Spacecraft interstage unlocking device and spacecraft

Abstract

The invention relates to the technical field of spacecrafts, and discloses a spacecraft interstage unlocking device and a spacecraft, the spacecraft interstage unlocking device comprises a protection cover, and the protection cover is connected with a first cabin section; the connecting piece penetrates through the second cabin section in a limiting manner and movably penetrates through the first cabin section and the top surface of the protective cover; a limiting groove is formed in the side wall of one end, extending into the protective cover, of the connecting piece; the locking mechanism is arranged in the protective cover and comprises a lock hook and a lock piece, the lock hook is rotationally connected to the inner wall of the protective cover, one end of the lock hook is bent to form a hook part, the lock piece is movably arranged in the protective cover and has a locking position and an unlocking position, and when the lock piece is located at the locking position, the lock piece abuts against the lock hook to limit rotation of the lock hook; when the lock piece is located at the unlocking position, the lock piece is separated from the second cabin section along with the first cabin section, and the connecting piece moves along with the second cabin section and drives the lock hook to rotate till the hook part is separated from the limiting groove. The spacecraft comprises the spacecraft interstage unlocking device. And testability is achieved, and the using impact force is low.

Description

Technical Field

[0001] The present invention relates to the field of spacecraft technology, and in particular to a spacecraft interstage unlocking device and a spacecraft. Background Art

[0002] The connection and separation of spacecraft stages is the key to the success of flight tests. At present, pyrotechnic devices are mainly used on launch vehicles to achieve the connection and unlocking of stage separation and rocket-satellite separation. Common pyrotechnic devices include separation bolts, separation nuts, cutting ropes, etc. Their advantages are simple and compact structure, small mass and volume, and fast response speed. However, since pyrotechnics rely on the energy generated by the explosion or combustion of gunpowder to destroy the structure, they can only be used once, and the impact load on the structure is large.

[0003] Therefore, there is an urgent need for a spacecraft interstage unlocking device and a spacecraft to solve the above problems. Summary of the invention

[0004] Based on the above, the purpose of the present invention is to provide a spacecraft interstage unlocking device and a spacecraft, which can be reused, have testability, have low impact force in use, and have high safety.

[0005] To achieve the above object, the present invention adopts the following technical solutions:

[0006] A spacecraft interstage unlocking device, wherein one of two compartments to be separated is a first compartment and the other is a second compartment, and the spacecraft interstage unlocking device comprises:

[0007] Protective cover;

[0008] A connecting piece, the connecting piece sequentially passes through the second compartment and moves through the first compartment and the top surface of the protective cover, and a side wall of one end of the connecting piece extending into the protective cover is provided with a limiting groove;

[0009] A locking mechanism is arranged in the protective cover, and the locking mechanism includes a locking hook and a locking element. The locking hook is rotatably connected to the inner wall of the protective cover, one end of the locking hook is bent to form a hook portion, and the locking element is movably arranged in the protective cover and has a locking position and an unlocking position. When the locking element is in the locking position, the locking element abuts against the locking hook to limit the rotation of the locking hook, and the hook portion is inserted into the limiting groove. When the locking element is in the unlocking position, the first compartment section and the second compartment section are separated, and the connecting element moves with the second compartment section and drives the locking hook to rotate until the hook portion is separated from the limiting groove.

[0010] As a preferred solution of a spacecraft inter-stage unlocking device, the locking mechanism also includes an elastic member, and the locking member is resettable and movable in the protective cover through the elastic member. In the initial state of the elastic member, the locking member is located in the locking position.

[0011] As a preferred solution of a spacecraft inter-stage unlocking device, the locking element includes a locking rod and a top block located at one end of the locking rod, a limiting portion is convexly provided on the outer periphery of the locking rod, the limiting portion is located between the top block and the bottom surface of the protective cover, the elastic element is connected between the limiting portion and the bottom surface of the protective cover, and under the elastic force of the elastic element, the locking element has a tendency to move away from the bottom surface of the protective cover, and the top block abuts against one end of the locking hook away from the hook portion.

[0012] As a preferred solution of a spacecraft inter-stage unlocking device, the inner wall of the protective cover is formed with a step surface, and the step surface is arranged opposite to the bottom surface of the protective cover. When the locking element is in the locking position, the limiting portion abuts against the step surface.

