Their performance directly affects the quality of satellite communication and plays an important role in satellite communication systems. Satellite antennas commonly used in communication satellites can be divided into three categories: lens antennas, reflector antennas and phased array antennas. Among them, reflector antennas are the most widely used in communication satellites. The technology is relatively mature and has the advantages of low cost, simple structure, wide frequency range and high gain. Existing reflector antennas are feed bias antennas, which are mainly composed of a feed source and a reflector. Most of the reflectors are parabolic. During installation, the feed source and the secondary reflector are offset from the front of the main reflector to avoid blocking the central field of view of the main reflector, so that the efficiency of the bias antenna is significantly improved. The efficiency of the dual reflector bias antenna can be as high as 80%, which has great application prospects in satellite communication systems.

[0004] With the continuous development of satellite communication technology, the requirements for satellite payloads are becoming higher and higher. Early satellite antennas were generally only required to be fixedly pointed to a certain area on the ground; in recent years, in order to improve the maneuverability and flexibility of satellite communication systems, satellite antennas are usually required to have one-dimensional or multi-dimensional rotation and positioning functions, and antenna pointing mechanisms were born. In satellite systems, antenna pointing mechanisms are mainly used to drive satellite antennas to rotate in one or more dimensions to achieve functions such as aiming, positioning and tracking of ground targets, and they play an irreplaceable role in satellite communication systems.

[0005] At present, wide coverage and lightweight satellite-borne antenna pointing mechanisms have gradually become the key to promoting the development of satellite communication technology. In order to reduce the spatial envelope of the satellite body in the rocket fairing, the feed bias antenna mechanism is installed on the satellite outer cabin board in a locked state. After unfolding, the mechanism performs two-dimensional pointing movement above the cabin board. Since the area size of the main reflector is relatively large, its movement mode is the rotation of the main reflector surface, and it moves around the secondary reflector axis under the action of the driving connecting rod. Therefore, it occupies a large envelope space above the cabin board, affecting the layout of the remaining space payloads of the satellite on the satellite body. In the case of limited space, some payloads cannot be carried, and the carried payload is small, which makes the layout of the satellite body difficult and affects the functional requirements of the satellite to perform its mission. Summary of the invention

[0006] The purpose of the present invention is to solve the problems that the existing reflector antenna needs to occupy a large envelope space, carries less payload, and has difficult satellite layout, and to provide a foldable multi-dimensional unfolding mechanism for space payloads.

[0007] To achieve the above object, the present invention adopts the following technical solutions:

[0008] A foldable multi-dimensional unfolding mechanism for space payloads, comprising a folding and unfolding module, a main connecting rod, a secondary connecting rod, a secondary reflection mounting module and a main reflection mounting module, a main locking module and a secondary locking module; the folding and unfolding module is arranged at the edge of a satellite cabin board, and is used to realize a 180° flip of the secondary connecting rod; the folding and unfolding module comprises a main support frame, a coil spring, a reducer, a support shaft, a locker and an annular guide rail; the main support frame is arranged on the satellite cabin board, the coil spring is arranged on the main support frame, and its output end is connected to the support shaft through the reducer, the support shaft is connected to one end of the secondary connecting rod, the coil spring drives the support shaft to rotate, and the secondary connecting rod rotates with the support shaft In order to unfold the axis above the star cabin board and realize 180° flipping, the other end of the secondary connecting rod is flipped to the outside of the star body; the annular guide rail is arranged on the main support frame, and a slot is arranged on it, and the lock is arranged on the secondary connecting rod, and the lock is used to cooperate with the slot of the annular guide rail to realize the locking of the position of the secondary connecting rod after 180° flipping; the secondary reflection installation module includes a secondary reflection bracket and a secondary reflection motor; the secondary reflection bracket is connected to the other end of the secondary connecting rod, and the secondary reflection motor is arranged on the secondary reflection bracket, and the output shaft of the secondary reflection motor is connected to one end of the main connecting rod, so that the main connecting rod rotates with the connection point as the center of the circle, The sub-reflector antenna is arranged on the output shaft of the sub-reflector motor or the main connecting rod to realize synchronous rotation with the main connecting rod. The length of the main connecting rod is less than that of the sub-connecting rod, so that the main connecting rod drives the main reflector antenna to rotate outside the satellite to realize ground scanning. The main reflection installation module includes a main reflection bracket and a main reflection motor. The main reflection bracket is arranged at the other end of the main connecting rod. The main reflection motor is installed on the main reflection bracket, and its output shaft is connected to the main reflector antenna, so as to drive the main reflector antenna to realize self-rotation around its axis. The main locking module includes a main ejector, a main locking column and a main locking device pressure plate. It is fixedly arranged on the satellite cabin plate, and the main locking device pressure plate is arranged on the main reflection bracket; the main ejector is a memory alloy unlocker, which connects the main locking column and the main locking device pressure plate during the satellite launch phase, and separates and disengages the main locking column and the main locking device pressure plate after the satellite enters orbit; the secondary locking module includes a secondary ejector, a secondary locking column and a secondary locking device pressure plate; the secondary locking column is fixedly arranged on the satellite cabin plate, and the secondary locking device pressure plate is arranged on the secondary reflection bracket; the secondary ejector is a memory alloy unlocker, which connects the secondary locking column and the secondary locking device pressure plate during the satellite launch phase, and separates and disengages the secondary locking column and the secondary locking device pressure plate after the satellite enters orbit.

