Unfolding locking device for satellite-borne driving mechanism

Abstract

The invention belongs to the technical field of spaceflight, and discloses an unfolding locking device for a satellite-borne driving mechanism, the unfolding locking device comprises a first connecting piece, a second connecting piece, a positioning sliding block and a locking mechanism, the first connecting piece is inserted into the second connecting piece, the positioning sliding block is arranged on the circumferential inner wall of the second connecting piece, a first sliding groove is formed in the circumferential side of the first connecting piece, and the locking mechanism is arranged in the first sliding groove; the positioning sliding block is limited in the first sliding groove in a sliding mode, a second sliding groove is formed in the peripheral side of the first connecting piece, a limiting groove is formed in the end, close to the second connecting piece, of the second sliding groove, and the output end of the locking mechanism elastically abuts against the inner wall of the second sliding groove or elastically stretches into the limiting groove. According to the unfolding and locking device for the satellite-borne driving mechanism, the reliability of the unfolding process is improved through guide fit between a positioning sliding block and a first sliding groove, the connecting face of the locking mechanism and a limiting groove can be positioned through insertion fit between a first connecting piece and a second connecting piece, the profile precision is guaranteed, and the safety of the unfolding process is improved. And a good rigidity keeping effect can be achieved for the connection of the extensible mechanism.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and in particular to a deployment locking device for a satellite-borne drive mechanism. Background Art

[0002] With the development of aerospace technology, there is an urgent need for large / super-large foldable antennas with large aperture (high gain), high precision, high folding / expansion ratio, and low mass, as well as high storage ratio solar arrays. Limited by the space of the rocket fairing, onboard satellite antenna mechanisms, solar wings and other deployable mechanisms are in a folded state before launch. After entering orbit, they are unfolded and locked by the driving mechanism. Antennas, solar wings, etc. will rotate with the driving mechanism. In order to meet work requirements, it is necessary to ensure that their active envelope can avoid other components on the satellite, such as clamping seats, etc., so the driving and locking performance of the rotating mechanism is crucial for the reliable deployment of the deployable mechanism, maintaining structural rigidity, and maintaining surface accuracy.

[0003] The existing automatic locking device usually realizes self-locking by pushing the locking rod on the rotating rod into the positioning hole through the elastic force of the torsion spring after the rotating rod is rotated into place. Since the locking rod and the positioning hole are clearance-matched, the overall stiffness of the locked structure is often lower than expected.

[0004] Therefore, it is urgent to design a new deployment locking device for a satellite-borne drive mechanism to improve the above-mentioned problems. Summary of the invention

[0005] The object of the present invention is to provide a deployment locking device for a satellite-borne drive mechanism, so as to solve the technical problem that the locking performance and overall rigidity of the automatic locking device of the rotating mechanism cannot meet the requirements.

[0006] To achieve this object, the present invention adopts the following technical solutions:

[0007] The deployment locking device for a satellite-borne drive mechanism provided by the present invention is provided with a pressing device on the outside of the deployment locking device for a satellite-borne drive mechanism, and the deployment locking device for a satellite-borne drive mechanism comprises:

[0008] a first connecting member, the driving mechanism being connected to the first connecting member;

[0009] A second connecting member, one end of which is open, the expandable mechanism is connected to the edge of the opening of the second connecting member, the first connecting member is plugged into the second connecting member, and a first elastic member is provided between the first connecting member and the second connecting member along the plugging direction;

[0010] A positioning slider, the positioning slider is arranged on the circumferential inner wall of the second connecting member, a first sliding groove extending along the plugging direction is opened on the circumferential side of the first connecting member, and the positioning slider is slidably limited in the first sliding groove;

[0011] A locking mechanism is arranged on the circumferential inner wall of the second connecting member, a second slide groove extending along the plug-in side is opened on the circumferential side of the first connecting member, a limiting groove is arranged at one end of the second slide groove close to the second connecting member, and the output end of the locking mechanism elastically abuts against the inner wall of the second slide groove or elastically extends into the limiting groove.

[0012] As a preferred solution for the deployment and locking device of the satellite-borne drive mechanism, the pressing device is used to squeeze the first elastic member to contract, so that the first connecting member and the second connecting member are close to each other and in a retracted and locked state;

[0013] Alternatively, releasing the first elastic member drives the first connecting member and the second connecting member to move away from each other to be in an unfolded and locked state.