[0013] As a preferred solution of a spacecraft inter-stage unlocking device, a partition plate is provided in the protective cover, and the partition plate divides the protective cover into a first cavity and a second cavity arranged along the axial direction of the protective cover. A guide hole is provided on the partition plate, and the locking rod seal moves through the guide hole, the locking hook is located in the first cavity, and the limiting portion is located in the second cavity. A vent hole connected to the second cavity is provided on the peripheral wall of the protective cover, and the vent hole is used to allow gas to pass. The gas can push the limiting portion to move toward the bottom surface of the protective cover to drive the locking element to move from the locked position to the unlocked position.

[0014] As a preferred solution of a spacecraft interstage unlocking device, the outer periphery of the limiting portion is sealed to the inner wall of the protective cover.

[0015] As a preferred solution of a spacecraft interstage unlocking device, the end of the top block facing away from the locking rod is tapered.

[0016] As a preferred solution of a spacecraft interstage unlocking device, a through hole is provided on the bottom surface of the protective cover, and one end of the locking rod facing away from the top block moves through the through hole.

[0017] As a preferred solution for a spacecraft inter-stage unlocking device, a roller is rotatably provided at one end of the lock hook away from the hook portion, and when the lock element moves from the unlocking position to the locking position, the lock element pushes the roller and drives the lock hook to rotate.

[0018] A spacecraft, comprising the spacecraft interstage unlocking device described in any of the above technical solutions.

[0019] The beneficial effects of the present invention are:

[0020] The present invention provides a spacecraft interstage unlocking device, which realizes the locking and releasing of the restriction of the lock hook by the lock element through the transformation of the lock element between the locking position and the unlocking position. When the lock element is in the locking position, the lock element presses against the lock hook, so that the hook portion at the end of the lock hook is inserted into the limiting groove, and the connecting element cannot move under the limiting action of the lock hook, that is, the connecting element fixedly connects the first cabin section and the second cabin section; when the two cabin sections need to be separated, it is only necessary to move the lock element to the unlocking position, the lock element is away from the lock hook, and the lock hook is not restricted by external force, that is, it can rotate freely. When the first cabin section and the second cabin section are separated, the second cabin section is pulled away from the connecting element, the connecting element moves, and the lock hook is rotated under force until the hook portion is completely separated from the limiting groove, the connecting element is separated from the protective cover and the first cabin section along with the second cabin section, and the first cabin section and the second cabin section are separated smoothly. Under the above structure, the spacecraft interstage unlocking device can be reused and tested multiple times to ensure the reliability and accuracy of unlocking, and the unlocking structure is visible and measurable; and when unlocking and separating, it is only necessary to move the position of the lock element, and no additional driving mechanism is required to drive the lock hook to rotate to disengage from the limit groove. The structure is relatively simple, the cost is low, and the probability of mechanical failure is low; at the same time, compared with the prior art that uses pyrotechnic devices to achieve unlocking and separation, the spacecraft interstage unlocking device uses pure mechanical means to achieve interstage unlocking and separation, which can effectively avoid the impact force or fragments generated during unlocking from causing impact and damage to other structures, and has a higher safety level.

[0021] The present invention also provides a spacecraft, which includes the above-mentioned spacecraft inter-stage unlocking device, which can quickly and effectively realize the unlocking and separation between spacecraft cabins, and has high separation safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for use in the description of the embodiments of the present invention. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the contents of the embodiments of the present invention and these drawings without paying any creative work.

[0023] Figure 1 is a schematic structural diagram of a spacecraft interstage unlocking device provided by an embodiment of the present invention;

[0024] Figure 2 is a cross-sectional view of a spacecraft interstage unlocking device provided by an embodiment of the present invention Figure 1 (locked position);

[0025] Figure 3 is a cross-sectional view of a spacecraft interstage unlocking device provided by an embodiment of the present invention Figure 1 (unlocked position).

[0026] In the figure:

[0027] 1. First compartment; 2. Second compartment; 3. Protective cover; 31. Shell; 311. Step surface; 32. Bottom end cover; 33. Partition plate; 330. Guide hole; 301. First cavity; 302. Second cavity; 303. Vent; 4. Connector; 40. Limiting groove; 5. Locking mechanism; 51. Lock hook; 511. Hook; 512. Roller; 52. Locking member; 521. Locking rod; 522. Top block; 523. Limiting portion; 53. Elastic member; 6. First sealing gasket; 7. Second sealing gasket. DETAILED DESCRIPTION

[0028] 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.

[0029] 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.

[0030] 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.

[0031] In the description of the present embodiment, the terms "upper", "lower", "left", "right" and other directions or positional relationships are based on the directions or positional relationships shown in the accompanying 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 a limitation of the present invention. In the description of the present invention, unless otherwise specified, the meaning of "plurality" is two or more. In addition, the terms "first" and "second" are only used to distinguish in the description and have no special meaning.

