L-shaped electric propulsion two-dimensional rotating mechanism

Abstract

The invention belongs to the technical field of asteroid exploration satellite propulsion application, and particularly relates to an L-shaped electric propulsion two-dimensional rotating mechanism. Comprising a simulated star body, an azimuth driving mechanism, an L-shaped connecting plate, a pitching driving mechanism, a pressing and releasing mechanism and an electric propulsion system mounting platform, the azimuth driving mechanism is arranged on the simulated star body, the output end of the azimuth driving mechanism is connected with the L-shaped connecting plate, the pitching driving mechanism is arranged on the L-shaped connecting plate, and the output end of the pitching driving mechanism is connected with the electric propulsion system mounting platform; the pressing and releasing mechanism is arranged between the simulated star body and the electric propulsion system mounting platform and is used for locking or releasing the electric propulsion system mounting platform; and the azimuth driving mechanism and the pitching driving mechanism are respectively used for adjusting the pitching angle and the azimuth angle of a propeller on the electric propulsion system mounting platform. According to the invention, the thrust direction of the thruster can be changed, the rotation angle in the two-dimensional direction can be measured in real time, and support is provided for orbit transfer, attitude control, position maintenance and constellation formation flight of microsatellites.

Description

Technical Field

[0001] The invention belongs to the technical field of propulsion application of asteroid exploration satellites, and specifically is an L-type electric propulsion two-dimensional rotating mechanism. Background Art

[0002] With the rapid development of aerospace technology, the requirements of space missions for spacecraft propulsion systems are becoming more and more diverse. New aerospace missions such as deep space exploration, space satellite networking, all-electric propulsion satellites, and high-precision space science exploration satellites are constantly emerging. These missions have different requirements for satellite propulsion systems. Drag-free control requires the propulsion system to have micro-thrust and high resolution to compensate for non-conservative forces in real time. Commercial satellites require space propulsion systems to be low-cost and cost-effective to improve market competitiveness. In order to meet the needs of space missions from different fields such as military, commercial, and scientific research, space propulsion technology has been continuously developing and improving.

[0003] The two-dimensional rotation mechanism serves as the installation platform of the space propulsion system, driving the propulsion system to perform azimuth and pitch movements, thereby changing the thrust direction of the thruster and measuring the rotation angle in the two-dimensional direction in real time, realizing the orbit transfer, attitude control, position maintenance and constellation formation flight of micro-satellites. The two-dimensional rotation mechanism is the structural basis for the propulsion system to achieve propulsion, and plays a vital role in the development and improvement of space propulsion technology. However, the current two-dimensional rotation mechanism still has many problems such as large size, heavy mass, low precision and high cost, and therefore cannot meet the requirements of micro-satellite propulsion. Summary of the invention

[0004] In order to meet the requirements of microsatellite propulsion, the purpose of the present invention is to provide an L-type electric propulsion two-dimensional rotation mechanism, which can change the thrust direction of the propeller and measure the rotation angle in two dimensions in real time, so as to provide support for the orbit transfer, attitude control, position maintenance and constellation formation flight of microsatellites.

[0005] The objective of the present invention is achieved through the following technical solutions:

[0006] The present invention provides an L-shaped electric propulsion two-dimensional rotation mechanism, comprising a simulated star body, an azimuth drive mechanism, an L-shaped connecting plate, a pitch drive mechanism, a clamping and releasing mechanism and an electric propulsion system installation platform, wherein the azimuth drive mechanism is arranged on the simulated star body, and the output end is connected to the L-shaped connecting plate, the pitch drive mechanism is arranged on the L-shaped connecting plate, and the output end is connected to the electric propulsion system installation platform; the clamping and releasing mechanism is arranged between the simulated star body and the electric propulsion system installation platform, and is used for locking or releasing the electric propulsion system installation platform; the electric propulsion system installation platform is used for installing a thruster, and the azimuth drive mechanism and the pitch drive mechanism are used for adjusting the pitch and azimuth angles of the thruster respectively.

[0007] A mounting seat is provided on the simulated star body, and the azimuth driving mechanism is mounted on the mounting seat; the rotation axes of the azimuth driving mechanism and the pitch driving mechanism are perpendicular to each other.