[0014] As a preferred solution of the deployment locking device for the satellite-borne drive mechanism, the locking mechanism comprises:

[0015] A locking pin housing, one side of which is connected to the circumferential inner wall of the second connecting member, and a through hole is formed in the locking pin housing;

[0016] a wedge-shaped locking pin, the wedge-shaped locking pin being located in the through hole;

[0017] A compression spring is located in the through hole, one end of the compression spring abuts against the inner wall of the second connecting member, and the other end abuts against the end of the wedge-shaped locking pin.

[0018] As a preferred solution of the deployment locking device for the satellite-borne drive mechanism, when in the retracted locking state, the compression spring is compressed, the wedge-shaped locking pin extends into the through hole, and one end of the wedge-shaped locking pin abuts against the inner wall of the second slide groove;

[0019] When in the unfolded locking state, the compression spring is released, the wedge-shaped locking pin extends out of the through hole, and one end of the wedge-shaped locking pin is located in the limiting groove.

[0020] As a preferred solution for the deployment locking device of the satellite-borne drive mechanism, a limiting portion is provided on the outer periphery of the end of the second slide groove away from the limiting groove, and the limiting portion is used to limit the locking mechanism to be located in the second slide groove.

[0021] As a preferred solution for the deployment locking device of the satellite-borne drive mechanism, the end edge of the wedge-shaped locking pin is arranged in an arc surface, and the inclination angle of the arc surface is smaller than the friction angle of the friction coefficient between the wedge-shaped locking pin and the contact surface of the limit groove.

[0022] As a preferred solution for the deployment locking device of the satellite-borne drive mechanism, the locking pin housing and the positioning slide block are both detachably connected to the circumferential inner wall of the second connecting member by screws.

[0023] As a preferred solution for the deployment locking device of the satellite-borne drive mechanism, a threaded hole is provided on the outer periphery of the second connecting member, the diameter of the threaded hole is smaller than the diameter of the through hole, a reset screw hole is provided at the end of the wedge-shaped locking pin, and a reset screw is threadedly connected to the threaded hole and the end of the reset screw is threadedly connected to the reset screw hole.

[0024] As a preferred solution for the deployment and locking device of the satellite-borne drive mechanism, the positioning slider is arranged in a T shape, and the shape of the first slide groove matches the positioning slider. When in the deployment and locking state, the shoulder of the positioning slider abuts against the inner wall of the first slide groove.

[0025] As a preferred solution for the deployment locking device of the satellite-borne drive mechanism, the first connecting member and the second connecting member are both arranged in a polygonal shape, and at least one of the positioning slider and the locking mechanism is provided.

[0026] Beneficial effects of the present invention:

[0027] During the process of track unlocking and releasing, the clamping device keeps clamping the clamping point of the deployable mechanism, so that the automatic locking device is in a retracted and locked state. When the clamping device is unlocked, the second connecting member is pushed away from the star table by the first elastic member. At the same time, the positioning slider is gradually inserted into the first slide groove and abuts against the inner wall of the first slide groove to ensure that the first connecting member and the second connecting member are always connected, and the first connecting member and the second connecting member are locked in the circumferential direction. The guiding cooperation between the positioning slider and the first slide groove can avoid the tilting and jamming problems caused by the large non-synchronous unlocking of multiple clamping points, thereby improving the reliability of the deployment process. The output end of the locking mechanism slides in the second sliding groove until it reaches the limiting groove. Under the push of the elastic member, the output end extends into the limiting groove and is kept tightly against the inner wall of the limiting groove, thereby realizing the locking of the first connecting member and the second connecting member along the plug-in direction. The locking mechanism can achieve a self-locking effect after moving into place. The plug-in cooperation between the first connecting member and the second connecting member can position the connecting surface of the locking mechanism and the limiting groove, ensure the surface accuracy, and have a good rigidity retention effect for the connection of the expandable mechanism. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 is a first structural schematic diagram of a folded and locked state of an unfolding and locking device for a satellite-borne drive mechanism provided by an embodiment of the present invention;