[0009] Furthermore, the sub-reflector motor is a hollow motor, the main reflector antenna transmits the collected signal wave to the sub-reflector antenna, the sub-reflector antenna transmits the signal wave to the feed source through the through hole of the hollow motor, and the feed source transmits the signal to the star body through the transmission waveguide.

[0010] Furthermore, the main release device includes a main separation head and a main connecting bolt, wherein the main separation head is arranged on the main locking column, and the main connecting bolt is used to connect the main separation head and the main locking device pressure plate. After power is turned on, the main separation head and the main connecting bolt are disengaged, so that the main locking column and the main locking device pressure plate are disengaged.

[0011] Furthermore, the auxiliary release device includes an auxiliary separation head and an auxiliary connecting bolt, wherein the auxiliary separation head is arranged on the auxiliary locking column, and the auxiliary connecting bolt is used to connect the auxiliary separation head and the auxiliary locking device pressure plate. After power is turned on, the auxiliary separation head and the auxiliary connecting bolt are disengaged, so that the auxiliary locking column and the auxiliary locking device pressure plate are disengaged.

[0012] Furthermore, the lock includes an outer cylinder, a pressure cover, a compression spring and a locking pressure rod. The outer cylinder is arranged on the secondary connecting rod, the pressure cover is arranged on the outer cylinder, and the compression spring is arranged in the outer cylinder. One end of the compression spring is limited by the pressure cover, and the other end is connected to the locking pressure rod, so that the locking pressure rod moves along its axis and cooperates with the slot to achieve locking.

[0013] Furthermore, an annular boss is provided at one end of the locking rod connected to the compression spring, and the annular boss is arranged in the outer tube to prevent the connecting end of the locking rod and the compression spring from escaping from the outer tube.

[0014] Compared with the prior art, the present invention has the following beneficial effects:

[0015] 1. The present invention provides a foldable multi-dimensional unfolding mechanism for space payloads. During the launch phase, the foldable multi-dimensional unfolding mechanism is in a locked state, and the main reflector antenna and the sub-reflector antenna are installed on the inner side of the satellite cabin. After entering orbit and unlocking, the main reflector antenna and the sub-reflector antenna rotate 180° to the outside of the satellite. When scanning the ground, the main reflector antenna and the sub-reflector antenna are both implemented on the outside of the satellite, which will not affect the payload carried on the satellite. In addition, because the sub-reflector antenna has a very small area and does not rotate, the space motion envelope it occupies when folded 180° is very small, which has little impact on the single-machine layout of the satellite cabin, and is conducive to the satellite carrying more single machines.

[0016] 2. The length of the main connecting rod of the present invention is smaller than that of the auxiliary connecting rod, so that the main connecting rod drives the main reflector antenna to rotate outside the star body, so that the main reflector antenna performs two-dimensional motion scanning of the ground outside the star body, with basically no obstruction, and further increases the scanning field of view of the main reflector antenna to the ground.