[0008] The azimuth drive mechanism and the pitch drive mechanism have the same structure, both comprising a stepper motor, a housing, an end transmission flange, an output shaft assembly, a photoelectric encoder and a harmonic reducer, wherein the harmonic reducer is arranged in the housing, the stepper motor is mounted on the housing and the output end is connected to the input shaft of the harmonic reducer, and the output end of the harmonic reducer is connected to the end transmission flange through the output shaft assembly; the photoelectric encoder is arranged on the output shaft assembly, and the photoelectric encoder is used to detect the rotation angle of the output shaft assembly.

[0009] The azimuth drive mechanism, the mounting seat and the L-shaped connecting plate, as well as the pitch drive mechanism, the L-shaped connecting plate and the electric propulsion system mounting platform are all insulated by thermal insulation pads.

[0010] The clamping and releasing mechanism includes an adapter, a memory alloy expander, a connecting plate, an in-place switch, a base and a rotating shaft, wherein the base is arranged on the simulated star body, the lower end of the connecting plate is rotatably connected to the base through the rotating shaft, and the upper end of the connecting plate is connected to the electric propulsion system mounting platform through the memory alloy expander; the in-place switch is arranged on the base, and when the memory alloy expander is expanded and broken, the connecting plate rotates downward to trigger the in-place switch, thereby unlocking the electric propulsion system mounting platform.

[0011] A heat insulating pad D is provided between the base and the simulated star.

[0012] The L-shaped electric propulsion two-dimensional rotation mechanism also includes a pipeline system arranged between the simulated star body and the electric propulsion system installation platform. The pipeline system passes through the azimuth drive mechanism and the pitch drive mechanism, and can follow the movement of the azimuth drive mechanism and the pitch drive mechanism.

[0013] The pipeline system includes a heat-insulating sleeve A, a penetration joint A, a penetration joint fixing plate, a penetration joint B, a pipeline A, a pipeline B, a penetration joint C and a heat-insulating sleeve B, wherein one end of the heat-insulating sleeve A is connected to the L-shaped connecting plate, and the other end is connected to the penetration joint fixing plate, and the axis of the heat-insulating sleeve A is colinear with the rotation axis of the azimuth driving mechanism; the pipeline A is wound around the heat-insulating sleeve A, and the two ends are respectively connected to the penetration joint A and the penetration joint B, the penetration joint A is installed on the simulated star, and the penetration joint B is installed on the penetration joint fixing plate;

[0014] The thermal insulation sleeve B is arranged on the pitch drive mechanism, and the axis of the thermal insulation sleeve B is colinear with the rotation axis of the pitch drive mechanism; the pipeline B is wound around the thermal insulation sleeve B, and the two ends are respectively connected to the through-plate joint B and the through-plate joint C, and the through-plate joint C is installed on the electric propulsion system installation platform.

[0015] A plurality of pipe clamps A are provided on the outer side of the heat insulation sleeve A along the circumferential direction, and the pipe clamps A prevent the pipe A from falling off;

[0016] A plurality of pipe clamps B are provided on the outer side of the heat insulation sleeve B along the circumferential direction, and the pipe clamps B prevent the pipe B from falling off.

[0017] The pipeline A includes an inner pipeline A, a middle pipeline A and an outer pipeline A; the pipeline B includes an inner pipeline B, a middle pipeline B and an outer pipeline B; wherein the inner pipeline A is connected to the inner pipeline B, the middle pipeline A is connected to the middle pipeline B, and the outer pipeline A is connected to the outer pipeline B.

[0018] The advantages and positive effects of the present invention are:

[0019] The invention provides an L-shaped electric propulsion two-dimensional rotation mechanism, which is used as the main functional component of the satellite propulsion system to change the thrust direction of the thruster and measure the rotation angle in the two-dimensional direction in real time, and adjust the pointing angle in real time according to the command of the platform; when adjusting the angle, it plays a connecting and supporting role between the electric thruster, the driving angle measurement unit and the cabin plate, and has the ability to maintain the posture of the driving mechanism when the power is off; it is pressed during the satellite launch phase to limit the movement of the mechanism and ensure that the mechanism withstands the harsh mechanical environment of the launch phase; it is unlocked and released after the satellite enters orbit, so that the mechanism can start to adjust the direction; when the electric thruster is ignited for direction adjustment, the thruster is provided with air supply, the two ends are connected to the thruster and the entire satellite, and pass through the outside of the rotation mechanism to fix and reduce the resistance torque as much as possible; the design not only meets the current satellite propulsion needs, but also can be used as the main propulsion system of small spacecraft for orbit enhancement and life extension of low-Earth orbit missions. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a schematic diagram of the three-dimensional structure of an L-shaped electric propulsion two-dimensional rotation mechanism of the present invention;