[0029] Figure 2 is a second structural schematic diagram of a folded and locked state of an unfolding and locking device for a satellite-borne drive mechanism provided by an embodiment of the present invention;

[0030] Figure 3 is a top view of a deployed locking device for a satellite-borne drive mechanism provided by an embodiment of the present invention in a retracted and locked state;

[0031] Figure 4 is along Figure 3 Sectional view along line AA;

[0032] Figure 5 is a first structural schematic diagram of an unfolding and locking state of an unfolding and locking device for a satellite-borne drive mechanism provided by an embodiment of the present invention;

[0033] Figure 6 is a second structural schematic diagram of an unfolding and locking state of an unfolding and locking device for a satellite-borne drive mechanism provided by an embodiment of the present invention;

[0034] Figure 7 is a top view of an unfolding and locking state of an unfolding and locking device for a satellite-borne drive mechanism provided by an embodiment of the present invention;

[0035] Figure 8 is along Figure 7 Cross-section along line BB.

[0036] In the figure:

[0037] 1. first connecting member; 11. first sliding groove; 12. second sliding groove; 121. limiting groove; 122. limiting portion; 13. embedding groove; 131. first elastic member;

[0038] 2. second connecting member; 21. threaded hole;

[0039] 3. Positioning slider;

[0040] 4. Locking mechanism; 41. Locking pin housing; 411. Perforation; 42. Wedge-shaped locking pin; 421. Reset screw hole;

[0041] 5. Compression spring. DETAILED DESCRIPTION

[0042] The present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are only used to explain the present invention, rather than to limit the present invention. It should also be noted that, for ease of description, only parts related to the present invention, rather than all structures, are shown in the accompanying drawings.

[0043] In the description of the present invention, unless otherwise clearly specified and limited, the terms "connected", "connected", and "fixed" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0044] In the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0045] In the description of this embodiment, the terms "upper", "lower", "right", etc., directions or positional relationships are based on the directions or positional relationships shown in the drawings, and are only for the convenience of description and simplification of operation, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as limiting the present invention. In addition, the terms "first" and "second" are only used to distinguish in the description and have no special meaning.

[0046] Combination Figure 1-Figure 8As shown, this embodiment provides an unfolding and locking device for a satellite-borne drive mechanism, and a clamping device (not shown in the figure) is arranged on the outside of the unfolding and locking device for the satellite-borne drive mechanism. The unfolding and locking device for the satellite-borne drive mechanism includes a first connecting member 1, a second connecting member 2, a positioning slider 3 and a locking mechanism 4. The driving mechanism is connected to the first connecting member 1, one end of the second connecting member 2 is open, the expandable mechanism is connected to the opening edge of the second connecting member 2, the first connecting member 1 is inserted into the second connecting member 2, a first elastic member 131 is arranged between the first connecting member 1 and the second connecting member 2 along the plug-in direction, the positioning slider 3 is arranged on the circumferential inner wall of the second connecting member 2, a first slide groove 11 extending along the plug-in direction is opened on the circumferential side of the first connecting member 1, the positioning slider 3 is slidably limited in the first slide groove 11, the locking mechanism 4 is arranged on the circumferential inner wall of the second connecting member 2, a second slide groove 12 extending along the plug-in direction is opened on the circumferential side of the first connecting member 1, a limiting groove 121 is arranged at one end of the second slide groove 12 close to the second connecting member 2, and the output end of the locking mechanism 4 elastically abuts against the inner wall of the second slide groove 12 or elastically extends into the limiting groove 121.

[0047] It should be noted that, during the process of rail unlocking and releasing, the pressing device keeps pressing the pressing point of the deployable mechanism, and the pressing device is used to squeeze the first elastic member 131 to contract, so that the first connecting member 1 and the second connecting member 2 are close to each other and in a retracted and locked state (see Figure 2 ), wherein there are usually multiple pressing points, and three are arranged in this embodiment.

[0048] When the clamping device is unlocked, the first elastic member 131 is released, and the second connecting member 2 is pushed away from the first connecting member 1 and away from the star table by the first elastic member 131, so that the automatic locking device is in the unfolded locking state (see Figure 6 ). During this process, the positioning slider 3 is gradually inserted into the first slide groove 11 and abuts against the inner wall of the first slide groove 11 to ensure that the first connecting member 1 and the second connecting member 2 are always connected, and the first connecting member 1 and the second connecting member 2 are locked in the circumferential direction. The guiding cooperation between the positioning slider 3 and the first slide groove 11 can avoid the large non-synchronous unlocking of multiple clamping points, resulting in tilting and jamming problems, thereby improving the reliability of the deployment process.