[0017] 3. The present invention adopts passive driving devices such as coil springs and reducers, which are safe and reliable, have high mechanical resistance, have no power consumption requirements, and do not occupy stellar energy. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1This is a schematic diagram of the locking state of the foldable multi-dimensional unfolding mechanism of the present invention;

[0019] Figure 2 It is a schematic diagram of the unfolding state of the foldable multi-dimensional unfolding mechanism of the present invention;

[0020] Figure 3 This is a schematic diagram of the structure of the foldable multi-dimensional unfolding mechanism of the present invention;

[0021] Figure 4 It is a schematic diagram of the structure of the folding and unfolding module of the present invention before being turned over;

[0022] Figure 5 This is a schematic diagram of the structure of the folding and unfolding module of the present invention after being turned 180° and locked;

[0023] Figure 6 It is a structural schematic diagram of the locking device of the present invention;

[0024] Figure 7 It is a structural schematic diagram of the main locking module and the main reflective installation module of the present invention;

[0025] Figure 8 It is a schematic structural diagram of the auxiliary locking module and the auxiliary reflection installation module of the present invention.

[0026] Figure numerals: 1-main reflector antenna, 2-sub-reflector antenna, 3-folding module, 4-main connecting rod, 5-sub-connecting rod, 6-sub-reflector mounting module, 7-main reflector mounting module, 8-main locking module, 9-sub-locking module, 10-star body, 31-main support frame, 32-coil spring, 33-reducer, 34-support shaft, 35-locker, 36-annular guide rail, 37-slot, 351-outer cylinder, 352-pressure cover, 353-compression spring, 354-locking pressure rod, 355-annular boss, 61-secondary reflection bracket, 62-secondary reflection motor, 71-main reflection bracket, 72-main reflection motor, 81-main ejector, 82-main locking column, 83-main locking device pressure plate, 811-main separation head, 812-main connecting bolt, 91-secondary ejector, 92-secondary locking column, 93-secondary locking device pressure plate, 911-secondary separation head, 912-secondary connecting bolt. DETAILED DESCRIPTION

[0027] The present invention is described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be understood by those skilled in the art that these embodiments are only used to explain the technical principles of the present invention and are not intended to limit the protection scope of the present invention.

[0028] In order to reduce the motion envelope of the antenna pointing mechanism above the satellite cabin, reduce the difficulty of satellite layout, and increase the number and types of satellite units, the present invention provides a foldable multi-dimensional unfolding mechanism for space payloads. During the launch phase, the foldable multi-dimensional unfolding mechanism is in a locked state, and the sub-reflector antenna and the main reflector antenna are installed on the inner side of the satellite cabin. After entering orbit and unlocking, under the action of the coil spring, the sub-connecting rod rotates 180°, so that the sub-reflector antenna and the main reflector antenna both move to the outside of the satellite to scan the ground. Since the main reflector antenna performs two-dimensional motion scanning on the outside of the satellite, it has little impact on the layout of the satellite cabin. At the same time, since the sub-reflector antenna has a small area and does not rotate, the space motion envelope occupied by it when it is folded 180° is very small, which has little impact on the layout of the satellite cabin, and is conducive to the satellite carrying more units.

[0029] like Figures 1 to 6 As shown, the present invention provides a foldable multi-dimensional unfolding mechanism for locking and unfolding a space payload, wherein the space payload includes a main reflector antenna 1 and a sub-reflector antenna 2; the foldable multi-dimensional unfolding mechanism includes a folding module 3, a main connecting rod 4, a sub-connecting rod 5, a sub-reflector mounting module 6 and a main reflector mounting module 7, a main locking module 8 and a sub-locking module 9. The folding module 3 is arranged at the edge of the cabin board of the satellite 10, and is used to realize a 180° flip of the sub-connecting rod 5; specifically, the folding module 3 includes a main support frame 31, a coil spring 32, a reducer 33, a support shaft 34, a locker 35 and an annular guide rail 36; the main support frame 31 is arranged on the cabin board of the satellite 10, and the coil spring 32 is arranged on the main support frame 31, and its output end is connected to the support shaft 34 through the reducer 33, and the support shaft 34 is connected to one end of the sub-connecting rod 5 The coil spring 32 drives the support shaft 34 to rotate, and the secondary connecting rod 5 is unfolded above the cabin board of the star body 10 with the support shaft 34 as the axis to achieve 180° flipping, and the other end of the secondary connecting rod 5 is flipped to the outside of the star body 10; the annular guide rail 36 is arranged on the main support frame 31, and a slot 37 is arranged on it. The locker 35 is arranged on the secondary connecting rod 5, and the locker 35 is used to cooperate with the slot 37 of the annular guide rail 36 to realize the locking of the position of the secondary connecting rod 5 after 180° flipping.