[0021] Figure 2 It is a structural schematic diagram of the azimuth driving mechanism in the present invention;

[0022] Figure 3 It is a structural schematic diagram of the pitch driving mechanism in the present invention;

[0023] Figure 4 It is a three-dimensional structural schematic diagram of the compression and release mechanism in the present invention;

[0024] Figure 5It is a schematic diagram of the three-dimensional structure of the pipeline system in the present invention.

[0025] In the figure: 1-simulated star;

[0026] 2- azimuth drive mechanism, 201- stepper motor, 202- motor seat, 203- transition plate, 204- housing, 205- thermal insulation pad A, 206- protective cover, 207- end transmission flange, 208- thermal insulation pad B, 209- end fixing plate, 210- output shaft, 211- photoelectric encoder, 212- bearing end cover, 213- mounting seat, 214- thermal insulation pad C, 215- angular contact ball bearing, 216- adapter shaft, 217- adapter shaft gasket, 218- harmonic reducer, 219- input shaft;

[0027] 3-L-type connecting plate;

[0028] 4- Pitch drive mechanism;

[0029] 5-pressing and releasing mechanism, 501-adapter, 502-memory alloy expander, 503-connecting plate, 504-in-place switch, 505-insulation pad D, 506-base, 507-rotating shaft;

[0030] 6-pipe system, 601-insulation sleeve A, 602-pipe clamp A, 603-thru-board joint A, 604-thru-board joint fixing plate, 605-pipe clamp B, 606-thru-board joint B, 607-inner pipeline A, 608-middle pipeline A, 609-outer pipeline A, 610-inner pipeline B, 611-middle pipeline B, 612-outer pipeline B, 613-thru-board joint C, 614-insulation sleeve B;

[0031] 7-Electric propulsion system installation platform. DETAILED DESCRIPTION

[0032] In order to make the purpose, technical solutions and advantages of the present invention more clear, the present invention is described in detail below with reference to the accompanying drawings and specific embodiments.

[0033] See also Figure 1As shown, the present invention provides an L-type electric propulsion two-dimensional rotation mechanism, including a simulated star body 1, an azimuth drive mechanism 2, an L-shaped connecting plate 3, a pitch drive mechanism 4, a clamping and releasing mechanism 5 and an electric propulsion system installation platform 7, wherein the azimuth drive mechanism 2 is arranged on the simulated star body 1, and the output end is connected to the L-shaped connecting plate 3, the pitch drive mechanism 4 is arranged on the L-shaped connecting plate 3, and the output end is connected to the electric propulsion system installation platform 7; the clamping and releasing mechanism 5 is arranged between the simulated star body 1 and the electric propulsion system installation platform 7, and is used to lock or release the electric propulsion system installation platform 7; the electric propulsion system installation platform 7 is used to install a thruster, and the azimuth drive mechanism 2 and the pitch drive mechanism 4 are respectively used to adjust the pitch and azimuth angles of the thruster.

[0034] See also Figure 2 As shown, in the embodiment of the present invention, a mounting seat 213 is provided on the simulated star body 1, and the azimuth driving mechanism 2 is installed on the mounting seat 213; the azimuth driving mechanism 2 and the pitch driving mechanism 4 are respectively installed on two vertical surfaces of the L-shaped connecting plate 3, and the rotation axes are perpendicular to each other.