[0032] like Figure 1-3As shown, the present embodiment provides a spacecraft inter-stage unlocking device for inter-cylinder connection unlocking, one of the two compartments to be separated is the first compartment 1, and the other is the second compartment 2, and the first compartment 1 and the second compartment 2 are connected along a first direction. Specifically, the spacecraft inter-stage unlocking device includes a protective cover 3, a connecting piece 4 and a locking mechanism 5. The protective cover 3 is connected to or not connected to the first compartment 1 along the first direction. Specifically, the top surface of the protective cover 3 is connected to the first compartment 1 by threads or other connection methods; the connecting piece 4 is limited to pass through the second compartment 2 in sequence and movably pass through the first compartment 1 and the top surface of the protective cover 3, and a limiting groove 40 is provided on the side wall of one end of the connecting piece 4 extending into the protective cover 3; the locking mechanism 5 is arranged in the protective cover 3, and the locking mechanism 5 includes a locking hook 51 and a locking piece 52, and the locking hook 51 is rotatably connected to the protective cover 3. The inner wall of the protective cover 3 is rotatably connected to the inner wall of the protective cover 3 through a pin shaft. One end of the locking hook 51 is bent to form a hook portion 511. The locking element 52 is movably arranged in the protective cover 3 and has a locking position and an unlocking position. When the locking element 52 is in the locking position, the locking element 52 abuts against the locking hook 51 to limit the rotation of the locking hook 51, and the hook portion 511 is inserted into the limiting groove 40. When the locking element 52 is in the unlocking position, it is separated from the first compartment 1 and the second compartment 2, and the connecting member 4 moves with the second compartment 2 and drives the locking hook 51 to rotate until the hook portion 511 is out of the limiting groove 40. By changing the locking member 52 between the locking position and the unlocking position, the locking member 52 can lock and release the restriction on the lock hook 51. When the locking member 52 is in the locking position, the locking member 52 resists the lock hook 51, so that the hook portion 511 at the end of the lock hook 51 is inserted into the limiting groove 40, and the connecting member 4 cannot move under the limiting action of the locking hook 51, that is, the connecting member 4 fixes the first compartment 1 and the second compartment 2 together; when the two compartments need to be separated, it is only necessary to move the locking member 52 to the unlocking position, the locking member 52 is away from the lock hook 51, and the lock hook 51 is not restricted by external force, that is, it can rotate freely. When the first compartment 1 and the second compartment 2 are separated, the second compartment 2 is pulled away from the connecting member 4, the connecting member 4 moves, and the lock hook 51 is rotated under force until the hook portion 511 is completely separated from the limiting groove 40, and the connecting member 4 is separated from the protective cover 3 and the first compartment 1 along with the second compartment 2, and the first compartment 1 and the second compartment 2 are separated smoothly. Under the above structure, the spacecraft interstage unlocking device can be reused and tested multiple times to ensure the reliability and accuracy of unlocking, and the unlocking structure is visible and measurable; and when unlocking and separating, it is only necessary to move the position of the lock member 52, and no additional driving mechanism is required to drive the lock hook 51 to rotate to disengage from the limit groove 40. The structure is relatively simple, the cost is low, and the probability of mechanical failure is low; at the same time, compared with the prior art that uses pyrotechnic devices to achieve unlocking and separation, the spacecraft interstage unlocking device uses pure mechanical means to achieve interstage unlocking and separation, which can effectively avoid the impact force or fragments generated during unlocking from causing impact and damage to other structures, and has a higher safety level.

[0033] In this embodiment, the connecting member 4 includes a connecting column and a nut. The connecting column movably passes through the first compartment 1, the second compartment 2 and the protective cover 3. An external thread is arranged on the outer periphery of one end of the connecting column. The nut is threadedly connected to the external thread and abuts against the second compartment 2. The above-mentioned limiting groove 40 is arranged on the outer periphery of the other end. After the connecting column passes through the first compartment 1, the second compartment 2 and the protective cover 3, the two ends are respectively limited and fixed by nuts and lock hooks 51, thereby realizing the connection between the first compartment 1 and the second compartment 2. When the first compartment 1 and the second compartment 2 are separated, the second compartment 2 is away from the first compartment 1, the lock hook 51 loses the limiting effect on the connecting column, the second compartment 2 drives the connecting column to move along the first direction, and the connecting column gradually separates from the protective cover 3 and the first compartment 1. Of course, in other embodiments, the connecting member 4 can also be connected to the second compartment 2 through other structures, for example, the connecting member 4 is welded to the second compartment 2 or clamped to the second compartment 2, which is specifically set according to actual needs.

