A two-stage orbit transfer vehicle inter-stage active unlocking and separation device

Abstract

The present invention discloses an active unlocking and separating device for the stage separation of a two-stage orbital vehicle, belonging to the technical field of aerospace vehicles, and includes two sets of intra-group synchronous unlocking and separating mechanisms and a separating deck inside the stage separation device of the two-stage orbital vehicle. The separating deck is fixedly connected with the two sets of intra-group synchronous unlocking and separating mechanisms inside, and its lower part is fixedly connected to the separating platform of the first-stage vehicle in the two-stage orbital vehicle. The intra-group synchronous unlocking and separating mechanism is driven by a driving motor to rotate a transmission shaft, and a turntable cooperating with the transmission shaft also rotates with the rotation of the transmission shaft. The big ends of four connecting rods cooperate with the cylinders on the turntable, and at the same time, the small ends of the connecting rods cooperate with the separating pins through pin shafts. The separating pins slide in the flanged linear bearings under the drive of the connecting rods. When the separating pins completely return to the inside of the separating deck, the separation of the separating device from the second-stage vehicle is completed. The present invention can achieve the intra-group synchronous unlocking and separation of the two-stage orbital vehicle between stages and non-explosive work for the two sets in the front and back.

Description

Technical Field

[0001] The present invention relates to the technical field of aerospace vehicles, and particularly to an active unlocking and separating device between stages of a two-stage orbital vehicle. Background Art

[0002] Since the 21st century, countries around the world have regarded space as a major national strategic field, continuously exploring unknown basic sciences in the aerospace field, enhancing technological innovation capabilities, and promoting the continuous development of technologies in the aerospace flight field. An aerospace vehicle refers to a reusable vehicle that can freely travel back and forth between the dense atmosphere, near space, and orbital space, breaking through the limitations of traditional spacecraft and aircraft, achieving free shuttle flight in the atmosphere and space, and possessing advantages such as low cost, convenience, safety, and mobility.

[0003] Under this demand, two-stage orbital vehicles have emerged as the times require. By using a first-stage vehicle to send a second-stage vehicle to an orbit at a certain altitude, and then separating the first-stage vehicle from the second-stage vehicle, the second-stage vehicle can carry more fuel to improve its endurance function. Among them, how the first-stage vehicle and the second-stage aerospace vehicle separate after reaching the specified altitude has become one of the key technical difficulties.

[0004] Currently, the most widely used and technically mature separation device is the pyrotechnic clamping and releasing device, including explosive bolts, steel ball bolts, pull pins, cutters, unlocking nuts, straps, pyrotechnic connection locks, pyrotechnic separation push rods, etc. However, since the pyrotechnic device will generate a huge pyrotechnic impact during separation, it will affect the attitude of the two-stage orbital vehicle flying at hypersonic speed. At the same time, it will also cause the initial attitude of the second-stage vehicle to be disordered after separation. In addition, using a pyrotechnic device for separation will generate polluting gases and cannot be reused. In order to reduce pollution and achieve the function of reuse, this has put forward new requirements for a new type of non-pyrotechnic separation device.

[0005] For a vehicle flying at hypersonic speed, in order to ensure good aerodynamic characteristics of the second-stage vehicle in the initial state after separation, it is necessary to ensure the synchronization between the separation mechanism and the second-stage vehicle during separation. In a real working environment, the length of the second-stage vehicle is generally about several meters to 20 meters. If multiple sets of pyrotechnic clamping and releasing devices are used for inter-stage separation between the first-stage vehicle and the second-stage vehicle, it is inevitable that all release devices cannot be released at the same time, ultimately affecting the stability of the air attitude of the second-stage vehicle after separation from the first-stage vehicle.

[0006] To solve this problem, from the perspective of mechanism design, the present invention adopts a front and rear intra-group synchronous unlocking and separation mechanism to achieve stable separation between the second-stage aircraft and the first-stage aircraft. The advantage of this is that if the two-stage orbital aircraft can achieve ideal front and rear inter-group synchronous separation, then the mutual influence between the first-stage aircraft and the second-stage aircraft after separation will be minimized; even if the inter-group synchronous separation cannot be fully achieved, the impact on the second-stage aircraft is only an increase in the angle of attack. Through research on the literature, it can be known that an increase in the angle of attack can increase the aerodynamic lift received by the second-stage aircraft, which is beneficial to the separation of the second-stage aircraft from the first-stage aircraft. Summary of the Invention