[0049] The output end of the locking mechanism 4 slides in the second slide groove 12 until it reaches the limit groove 121. Under the push of the elastic member, the output end extends into the limit groove 121 and is kept tightly against the inner wall of the limit groove 121, thereby realizing the locking of the first connecting member 1 and the second connecting member 2 along the plug-in direction. The locking mechanism 4 can achieve a self-locking effect after moving into place. The plug-in cooperation between the first connecting member 1 and the second connecting member 2 can position the connecting surface of the locking mechanism 4 and the limit groove 121, ensure the surface accuracy, and have a good rigidity retention effect for the connection of the expandable mechanism.

[0050] The first connecting member 1 is provided with an embedding groove 13 on the end surface facing the second connecting member 2, and the first elastic member 131 is located in the embedding groove 13. One end of the first elastic member 131 abuts against the bottom wall of the embedding groove 13, and the other end of the first elastic member 131 abuts against the inner wall of the second connecting member 2. Preferably, the first elastic member 131 is a spring.

[0051] like Figure 1 and Figure 2 As shown, the first connecting member 1 and the second connecting member 2 of this embodiment are both flange structures. The driving mechanism is connected to the first connecting member 1 by bolts, and the expandable mechanism is also connected to the second connecting member 2 by bolts. The flange structure is easy to install and disassemble, and is convenient for maintenance and repair. The flange structure can withstand greater pressure and tension, and can ensure the stability of the connection.

[0052] Specifically, the first connecting member 1 and the second connecting member 2 are both polygonal, and in this embodiment, they are hexagonal, and the rotation between the two in the circumferential direction is limited by the shape, and the stability is better. In other embodiments, they can also be quadrilaterals, pentagons or heptagons, etc., which are not specifically limited in this embodiment.

[0053] The output end of the driving mechanism is connected to one end face of the first connecting member 1 , six ear plates are correspondingly arranged at the opening edge and hexagonal positions of the second connecting member 2 , and the expandable mechanism is connected to one end face of the second connecting member 2 through the six ear plates.

[0054] In addition, three positioning sliders 3 and three locking mechanisms 4 are respectively provided, and a locking mechanism 4 is provided between every two adjacent positioning sliders 3. Since the three locking mechanisms 4 in the circular array can completely position a plane, the combination of the locking mechanism 4 and the positioning slider 3 can have a good rigidity maintenance effect for the connection of the expandable mechanism.

[0055] like Figure 3 and Figure 4As shown, the locking mechanism 4 of this embodiment includes a locking pin housing 41, a wedge-shaped locking pin 42 and a compression spring 5. One side of the locking pin housing 41 is connected to the circumferential inner wall of the second connecting member 2. A through hole 411 is penetrated through the locking pin housing 41. The wedge-shaped locking pin 42 is located in the through hole 411. The compression spring 5 is located in the through hole 411. One end of the compression spring 5 abuts against the inner wall of the second connecting member 2, and the other end of the compression spring 5 abuts against the end of the wedge-shaped locking pin 42.

[0056] When in the closed and locked state (see Figure 4 ), the compression spring 5 is compressed, the wedge-shaped locking pin 42 extends into the through hole 411, and one end of the wedge-shaped locking pin 42 abuts against the inner wall of the second sliding groove 12.

[0057] When in the unfolded locked state (see Figure 8 ), the compression spring 5 is released, the wedge-shaped locking pin 42 extends out of the through hole 411, and one end of the wedge-shaped locking pin 42 is located in the limiting groove 121.

[0058] like Figure 4 As shown, in order to avoid separation of the first connecting member 1 and the second connecting member 2, a limiting portion 122 is provided on the outer periphery of the end of the second sliding groove 12 away from the limiting groove 121, and the locking pin housing 41 is limited in the second sliding groove 12 or the limiting groove 121, that is, it is limited in the first connecting member 1 and the locking pin housing 41, which has better reliability.