[0035] See also Figure 2 , Figure 3 As shown, in the embodiment of the present invention, the azimuth driving mechanism 2 and the pitch driving mechanism 4 have the same structure, both of which include a stepper motor 201, a housing 204, an end transmission flange 207, an output shaft assembly, a photoelectric encoder 211 and a harmonic reducer 218, wherein the harmonic reducer 218 is arranged in the housing 204, the stepper motor 201 is mounted on the housing 204 and the output end is connected to the input shaft 219 of the harmonic reducer 218, and the output end of the harmonic reducer 218 is connected to the end transmission flange 207 through the output shaft assembly; the photoelectric encoder 211 is arranged on the output shaft assembly, and the photoelectric encoder 211 is used to detect the rotation angle of the output shaft assembly. The harmonic reducer 218 has the characteristics of strong bearing capacity, large transmission ratio, high transmission accuracy and small return error.

[0036] Specifically, the stepper motor 201 is installed on the housing 204 through the motor seat 202 and the transition plate 203. Two angular contact ball shafts 215 are installed back to back in the housing 204 to improve the support stiffness. The angular contact ball shaft 215 is axially limited by the bearing end cover 212. The output shaft assembly includes an adapter shaft 216 and an output shaft 210. The adapter shaft 216 is supported by two angular contact ball shafts 215. One end of the adapter shaft 216 is connected to the output end of the harmonic reducer 218 through the adapter shaft gasket 217. One end of the adapter shaft 216 is connected to the output shaft 210. The output shaft 210 is connected to the end transmission flange 207 through the end fixing plate 209. The outer side of the output shaft 210 is provided with a protective cover 206, which is connected to the housing 204. The output shaft 210 transmits power to the end transmission flange 207. The photoelectric encoder 211 is connected to the output shaft 210, which can accurately measure the rotation angle and rotation speed.

[0037] Furthermore, the azimuth drive mechanism 2 and the mounting seat 213 and the L-shaped connecting plate 3, as well as the pitch drive mechanism 4 and the L-shaped connecting plate 3 and the electric propulsion system mounting platform 7 are all insulated by thermal insulation pads. Specifically, the housing 204 is mounted on the mounting seat 213 through a thermal insulation pad A205, and the mounting seat 213 is mounted on the simulated star body 1 through a thermal insulation pad C214. In this way, the azimuth drive mechanism 2 and the simulated star body 1 are insulated, and no heat conduction occurs between the two, and they do not affect each other. One end of the L-shaped connecting plate 3 is connected to the end transmission flange 207 through a thermal insulation pad B208, and the other end is insulated from the pitch drive mechanism 4 through another thermal insulation pad A205. The heat generated by the rotation of the two does not affect each other, which is conducive to maintaining the transmission accuracy.

[0038] See also Figure 4 As shown, in the embodiment of the present invention, the clamping release mechanism 5 includes an adapter 501, a memory alloy expander 502, a connecting plate 503, an in-place switch 504, a base 506 and a rotating shaft 507, wherein the base 506 is arranged on the simulated star 1, the lower end of the connecting plate 503 is rotatably connected to the base 506 through the rotating shaft 507, and the upper end of the connecting plate 503 is connected to the electric propulsion system installation platform 7 through the memory alloy expander 502; the in-place switch 504 is arranged on the base 506; when the memory alloy expander 502 is expanded and broken, the connecting plate 503 rotates downward to the in-place switch 504, thereby unlocking the electric propulsion system installation platform 7. The memory alloy expander 502 is a commercially available product, which belongs to mature technology, and the memory alloy expander 502 can also be replaced by a pyrotechnic product.

[0039] Furthermore, a heat insulating pad D505 is provided between the base 506 and the simulated star body 1 so that the base 506 and the simulated star body 1 are insulated from each other.

[0040] See also Figure 1As shown, based on the above embodiment, the present invention provides an L-shaped electric propulsion two-dimensional rotation mechanism, which also includes a pipeline system 6 arranged between the simulated star body 1 and the electric propulsion system installation platform 7, and the pipeline system 6 is connected to the electric propulsion device to form a loop to provide power for the electric propulsion device. The pipeline system 6 passes through the azimuth drive mechanism 2 and the pitch drive mechanism 4, and can follow the movement of the azimuth drive mechanism 2 and the pitch drive mechanism 4.