[0007] The purpose of the present invention is to solve the problems in the above-mentioned background technology, and propose an active unlocking and separation device for the inter-stage of a two-stage orbital aircraft. This device can achieve non-explosive front and rear intra-group synchronous separation between the first-stage aircraft and the second-stage aircraft after reaching the specified altitude, enabling the second-stage aircraft to have a good initial flight attitude after separation from the first-stage aircraft. Moreover, the non-explosive separation method effectively reduces the impact force generated during the separation of the second-stage aircraft and the first-stage aircraft, ensuring the stability of the entire separation process.

[0008] The present invention is implemented as follows:

[0009] An active unlocking and separation device for the inter-stage of a two-stage orbital aircraft, characterized in that the device includes a separation deck (3), and an intra-group synchronous unlocking and separation mechanism (4) is arranged inside the separation deck (3) in the front and rear directions;

[0010] The lower end of the described separation deck (3) is fixedly connected to the separation platform (1) of one stage of the two-stage orbital vehicle; each of the two sets of in-group synchronous unlocking and separation mechanisms (4) includes a number of flanged linear bearings (6), a turntable (15), a separation pin (10), a transmission shaft (9), a driving motor (16) and a connecting rod (11); the flanged linear bearings (6) are installed on the separation deck (3), and are circumferentially distributed on the turntable (15) through the separation pins (10) and the connecting rods (11). The transmission shaft (9) is located at the center of the turntable (15). The separation pins (10) are provided at the ends of the flanged linear bearings (6). The turntable (15) is integrally located on the driving motor (16); the head of the separation pin (10) includes a separation pin cylindrical structure and a spherical structure (20) on the outer end face of the separation pin; the spherical structure (20) on the outer end face of the separation pin is fully meshed with the locking of the second-stage vehicle (2), restricting the relative movement between the first-stage vehicle and the second-stage vehicle (2), and realizing the fixing effect of the separation device on the second-stage vehicle (2) before separation; a part of the separation pin cylindrical structure (21) is matched with the flanged linear bearing (6) and slides in the linear bearing. Another part of the separation pin cylindrical structure (21) is matched with the second-stage vehicle (2).

[0011] The tail of the separation pin (10) passes through the flanged linear bearing (6) and is matched with one end of the connecting rod (11); the other end of the connecting rod (11) is matched with the boss on the turntable (15). The movement of the connecting rod (11) is driven by the rotation of the turntable (15). According to the crank-slider principle, the connecting rod (11) drives the separation pin (10) to contract in the flanged linear bearing (6), so as to realize the unlocking and separation between the first-stage vehicle and the second-stage vehicle (2).

[0012] The separation device of the present invention separates in a non-explosive way, significantly reducing the large overload impact generated during separation, eliminating the safety problems, harmful gases and threats to the structural safety of the vehicle body brought by explosive combustion substances such as gunpowder, and can be reused multiple times. By adopting two sets of in-group synchronous unlocking and separation mechanisms, the synchronism and stability during the separation of the second-stage vehicle and the first-stage vehicle are realized, providing a good initial flight attitude for the second-stage vehicle. The advantage of adopting two sets of in-group synchronous unlocking and separation mechanisms is that if the two-stage orbital vehicle can achieve ideal in-group synchronous separation between the front and rear groups, then the mutual influence between the first-stage vehicle and the second-stage vehicle after separation will be minimized; even if the in-group synchronous separation cannot be completely achieved, the influence on the second-stage vehicle is only an increase in the angle of attack, and the increase in the angle of attack can increase the aerodynamic lift received by the second-stage vehicle, which is beneficial to the separation of the second-stage vehicle from the first-stage vehicle.

[0013] 4. The principle of the synchronous unlocking and separation mechanism within the group is the crank slider principle. Four non-uniformly distributed crank slider mechanisms are used to drive the separation pin to move inside the linear bearing. From the perspective of mechanism design, it realizes synchronous unlocking and separation within the group, and helps to ensure that the transmission angle of the drag force of the crank slider mechanism to drag the pin column back during unlocking is always in a good working condition.