[0059] Preferably, the locking pin housing 41 and the positioning slide block 3 are both detachably connected to the circumferential inner wall of the second connecting member 2 by screws, and the detachable installation is achieved by screws, which facilitates the assembly of the automatic locking device.

[0060] Optionally, the end edge of the wedge-shaped locking pin 42 is set to be an arc surface, and the inclination angle of the arc surface is smaller than the friction angle of the friction coefficient between the contact surface of the wedge-shaped locking pin 42 and the limiting groove 121, so the wedge-shaped locking pin 42 can achieve a self-locking effect after being locked in place, and the locking effect is good.

[0061] Preferably, the positioning slider 3 is arranged in a "T" shape, and the shape of the first slide groove 11 matches the positioning slider 3. When in the unfolded and locked state, the shoulder of the positioning slider 3 abuts against the inner wall of the first slide groove 11. On the one hand, the cooperation between the positioning slider 3 and the first slide groove 11 plays a role of limiting, and on the other hand, it plays a circumferential positioning function before the locking mechanism 4 is completely locked. The positioning slider 3 is made of self-lubricating material, and the contact surface between the positioning slider 3 and the first connecting member 1 is guaranteed by the tolerance to have a small gap between the surfaces, so as to ensure the stability of the first connecting member 1 during the unfolding process.

[0062] Furthermore, a threaded hole 21 is provided on the outer periphery of the second connecting member 2, the diameter of the threaded hole 21 is smaller than the diameter of the through hole 411, a reset screw hole 421 is provided at the end of the wedge-shaped locking pin 42, and a reset screw whose end is threadedly connected to the reset screw hole 421 is threadedly connected in the threaded hole 21.

[0063] In addition, a micro switch is also provided on the inner wall of the second connecting member 2. The micro switch is located in the second slide groove 12 or the limit groove 121. The micro switch is electrically connected to the controller. The micro switch is used to monitor the wedge-shaped locking pin 42 and send an in-position indication signal to the controller after the locking is completed, so that the operator can understand the locking status. The second connecting member 2 is provided with a wiring hole for the cable to pass through, which is convenient for the installation of electronic devices and components.

[0064] Now combined Figure 4 and Figure 8 The on-orbit deployment and locking process of the deployment and locking device for the onboard drive mechanism and the ground-based retraction and locking process are further described in detail:

[0065] After the pressing point of the deployable mechanism is unlocked, the deployable mechanism is pushed away from the star table under the elastic force of the first elastic member 131, and the wedge-shaped locking pin 42 slides along the second slide groove 12 to the limit groove 121. When the wedge-shaped locking pin 42 reaches the limit groove 121, the compression spring 5 pushes the wedge-shaped locking pin 42 into the limit groove 121 to complete self-locking, and the micro switch gives a locked in place indication signal, that is, the whole on-orbit process is completed. In this way, the deployable mechanism can maintain a safe distance from other units of the star table, especially the pressing seat, after being deployed in place, and use wedge-shaped unilateral locking, that is, the locking mechanism 4 is set with three, and the wedge-shaped locking pin 42 locks the pre-tightening force to amplify the locking, which has the effect of high-rigidity locking, and the three locking devices can achieve good surface retention.

[0066] The screw is screwed into the threaded hole 21 and threadedly connected with the reset screw hole 421 on the wedge-shaped locking pin 42, and the reset screw and the wedge-shaped locking pin 42 are dragged to squeeze the compression spring 5 to contract, thereby unlocking the wedge-shaped locking pin 42.

[0067] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention. For those skilled in the art, various obvious changes, readjustments and substitutions can be made without departing from the protection scope of the present invention. It is not necessary and impossible to list all the embodiments here. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the claims of the present invention.