[0034] Preferably, two locking hooks 51 are provided, and the two locking hooks 51 are relatively arranged on both sides of the connecting column. The outer periphery of the connecting column is provided with an annular limiting groove 40 or two limiting grooves 40 are relatively arranged on the outer periphery. Each locking hook 51 can be correspondingly inserted into a limiting groove 40. When the locking member 52 is in the locking position, it abuts between the two locking hooks 51, that is, the locking member 52 locks the two locking hooks 51 at the same time. The two symmetrically arranged locking hooks 51 make the connection stability between the connecting member 4 and the locking hooks 51 better, the force is more uniform, and the connection is more firm, so that the connection between the first compartment 1 and the second compartment 2 is more stable and reliable. Of course, in other embodiments, the number of locking hooks 51 can also be other, for example, three or four locking hooks 51 are arranged at intervals along the circumference, etc., which are specifically set according to actual needs.

[0035] Furthermore, the locking mechanism 5 further includes an elastic member 53, through which the locking member 52 is resettable and movable in the protective cover 3, and in the initial state of the elastic member 53, the locking member 52 is in the locking position. That is, the elastic member 53 provides a continuous and stable force for the locking member 52, so that the locking member 52 is always stable in the locking position, so that the first compartment 1 and the second compartment 2 are in a connected state in the initial state; when a force that overcomes the elastic member 53 is applied to the locking member 52, the locking member 52 moves away from the locking position, that is, the locking member 52 moves away from the locking hook 51, and the restriction on the locking hook 51 is cancelled, thereby achieving unlocking.

[0036] In one embodiment, the locking element 52 includes a locking rod 521 and a top block 522 located at one end of the locking rod 521. The top block 522 can be optionally threadedly connected to the locking rod 521 or integrally arranged. A limiting portion 523 is convexly provided on the outer periphery of the locking rod 521. The limiting portion 523 is located between the top block 522 and the bottom surface of the protective cover 3. The elastic member 53 is connected between the limiting portion 523 and the bottom surface of the protective cover 3. Under the elastic force of the elastic member 53, the locking element 52 has a tendency to move away from the bottom surface of the protective cover 3. The top block 522 abuts against one end of the locking hook 51 away from the hook portion 511, and the abutment between the hook portion 511 and the top block 522 against the locking hook 51 is located on the same surface of the locking hook 51. The elastic member 53 always exerts an upward thrust on the limiting portion 523, so that the locking rod 521 has an upward tendency, and the top block 522 supports the locking hook 51. Due to the limiting effect of the limiting groove 40, the locking hook 51 cannot continue to rotate in the direction of the limiting groove 40. Due to the limiting effect of the top block 522, and the locking hook 51 abuts against the side of the top block 522, the top block 522 is subjected to the force of the locking hook 51 perpendicular to the moving direction of the top rod. When the locking hook 51 is subjected to a large rotational force, it is not easy to push the locking rod 521 to cause self-unlocking, that is, the locking hook 51 cannot rotate in the direction away from the limiting groove 40, so as to achieve the locking of the locking hook 51 and the limiting groove 40. The elastic member 53 is preferably a compression spring. Of course, in other embodiments, the elastic member 53 can also be other structures, such as elastic rubber.

[0037] In order to further improve the stability of the lock 52, the inner wall of the protective cover 3 is formed with a step surface 311, which is arranged opposite to the bottom surface of the protective cover 3. When the lock 52 is in the locked position, the limit portion 523 abuts against the step surface 311. The setting of the step surface 311 limits the maximum extension or contraction distance of the elastic member 53, that is, ensures the distance between the limit portion 523 and the lock hook 51, so that the top block 522 is stabilized at a fixed point to provide a stable limiting force for the lock hook 51.

[0038] In another embodiment, the elastic member 53 is connected between the limiting portion 523 and the side wall or top surface of the protective cover 3 . The elastic member 53 may be a compression spring or a tension spring, as long as it can provide a force for the limiting portion 523 in a direction close to the locking hook 51 .