[0041] See also Figure 1 , Figure 3 , Figure 5 As shown, in the embodiment of the present invention, the pipeline system 6 includes a heat insulating sleeve A601, a through-plate joint A603, a through-plate joint fixing plate 604, a through-plate joint B606, a pipeline A, a pipeline B, a through-plate joint C613 and a heat insulating sleeve B614, wherein one end of the heat insulating sleeve A601 is connected to the L-shaped connecting plate 3, and the other end is connected to the through-plate joint fixing plate 604, and the axis of the heat insulating sleeve A601 is colinear with the rotation axis of the azimuth driving mechanism 2; the pipeline A is wound around the heat insulating sleeve A601, and the two ends are respectively connected to the through-plate joint A6 03 is connected with the through-plate joint B606, the through-plate joint A603 is installed on the simulated star body 1, and the through-plate joint B606 is installed on the through-plate joint fixing plate 604; the thermal insulation sleeve B614 is installed on the transition plate 203 of the pitch drive mechanism 4, and the axis of the thermal insulation sleeve B614 is colinear with the rotation axis of the pitch drive mechanism 4; the pipeline B is wound around the thermal insulation sleeve B614, and the two ends are respectively connected with the through-plate joint B606 and the through-plate joint C613, and the through-plate joint C613 is installed on the electric propulsion system installation platform 7.

[0042] Furthermore, a plurality of pipe clamps A602 are provided along the circumferential direction on the outer side of the heat insulating sleeve A601. In this embodiment, three pipe clamps A602 are used, and both ends of each pipe clamp A602 are respectively connected to the L-shaped connecting plate 3 and the through-plate joint fixing plate 604. The pipeline A is located inside the pipe clamp A602, and the pipe clamp A602 prevents the pipeline A from falling off the heat insulating sleeve A601.

[0043] Furthermore, a plurality of pipe clamps B605 are provided along the circumferential direction on the outer side of the heat insulating sleeve B614, and the pipeline B is located on the inner side of the pipe clamp B605, and the pipe clamp B605 prevents the pipeline B from falling off the heat insulating sleeve B614. The heat insulating sleeve B614 provides installation support for the pipe clamp B605 on the one hand, and avoids heat exchange with the pipeline system 6 on the other hand. The heat insulating sleeve A601 and the pipe clamp A602 provide spatial orientation and support for the pipeline B.

[0044] In the embodiment of the present invention, pipeline A includes an inner pipeline A607, a middle pipeline A608 and an outer pipeline A609, and the two ends of each pipeline are respectively connected to a group of through-plate joints; pipeline B includes an inner pipeline B610, a middle pipeline B611 and an outer pipeline B612, and the two ends of each pipeline are respectively connected to a group of through-plate joints; wherein the inner pipeline A607 is connected to the inner pipeline B610, the middle pipeline A608 is connected to the middle pipeline B611, and the outer pipeline A609 is connected to the outer pipeline B612. Correspondingly, three through-plate joints A603 are provided on the simulated star 1, three through-plate joints B606 are provided on the through-plate joint fixing plate 604, and three through-plate joints C613 are provided on the electric propulsion system installation platform 7.

[0045] The present invention provides an L-shaped electric propulsion two-dimensional rotation mechanism, in which the azimuth drive mechanism 2 is connected to the pitch drive mechanism 4 to realize two-axis linkage. Under the premise of limited installation space, the layout is optimized and the installation is reasonable so that the envelope size is minimized at the extreme motion position. The clamping release mechanism 5 is installed on the simulated star body 1 in a 45-degree installation manner, and the freedom degrees in two directions are fixed at the same time. The pipeline system 6 adopts a passing method from the azimuth drive mechanism 2 and the pitch drive mechanism 4, and is fixed on the mechanism. The pipeline cable is bendable and can follow the movement of the mechanism, and the resistance torque is small. The pitch drive mechanism 4 is connected to the electric propulsion system installation platform 7, and the electric thruster is installed on the electric propulsion system installation platform 7. The two-dimensional rotation mechanism formed in this way serves as the structural basis for the propulsion system to realize propulsion, and plays a vital role in the development and improvement of space propulsion technology.