[0030] like Figure 8 As shown, the sub-reflection mounting module 6 includes a sub-reflection bracket 61 and a sub-reflection motor 62; the sub-reflection bracket 61 is connected to the other end of the sub-connecting rod 5, the sub-reflection motor 62 is arranged on the sub-reflection bracket 61, and the output shaft of the sub-reflection motor 62 is connected to one end of the main connecting rod 4, so that the main connecting rod 4 rotates with the connection point as the center of the circle, and the sub-reflector antenna 2 is arranged on the output shaft of the sub-reflection motor 62 or the main connecting rod 4 to achieve synchronous rotation with the main connecting rod 4. The length of the main connecting rod 4 is less than the length of the sub-connecting rod 5, so that the main connecting rod 4 drives the main reflector antenna 1 to rotate outside the star body 10 to achieve ground scanning.

[0031] The sub-reflector motor 62 of the mechanism of the present invention is a hollow motor. When the satellite-borne antenna transmits signals, the main reflector antenna 1 transmits the collected signal waves to the sub-reflector antenna 2. The sub-reflector antenna 2 transmits the signal waves to the feed source through the through hole in the hollow motor. The feed source transmits the signal to the satellite body 10 through the transmission waveguide.

[0032] like Figure 7 As shown, the main reflection mounting module 7 of the present invention includes a main reflection bracket 71 and a main reflection motor 72; the main reflection bracket 71 is arranged at the other end of the main connecting rod 4; the main reflection motor 72 is installed on the main reflection bracket 71, and its output shaft is connected to the main reflection surface antenna 1, which is used to drive the main reflection surface antenna 1 to realize self-rotation around its axis.

[0033] like Figure 7 As shown, the main locking module 8 of the present invention includes a main ejector 81, a main locking column 82 and a main locking plate 83; the main locking column 82 is fixedly arranged on the cabin plate of the satellite 10, and the main locking plate 83 is arranged on the main reflection bracket 71; the main ejector 81 is a memory alloy unlocker, which connects the main locking column 82 and the main locking plate 83 during the satellite launch phase, and separates the main locking column 82 and the main locking plate 83 after the satellite enters orbit.

[0034] like Figure 8 As shown, the secondary locking module 9 of the present invention is similar in structure to the main locking module 8, and the secondary locking module 9 includes a secondary ejector 91, a secondary locking column 92 and a secondary locking device pressure plate 93; the secondary locking column 92 is fixedly arranged on the cabin plate of the satellite body 10, and the secondary locking device pressure plate 93 is arranged on the secondary reflection bracket 61; the secondary ejector 91 is a memory alloy unlocker, which connects the secondary locking column 92 and the secondary locking device pressure plate 93 during the satellite launch phase, and separates and disengages the secondary locking column 92 and the secondary locking device pressure plate 93 after the satellite enters orbit.

[0035] In an embodiment of the present invention, the main ejector 81 includes a main separation head 811 and a main connecting bolt 812. The main separation head 811 is arranged on the main locking column 82. The main connecting bolt 812 is used to connect the main separation head 811 and the main locking device pressure plate 83. After power is turned on, the main separation head 811 and the main connecting bolt 812 are disengaged, so that the main locking column 82 and the main locking device pressure plate 83 are disengaged. The main separation head 811 includes a nickel-titanium memory alloy wire, a spring, a steel ball, a connecting sleeve, etc. When power is turned on, the memory alloy wire contracts, driving the sliding bolt to move upward, and the limiting steel ball bounces into the sliding bolt groove, the bolt elimination constraint is released, and it moves downward. The limiting steel column of the main separation head 811 bounces into the groove above the bolt elimination, and the connecting sleeve connected to the main connecting bolt 812 pops up upward to release the lock. Correspondingly, the structure of the auxiliary ejector 91 is consistent with that of the main ejector 81, and also includes an auxiliary separation head 911 and an auxiliary connecting bolt 912. The auxiliary separation head 911 is arranged on the auxiliary locking column 92, and the auxiliary connecting bolt 912 is used to connect the auxiliary separation head 911 and the auxiliary locking device pressure plate 93. After power is turned on, the auxiliary separation head 911 and the auxiliary connecting bolt 912 are disengaged, so that the auxiliary locking column 92 and the auxiliary locking device pressure plate 93 are disengaged. The auxiliary separation head 911 may specifically include a memory alloy wire, a spring, a steel ball, a connecting sleeve, etc. The auxiliary ejector 91 is used to connect the auxiliary locking device pressure plate 93 and the auxiliary locking column 92. After power is turned on, the connecting sleeve pops up to separate and disengage the auxiliary locking device pressure plate 93 and the auxiliary locking column 92.