[0039] Preferably, a through hole is provided on the protective cover 3, for example, a through hole is provided on the bottom surface of the protective cover 3, and one end of the locking rod 521 away from the top block 522 is movable through the through hole. By extending the locking rod 521 out of the protective cover 3, it is convenient to manually or mechanically drive the locking rod 521 to move, so as to facilitate testing, etc. More preferably, a mounting hole is provided at the end of the locking rod 521 extending out of the protective cover 3, so as to facilitate the connection of a limit pin or other structure. The limit pin can limit the locking rod 521 from fully extending into the protective cover 3, and it is also convenient to apply force to pull the locking rod 521. In this embodiment, the protective cover 3 includes a shell 31 and a bottom end cover 32. One end of the shell 31 is open, and the other end is provided with a hole for the connector 4 to pass through. The bottom end cover 32 is detachably connected to the open end of the shell 31, so as to facilitate the disassembly and assembly of the locking mechanism 5.

[0040] Preferably, the end of the top block 522 facing away from the locking rod 521 is tapered. The tapered top block 522 facilitates the lock element 52 to smoothly push open the lock hook 51 when it moves from the locked position to the unlocked position, thereby pushing the lock hook 51 to rotate so that the hook portion 511 is inserted into the limit groove 40. The tapered top block 522 can prevent the top block 522 from getting stuck or stuck when contacting the lock hook 51, thereby improving the smoothness of locking.

[0041] More preferably, a roller 512 is rotatably provided at one end of the lock hook 51 away from the hook portion 511. When the lock member 52 moves from the unlocking position to the locking position, the lock member 52 pushes the roller 512 and drives the lock hook 51 to rotate. The setting of the roller 512 converts the sliding friction between the lock member 52 and the lock hook 51 into rolling friction, improves the smoothness of the top block 522 pushing the lock hook 51, and can effectively reduce wear. When the lock member 52 moves from the unlocking position to the locking position, the conical top of the top block 522 contacts the roller 512. As the lock rod 521 moves upward, the conical top block 522 moves upward and moves along the roller 512. The roller 512 rolls and the lock hook 51 rotates until the hook portion 511 is inserted into the limiting groove 40 and abuts against the bottom of the limiting groove 40.

[0042] Furthermore, a partition plate 33 is provided in the protective cover 3, and the partition plate 33 divides the protective cover 3 into a first cavity 301 and a second cavity 302 arranged along the axial direction of the protective cover 3. A guide hole 330 is opened on the partition plate 33, and the locking rod 521 seals and moves through the guide hole 330. The locking hook 51 is located in the first cavity 301, and the limiting portion 523 is located in the second cavity 302. The peripheral wall of the protective cover 3 is provided with a vent hole 303 connected with the second cavity 302, and the vent hole 303 is used to allow gas to pass. The vent hole 303 is preferably connected to the cylinder air inlet nozzle. The gas can push the limiting portion 523 to move toward the bottom surface of the protective cover 3 to drive the lock 52 to move from the locked position to the unlocked position. Among them, the lock rod 521 passes through the guide hole 330 in a sealed manner so that the first cavity 301 and the second cavity 302 are not connected to each other, so as to avoid leakage during inflation that affects the structure in the first cavity 301 or causes insufficient power. For example, the inner peripheral wall of the guide hole 330 is provided with a first sealing gasket 6 to ensure the sealing of the guide hole 330 when the lock rod 521 moves. When it is necessary to unlock and separate the first compartment 1 and the second compartment 2, it is only necessary to ventilate the second cavity 302 through the vent hole 303. The limiting part 523 overcomes the movement of the elastic part 53 under the action of air pressure, that is, the lock 52 moves. In this embodiment, the lock 52 moves downward, that is, the lock 52 is close to the bottom surface of the protective cover 3 and away from the lock hook 51. The lock 52 loses its limiting effect on the lock hook 51, and the second compartment 2 can move away from the first compartment 1, driving the connecting part 4 to move away from the protective cover 3 and the first compartment 1. With the movement of the connecting part 4, the lock hook 51 rotates until the hook 511 is separated from the limiting groove. Providing unlocking power through inflation saves complicated mechanical drive and transmission structures, making the internal structure of the spacecraft interstage unlocking device relatively simple and the overall volume smaller, thus reducing the possibility of mechanical failure.

[0043] Preferably, the peripheral wall of the limiting portion 523 is sealed to the inner wall of the protective cover 3, so that the limiting portion 523 is subjected to greater force during inflation to avoid wasting aerodynamic force or insufficient power. For example, a second sealing gasket 7 is provided on the outer peripheral ring of the limiting portion 523, so that the limiting portion 523 moves along the inner wall of the protective cover 3 while maintaining sealing.