[0014] The separation pin is retracted in the linear bearing, and its outer end face is a spherical structure. When the pin is retracted to the point where only its spherical end face is in a hole-shaft matching state with the secondary aircraft, the secondary aircraft, which has been lifted and raised relative to the first aircraft, has a tendency to separate from the first aircraft under the action of the large lift force that has been obtained. At this time, the second aircraft will squeeze the spherical end face of the pin during the rising and separation process relative to the first aircraft, causing the pin to passively retract, effectively avoiding the instability of the separation posture of the first aircraft and the second aircraft in the final stage of separation (i.e., the stage where only the spherical end face of the pin is matched with the second aircraft), so that the unlocking and releasing process is smoother and more stable. There is a compression spring between the separation pin and the crank slider transmission rod, and its elastic stiffness is specially designed so that the compression spring can only be squeezed and retracted when the second aircraft has an active upward and detaching tendency relative to the first aircraft, and any disturbance in the flight stage before separation (including the lifting and raising stage of the second aircraft relative to the first aircraft) will not cause it to retract, ensuring the safety of the flight process.

[0015] Furthermore, the connecting rods (11) are arranged in four groups, which are circumferentially distributed on the turntable (15).

[0016] Furthermore, one end of the connecting rod (11) is a small end of the connecting rod (12) and a pin (17); the tail of the separation pin (10) passes through a flanged linear bearing (6) and is matched with the pin (17) and the small end of the connecting rod (12) at one end of the connecting rod (11) through a compression spring (7); the other end of the connecting rod (11) is a large end of the connecting rod (13), which is matched with a boss on the turntable (15) through the large end of the connecting rod (13).

[0017] Furthermore, the flanged linear bearing (6) is fixed to the separation deck by bolts (8), thereby reducing the friction of the separation pin (10) during movement, thereby achieving smooth movement with high sensitivity and high precision; the separation pin (10) cooperates with the flanged linear bearing (6); and a circle of strip-shaped solid self-lubricating material is embedded on the inner wall of the flanged linear bearing (6) for lubricating the separation pin (10).

[0018] Furthermore, the turntable (15) is provided with a limit groove (5) to prevent the turntable (15) from rotating excessively during operation; the turntable (15) is connected to the transmission shaft (9) through a flat key (18). The turntable (15) has a hub and the transmission shaft (9) has a shaft groove. Torque is transmitted through the contact between the side surfaces of the flat key (18) and the side surfaces of the shaft groove and the hub groove; a bushing (14) is provided at the end of the transmission shaft (9), and the bushing (14) is fitted with the transmission shaft (9) through a positioning pin (19) to prevent the turntable (15) from shifting during rotation.

[0019] Furthermore, the transmission shaft (9) is driven to rotate by a driving motor (16), and the driving motor (16) serves as the power system of the entire in-group synchronous unlocking and separation mechanism (4) to provide a power source for the separation device.

[0020] Furthermore, the secondary aircraft (2) is fitted with a spherical structure (20) on the outer end face of the separation pin and a part of the cylindrical structure (21) of the separation pin to mutually restrain before the separation of the primary aircraft and the secondary aircraft; when the separation of the primary aircraft and the secondary aircraft begins, the separation pin (10) starts to retract under the drive of the connecting rod (11). When the separation pin (10) retracts to a certain position, that is, when only the spherical structure (20) on the outer end face of the separation pin cooperates with the secondary aircraft (2), the secondary aircraft has a tendency to fly away from the primary aircraft under the action of the obtained lift. At this time, the spherical structure (20) on the outer end face of the separation pin will be axially pressured under the upward separation movement of the secondary aircraft (2) relative to the primary aircraft. The compression spring (7) is compressed and shortened after being pressured, and the separation pin (10) is passively retracted for the last remaining part.

[0021] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0022] The present invention provides an in-orbit aircraft inter-stage active unlocking and separation device with a simple structure, easy control, and strong applicability.

[0023] The entire separation device uses a non-explosive method for separation, significantly reducing the impact force generated during separation, eliminating the safety problems and harmful gases brought by explosive combustion substances such as gunpowder, and enabling multiple reuse.

[0024] By adopting two sets of in-group synchronous unlocking and separation mechanisms, the synchronism and stability during the separation of the secondary aircraft and the primary aircraft are achieved, providing a good initial flight attitude for the secondary aircraft.