Claims

1. A deployment locking device for a satellite-borne drive mechanism, wherein a clamping device is provided on the outside of the deployment locking device for a satellite-borne drive mechanism, characterized in that: The deployment locking device for the onboard drive mechanism includes: A first connecting member (1), the driving mechanism being connected to the first connecting member (1); a second connecting member (2), one end of the second connecting member (2) being open, the expandable mechanism being connected to the edge of the opening of the second connecting member (2), the first connecting member (1) being plugged into the second connecting member (2), and a first elastic member being provided between the first connecting member (1) and the second connecting member (2) along the plugging direction; A positioning slide block (3), the positioning slide block (3) being arranged on the circumferential inner wall of the second connecting member (2), a first slide groove (11) extending along the plugging direction being provided on the circumferential side of the first connecting member (1), the positioning slide block (3) being slidably limited in the first slide groove (11); A locking mechanism (4), the locking mechanism (4) being arranged on the circumferential inner wall of the second connecting member (2), a second slide groove (12) extending along the plugging direction is provided on the circumferential side of the first connecting member (1), a limiting groove (121) is provided at one end of the second slide groove (12) close to the second connecting member (2), and an output end of the locking mechanism (4) elastically abuts against the inner wall of the second slide groove (12) or elastically extends into the limiting groove (121).

2. The deployment and locking device for a satellite-borne drive mechanism according to claim 1, characterized in that: The pressing device is used to squeeze the first elastic member to contract, so that the first connecting member (1) and the second connecting member (2) are close to each other and are in a retracted and locked state; Alternatively, releasing the first elastic member drives the first connecting member (1) and the second connecting member (2) to move away from each other so as to be in an unfolded and locked state.

3. The deployment and locking device for a satellite-borne drive mechanism according to claim 2, characterized in that: The locking mechanism (4) comprises: A locking pin housing (41), one side of the locking pin housing (41) being connected to the circumferential inner wall of the second connecting member (2), and a through hole (411) being formed through the locking pin housing (41); a wedge-shaped locking pin (42), wherein the wedge-shaped locking pin (42) is located in the through hole (411); A compression spring, wherein the compression spring is located in the through hole (411), one end of the compression spring abuts against the inner wall of the second connecting member (2), and the other end abuts against the end of the wedge-shaped locking pin (42).

4. The deployment and locking device for a satellite-borne drive mechanism according to claim 3, characterized in that: When in the retracted locking state, the compression spring is compressed, the wedge-shaped locking pin (42) extends into the through hole (411), and one end of the wedge-shaped locking pin (42) abuts against the inner wall of the second sliding groove (12); When in the unfolded locking state, the compression spring is released, the wedge-shaped locking pin (42) extends out of the through hole (411), and one end of the wedge-shaped locking pin (42) is located in the limiting groove (121).

5. The deployment and locking device for a satellite-borne drive mechanism according to claim 3, characterized in that: A limiting portion (122) is provided on the outer periphery of the end of the second sliding groove (12) away from the limiting groove (121), and the limiting portion (122) is used to limit the locking mechanism (4) to be located in the second sliding groove (12).

6. The deployment and locking device for a satellite-borne drive mechanism according to claim 3, characterized in that: The end edge of the wedge-shaped locking pin (42) is arranged in the form of an arc surface, and the inclination angle of the arc surface is smaller than the friction angle of the friction coefficient between the contact surface of the wedge-shaped locking pin (42) and the limiting groove (121).

7. The deployment and locking device for a satellite-borne drive mechanism according to claim 3, characterized in that: The locking pin housing (41) and the positioning slide block (3) are both detachably connected to the circumferential inner wall of the second connecting member (2) via screws.

8. The deployment and locking device for a satellite-borne drive mechanism according to claim 3, characterized in that: A threaded hole (21) is provided on the outer periphery of the second connecting member (2), the diameter of the threaded hole (21) being smaller than the diameter of the through hole (411), a reset screw hole (421) is provided at the end of the wedge-shaped locking pin (42), and a reset screw whose end is threadedly connected to the reset screw hole (421) is internally threadedly connected to the threaded hole (21).

9. The deployment and locking device for a satellite-borne drive mechanism according to claim 3, characterized in that: The positioning slide block (3) is arranged in a T-shape, and the shape of the first slide groove (11) matches that of the positioning slide block (3). When in the unfolded and locked state, the shoulder of the positioning slide block (3) abuts against the inner wall of the first slide groove (11).

10. The deployment and locking device for a satellite-borne drive mechanism according to any one of claims 1 to 9, characterized in that: The first connecting member (1) and the second connecting member (2) are both arranged in a polygonal shape, and at least one of the positioning slide block (3) and the locking mechanism (4) is provided.

Images