[0036] like Figure 6 As shown, in the embodiment of the present invention, the lock 35 includes an outer cylinder 351, a pressure cover 352, a compression spring 353 and a locking pressure rod 354. The outer cylinder 351 is arranged on the secondary connecting rod 5, the pressure cover 352 is arranged on the outer cylinder 351, and the compression spring 353 is arranged in the outer cylinder 351. One end of the compression spring 353 is limited by the pressure cover 352, and the other end is connected to the locking pressure rod 354, so that the locking pressure rod 354 moves along its axis and cooperates with the card slot 37 to achieve locking. An annular boss 355 is arranged at one end of the locking pressure rod 354 connected to the compression spring 353, and the annular boss 355 is arranged in the outer cylinder 351 to prevent the connection end of the locking pressure rod 354 and the compression spring 353 from escaping from the outer cylinder 351.

[0037] like Figure 1 and Figure 2As shown, the foldable multi-dimensional unfolding mechanism of the present invention is fixed on the satellite platform, mainly carrying the main reflector antenna 1 and the sub-reflector antenna 2, and performing the receiving and transmitting function of the wireless signal of a certain communication load of the satellite. In the launch stage, in order to meet the environmental requirements of its power flight stage and ensure that the fundamental frequency of the driving mechanism is not coupled with the whole satellite, the main reflector antenna 1 and the sub-reflector antenna 2 need to be locked by the main ejector 81 and the auxiliary ejector 91 respectively. After the satellite enters the orbit, the main ejector 81 and the auxiliary ejector 91 are unlocked, and the auxiliary connecting rod 5 is unfolded to the top of the satellite top plate with the support shaft 34 as the axis under the action of the passive driving device such as the coil spring 32 and the reducer 33, and the locking pressure rod 354 of the lock 35 moves along the annular guide rail 36. When it moves to the position of the slot 37, the locking pressure rod 354 is clamped in the slot 37 under the action of the compression spring 353, and the position locking of the auxiliary connecting rod 5 is completed. During the low-speed deployment of the secondary connecting rod 5, the main reflector antenna 1 and the secondary reflector antenna 2 move 180° through the secondary reflector motor 62 to reach the commanded position, and start the ground scanning working mode.