[0046] The present invention provides an L-shaped electric propulsion two-dimensional rotation mechanism, the working principle of which is:

[0047] The present invention provides an L-shaped electric propulsion two-dimensional rotation mechanism, which is used as the main functional component of the satellite propulsion system to change the thrust direction of the electric thruster and measure the rotation angle in the two-dimensional direction in real time, and adjust the pointing angle in real time according to the platform's instructions; when adjusting the angle, it plays a connecting and supporting role between the electric thruster, the driving angle measurement unit and the cabin plate, and has the ability to drive the mechanism to maintain its posture when the power is off; during the satellite launch phase, it is pressed to limit the movement of the mechanism to ensure that the mechanism withstands the harsh mechanical environment of the launch phase; after the satellite enters orbit, it is unlocked and the mechanism is released so that the mechanism can start to adjust the direction; when the electric thruster is ignited for direction adjustment, the electric thruster is provided with air supply, the two ends are connected to the electric thruster and the entire satellite, and pass through the outside of the rotation mechanism to fix and reduce the resistance torque as much as possible; this design not only meets the current needs of satellite propulsion, but can also be used as the main propulsion system of small spacecraft for orbit enhancement and life extension of low-Earth orbit missions.

[0048] The present invention relates to an L-shaped electric propulsion two-dimensional rotation mechanism, which is installed on a simulated star body 1, and an electric propulsion system installation interface is reserved thereon. The azimuth drive mechanism 2 and the pitch drive mechanism 4 adopt a standardized design, and the internal structure is exactly the same. The two are connected by an L-shaped connecting plate 3 to realize the linkage of the two axes; under the premise of limited installation space, the layout is optimized and the installation is reasonable so that the envelope size is minimized at the extreme motion position. The clamping release mechanism adopts a 45-degree installation method, which can limit the freedom in two directions at the same time, greatly saving installation space, quality and cost. The pipeline system 6 adopts a passing method from the azimuth drive mechanism 2 and the pitch drive mechanism 4, and is fixed on the mechanism. The cable is bendable and can follow the movement of the mechanism, and the resistance torque is small. The present invention provides a mechanical and electronically controlled installation interface for the electric propulsion system. As an installation platform for the electric thruster, it is the most important structural foundation for the propulsion system to achieve propulsion.

[0049] The above description is only an embodiment of the present invention and is not intended to limit the protection scope of the present invention. Any modification, equivalent replacement, improvement, expansion, etc. made within the spirit and principle of the present invention are included in the protection scope of the present invention.

Claims

1. An L-shaped electric propulsion two-dimensional rotation mechanism, characterized in that: The invention comprises a simulated star body (1), an azimuth drive mechanism (2), an L-shaped connecting plate (3), a pitch drive mechanism (4), a clamping and releasing mechanism (5) and an electric propulsion system installation platform (7), wherein the azimuth drive mechanism (2) is arranged on the simulated star body (1), and the output end is connected to the L-shaped connecting plate (3); the pitch drive mechanism (4) is arranged on the L-shaped connecting plate (3), and the output end is connected to the electric propulsion system installation platform (7); the clamping and releasing mechanism (5) is arranged between the simulated star body (1) and the electric propulsion system installation platform (7), and is used to lock or release the electric propulsion system installation platform (7); the electric propulsion system installation platform (7) is used to install a thruster, and the azimuth drive mechanism (2) and the pitch drive mechanism (4) are used to adjust the pitch and azimuth angles of the thruster respectively.

2. The L-shaped electric propulsion two-dimensional rotation mechanism according to claim 1, characterized in that: The simulated star body (1) is provided with a mounting seat (213), and the azimuth driving mechanism (2) is mounted on the mounting seat (213); the rotation axes of the azimuth driving mechanism (2) and the elevation driving mechanism (4) are perpendicular to each other.

3. The L-shaped electric propulsion two-dimensional rotation mechanism according to claim 2, characterized in that: The azimuth drive mechanism (2) and the pitch drive mechanism (4) have the same structure, and both comprise a stepper motor (201), a housing (204), an end transmission flange (207), an output shaft assembly, a photoelectric encoder (211), and a harmonic reducer (218), wherein the harmonic reducer (218) is arranged in the housing (204), the stepper motor (201) is mounted on the housing (204) and the output end is connected to the input shaft (219) of the harmonic reducer (218), and the output end of the harmonic reducer (218) is connected to the end transmission flange (207) via the output shaft assembly; the photoelectric encoder (211) is arranged on the output shaft assembly, and the photoelectric encoder (211) is used to detect the rotation angle of the output shaft assembly.