[0044] The spacecraft interstage unlocking device provided in this embodiment is reusable, visible and measurable, and has a small impact load on the structure. It is also easy to change parameters to achieve interstage connections with different load-bearing capacities, such as replacing elastic parts 53 with different elastic forces, different types of locking hooks 51, and disassembly and assembly of rollers 512.

[0045] This embodiment also provides a spacecraft, which includes the above-mentioned spacecraft inter-stage unlocking device, which can quickly and effectively achieve unlocking and separation between spacecraft cabins with high separation safety.

[0046] Note that the above are only preferred embodiments of the present invention and the technical principles used. Those skilled in the art will understand that the present invention is not limited to the specific embodiments described herein, and that various obvious changes, readjustments and substitutions can be made by those skilled in the art without departing from the scope of protection of the present invention. Therefore, although the present invention has been described in more detail through the above embodiments, the present invention is not limited to the above embodiments, and may include more other equivalent embodiments without departing from the concept of the present invention, and the scope of the present invention is determined by the scope of the appended claims.

Claims

1. A spacecraft interstage unlocking device, wherein one of the two compartments to be separated is a first compartment and the other is a second compartment, characterized in that: The spacecraft interstage unlocking device comprises: Protective cover; A connecting piece, the connecting piece sequentially passes through the second compartment and moves through the first compartment and the top surface of the protective cover, and a side wall of one end of the connecting piece extending into the protective cover is provided with a limiting groove; A locking mechanism is arranged in the protective cover, and the locking mechanism includes a locking hook and a locking element. The locking hook is rotatably connected to the inner wall of the protective cover, one end of the locking hook is bent to form a hook portion, and the locking element is movably arranged in the protective cover and has a locking position and an unlocking position. When the locking element is in the locking position, the locking element abuts against the locking hook to limit the rotation of the locking hook, and the hook portion is inserted into the limiting groove. When the locking element is in the unlocking position, the first compartment section and the second compartment section are separated, and the connecting element moves with the second compartment section and drives the locking hook to rotate until the hook portion is separated from the limiting groove.

2. The spacecraft interstage unlocking device according to claim 1, characterized in that: The locking mechanism further comprises an elastic member, through which the locking member is resettable and movable in the protective cover. In the initial state of the elastic member, the locking member is located at the locking position.

3. The spacecraft interstage unlocking device according to claim 2, characterized in that: The locking element includes a locking rod and a top block located at one end of the locking rod, a limiting portion is convexly provided on the outer periphery of the locking rod, the limiting portion is located between the top block and the bottom surface of the protective cover, the elastic element is connected between the limiting portion and the bottom surface of the protective cover, and under the elastic force of the elastic element, the locking element has a tendency to move away from the bottom surface of the protective cover, and the top block abuts against one end of the locking hook away from the hook portion.

4. The spacecraft interstage unlocking device according to claim 3, characterized in that: The inner wall of the protective cover is formed with a step surface, and the step surface is arranged opposite to the bottom surface of the protective cover. When the locking element is located at the locking position, the limiting portion abuts against the step surface.

5. The spacecraft interstage unlocking device according to claim 3, characterized in that: A partition plate is provided in the protective cover, and the partition plate divides the protective cover into a first cavity and a second cavity arranged along the axial direction of the protective cover. A guide hole is provided on the partition plate, and the locking rod seal moves through the guide hole. The locking hook is located in the first cavity, and the limiting portion is located in the second cavity. A vent hole connected to the second cavity is provided on the peripheral wall of the protective cover, and the vent hole is used to allow gas to pass. The gas can push the limiting portion to move toward the bottom surface of the protective cover to drive the locking element to move from the locked position to the unlocked position.

6. The spacecraft interstage unlocking device according to claim 5, characterized in that: The outer periphery of the limiting portion is sealed and connected to the inner wall of the protective cover.

7. The spacecraft interstage unlocking device according to any one of claims 3 to 6, characterized in that: One end of the top block facing away from the locking rod is tapered.

8. The spacecraft interstage unlocking device according to any one of claims 3 to 6, characterized in that: A through hole is formed on the bottom surface of the protective cover, and one end of the locking rod facing away from the top block movably passes through the through hole.

9. The spacecraft interstage unlocking device according to claim 1, characterized in that: A roller is rotatably provided at one end of the lock hook away from the hook portion. When the lock element moves from the unlocking position to the locking position, the lock element pushes the roller and drives the lock hook to rotate.

10. A spacecraft, characterized in that: Comprising the spacecraft interstage unlocking device as described in any one of claims 1-9.

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