Claims

1. A foldable multi-dimensional unfolding mechanism for a space payload, the space payload comprising a main reflector antenna (1) and a sub-reflector antenna (2); characterized in that: It comprises a folding and unfolding module (3), a main connecting rod (4), a secondary connecting rod (5), a secondary reflection installation module (6), a main reflection installation module (7), a main locking module (8) and a secondary locking module (9); The folding and unfolding module (3) is used to realize 180° flipping of the secondary connecting rod (5), and comprises a main support frame (31), a coil spring (32), a reducer (33), a support shaft (34), a lock (35) and an annular guide rail (36); the main support frame (31) is arranged on the cabin board of the star body (10); the coil spring (32) is arranged on the main support frame (31), and its output end is connected to the support shaft (34) through the reducer (33); the support shaft (34) is connected to one end of the secondary connecting rod (5); the coil spring (32) drives the support shaft (34) to rotate, and the secondary connecting rod (5) is unfolded above the cabin board of the star body (10) with the support shaft (34) as the axis to realize 180° flipping, and the other end of the secondary connecting rod (5) is flipped to the outside of the star body (10); the annular guide rail (36) is arranged The main support frame (31) is provided with a slot (37), the locking device (35) is provided on the auxiliary connecting rod (5), and the locking device (35) is used to cooperate with the slot (37) of the annular guide rail (36) to achieve locking of the auxiliary connecting rod (5) after turning 180 degrees; the locking device (35) comprises an outer cylinder (351), a pressure cover (352), a compression spring (353) and a locking pressure rod (354); the outer cylinder (351) is provided on the auxiliary connecting rod (5), the pressure cover (352) is provided on the outer cylinder (351), the compression spring (353) is provided in the outer cylinder (351), one end of the compression spring (353) is limited by the pressure cover (352), and the other end is connected to the locking pressure rod (354), so that the locking pressure rod (354) moves along its axis and cooperates with the slot (37) to achieve locking; The secondary reflector mounting module (6) comprises a secondary reflector bracket (61) and a secondary reflector motor (62); the secondary reflector bracket (61) is connected to the other end of the secondary connecting rod (5); the secondary reflector motor (62) is arranged on the secondary reflector bracket (61); the output shaft of the secondary reflector motor (62) is connected to one end of the main connecting rod (4), so that the main connecting rod (4) performs a rotational motion with the connection point as the center of the circle; the secondary reflector antenna (2) is arranged on the output shaft of the secondary reflector motor (62) or the main connecting rod (4) to achieve synchronous rotation with the main connecting rod (4); the length of the main connecting rod (4) is less than the length of the secondary connecting rod (5), so that the main connecting rod (4) drives the main reflector antenna (1) to rotate outside the star body (10) to achieve ground scanning; The main reflection mounting module (7) comprises a main reflection bracket (71) and a main reflection motor (72); the main reflection bracket (71) is arranged at the other end of the main connecting rod (4); the main reflection motor (72) is mounted on the main reflection bracket (71), and its output shaft is connected to the main reflection surface antenna (1) and is used to drive the main reflection surface antenna (1) to achieve self-rotation around its axis; The main locking module (8) comprises a main ejector (81), a main locking column (82) and a main locking device pressure plate (83); the main locking column (82) is fixedly arranged on the cabin plate of the star body (10), and the main locking device pressure plate (83) is arranged on the main reflection bracket (71); the main ejector (81) is a memory alloy unlocker; The secondary locking module (9) has the same structure as the primary locking module (8).

2. The foldable multi-dimensional unfolding mechanism for space loads according to claim 1, characterized in that: The sub-reflector motor (62) is a hollow motor. The main reflector antenna (1) transmits the collected signal wave to the sub-reflector antenna (2). The sub-reflector antenna (2) transmits the signal wave to the feed source through the through hole of the hollow motor. The feed source transmits the signal to the star body (10) through the transmission waveguide.

3. The foldable multi-dimensional unfolding mechanism for space loads according to claim 1, characterized in that: The main ejector (81) comprises a main separation head (811) and a main connection bolt (812); the main separation head (811) is arranged on a main locking column (82); the main connection bolt (812) is used to connect the main separation head (811) and a main locking device pressure plate (83); after power is turned on, the main separation head (811) and the main connection bolt (812) are disengaged, so that the main locking column (82) and the main locking device pressure plate (83) are disengaged.

4. The foldable multi-dimensional unfolding mechanism for space loads according to claim 1, characterized in that: The secondary locking module (9) comprises a secondary ejector (91), a secondary locking column (92) and a secondary locking device pressure plate (93); the secondary locking column (92) is fixedly arranged on a cabin plate of a satellite body (10), and the secondary locking device pressure plate (93) is arranged on a secondary reflection bracket (61); the secondary ejector (91) is a memory alloy unlocker, which connects the secondary locking column (92) and the secondary locking device pressure plate (93) during the satellite launch phase, and separates and disengages the secondary locking column (92) and the secondary locking device pressure plate (93) after the satellite enters orbit; The auxiliary ejector (91) comprises an auxiliary separation head (911) and an auxiliary connecting bolt (912); the auxiliary separation head (911) is arranged on the auxiliary locking column (92); the auxiliary connecting bolt (912) is used to connect the auxiliary separation head (911) and the auxiliary locking device pressure plate (93); after power is turned on, the auxiliary separation head (911) and the auxiliary connecting bolt (912) are disengaged, so that the auxiliary locking column (92) and the auxiliary locking device pressure plate (93) are disengaged.

5. The foldable multi-dimensional unfolding mechanism for space loads according to claim 1, characterized in that: An annular boss (355) is provided at one end of the locking pressure rod (354) connected to the compression spring (353). The annular boss (355) is arranged in the outer tube (351) and is used to prevent the connecting end of the locking pressure rod (354) and the compression spring (353) from falling out of the outer tube (351).

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