4. The L-shaped electric propulsion two-dimensional rotation mechanism according to claim 2, characterized in that: The azimuth drive mechanism (2), the mounting seat (213) and the L-shaped connecting plate (3), and the pitch drive mechanism (4), the L-shaped connecting plate (3) and the electric propulsion system mounting platform (7) are all insulated by thermal insulation pads.

5. The L-shaped electric propulsion two-dimensional rotation mechanism according to claim 1, characterized in that: The clamping and releasing mechanism (5) comprises an adapter (501), a memory alloy expander (502), a connecting plate (503), an in-position switch (504), a base (506) and a rotating shaft (507), wherein the base (506) is arranged on the simulated star (1), the lower end of the connecting plate (503) is rotatably connected to the base (506) via the rotating shaft (507), and the upper end of the connecting plate (503) is connected to the electric propulsion system installation platform (7) via the memory alloy expander (502); the in-position switch (504) is arranged on the base (506), and when the memory alloy expander (502) is expanded and broken, the connecting plate (503) rotates downward to trigger the in-position switch (504), thereby unlocking the electric propulsion system installation platform (7).

6. The L-shaped electric propulsion two-dimensional rotation mechanism according to claim 5, characterized in that: A heat insulating pad D (505) is provided between the base (506) and the simulated star (1).

7. The L-shaped electric propulsion two-dimensional rotation mechanism according to claim 1, characterized in that: It also includes a pipeline system (6) arranged between the simulated star body (1) and the electric propulsion system installation platform (7), wherein the pipeline system (6) passes through the azimuth drive mechanism (2) and the pitch drive mechanism (4), and can follow the movement of the azimuth drive mechanism (2) and the pitch drive mechanism (4).

8. The L-shaped electric propulsion two-dimensional rotation mechanism according to claim 7, characterized in that: The pipeline system (6) comprises a heat-insulating sleeve A (601), a through-plate joint A (603), a through-plate joint fixing plate (604), a through-plate joint B (606), a pipeline A, a pipeline B, a through-plate joint C (613) and a heat-insulating sleeve B (614), wherein one end of the heat-insulating sleeve A (601) is connected to the L-shaped connecting plate (3), and the other end is connected to the through-plate joint fixing plate (604), and the axis of the heat-insulating sleeve A (601) is colinear with the rotation axis of the azimuth driving mechanism (2); the pipeline A is wound around the heat-insulating sleeve A (601), and the two ends are respectively connected to the through-plate joint A (603) and the through-plate joint B (606), the through-plate joint A (603) is installed on the simulated star (1), and the through-plate joint B (606) is installed on the through-plate joint fixing plate (604); The heat-insulating sleeve B (614) is arranged on the pitch drive mechanism (4), and the axis of the heat-insulating sleeve B (614) is colinear with the rotation axis of the pitch drive mechanism (4); the pipeline B is wound around the heat-insulating sleeve B (614), and the two ends are respectively connected to the through-plate joint B (606) and the through-plate joint C (613), and the through-plate joint C (613) is installed on the electric propulsion system installation platform (7).

9. The L-shaped electric propulsion two-dimensional rotation mechanism according to claim 8, characterized in that: A plurality of pipe clamps A (602) are provided on the outer side of the heat insulation sleeve A (601) along the circumferential direction, and the pipe clamps A (602) prevent the pipe A from falling off; A plurality of pipe clamps B (605) are provided along the circumferential direction on the outer side of the heat insulating sleeve B (614), and the pipe clamps B (605) prevent the pipe B from falling off.

10. The L-shaped electric propulsion two-dimensional rotation mechanism according to claim 8, characterized in that: The pipeline A includes an inner pipeline A (607), a middle pipeline A (608) and an outer pipeline A (609); the pipeline B includes an inner pipeline B (610), a middle pipeline B (611) and an outer pipeline B (612); wherein the inner pipeline A (607) is connected to the inner pipeline B (610), the middle pipeline A (608) is connected to the middle pipeline B (611), and the outer pipeline A (609) is connected to the outer pipeline B (612).

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