[0025] The advantage of adopting the front and rear sets of in-group synchronous unlocking and separating mechanisms is that if the two-stage orbital vehicle can achieve ideal in-group synchronous separation between the front and rear sets, then the mutual influence between the first-stage vehicle and the second-stage vehicle after separation will be minimized; even if the in-group synchronous separation cannot be fully achieved, the influence on the second-stage vehicle is only an increase in the angle of attack, and the increase in the angle of attack can increase the aerodynamic lift received by the second-stage vehicle, which is beneficial to the separation of the second-stage vehicle from the first-stage vehicle.

[0026] The principle of the in-group synchronous unlocking and separating mechanism is the crank-slider principle. Four crank-slider mechanisms with non-uniform distribution are used to drive the separating pin to move inside the linear bearing. When the in-group synchronous unlocking and separating mechanism works, the greater the centripetal retraction tension on the separating pin, the better, that is, the greater the transmission angle ( α , β ), the better the force transmission performance of the mechanism. To achieve this goal, a non-uniform distribution design is adopted for the four crank-slider mechanisms in the in-group synchronous unlocking and separating mechanism. At the same time, the four crank-slider mechanisms can be divided into two groups according to the working conditions of the transmission angle ( α , β ), realizing in-group synchronous unlocking and separating from the perspective of mechanism design.

[0027] The separating pin expands and contracts in the linear bearing, and the outer end face of the separating pin is spherical. Such a design can effectively avoid the friction generated at the contact part between the separating pin and the first-stage vehicle when the first-stage vehicle and the second-stage vehicle are separated, and it is smooth, stable and highly reliable during unlocking and release. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 It is a schematic diagram of the overall structure of a device for inter-stage separation of a two-stage orbital vehicle according to the present invention;

[0029] Figure 2 It is a schematic diagram of the overall structure of a device for inter-stage separation of a two-stage orbital vehicle applicable to a two-stage orbital vehicle according to the present invention;

[0030] Figure 3 It is a schematic diagram of the overall structure of the in-group synchronous unlocking and separating mechanism of a device for inter-stage separation of a two-stage orbital vehicle according to the present invention;

[0031] Figure 4 It is a schematic diagram of the structure of the separation deck, the linear bearing with flange and the separating pin of the in-group synchronous unlocking and separating mechanism of a device for inter-stage separation of a two-stage orbital vehicle according to the present invention;

[0032] Figure 5Schematic structural diagram of the cooperation of the separation pin, pin shaft, connecting rod, turntable, etc. of the in-group synchronous unlocking and separating mechanism of a two-stage orbit transfer vehicle stage separation device according to the present invention;

[0033] Figure 6 Schematic structural diagram of the cooperation of the turntable, drive motor, transmission shaft, elastic retaining ring, etc. of the in-group synchronous unlocking and separating mechanism of a two-stage orbit transfer vehicle stage separation device according to the present invention;

[0034] Figure 7 Schematic state diagram of the in-group synchronous unlocking and separating mechanism of a two-stage orbit transfer vehicle stage separation device according to the present invention when starting passive retraction.

[0035] Wherein, 1 - separation platform of the first-stage vehicle, 2 - second-stage vehicle, 3 - separation deck, 4 - in-group synchronous unlocking and separating mechanism, 5 - limit groove, 6 - flanged linear bearing, 7 - compression spring, 8 - bolt, 9 - transmission shaft, 10 - separation pin, 11 - connecting rod, 12 - small end of the connecting rod, 13 - large end of the connecting rod, 14 - bushing, 15 - turntable, 16 - drive motor, 17 - pin shaft, 18 - flat key, 19 - positioning pin, 20 - spherical structure of the outer end face of the separation pin, 21 - cylindrical structure of the separation pin. Embodiment

[0036] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without making creative efforts shall fall within the protection scope of the present invention.

[0037] As Figure 1 shown, the present invention is a two-stage orbit transfer vehicle stage active unlocking and separating device, which is composed of a separation deck 3 and two sets of in-group synchronous unlocking and separating mechanisms 4 before and after.

[0038] As Figure 2 shown, the two sets of in-group synchronous unlocking and separating mechanisms 4 are fixedly connected inside the separation deck 3, and the separation deck 3 is fixedly connected below to the separation platform 1 of the first-stage vehicle of the two-stage orbit transfer vehicle.

[0039] As Figures 3 - 4As shown in the figure, the in-group synchronous unlocking and separating mechanism 4 includes a flanged linear bearing 6, a turntable 15, a connecting rod 11, a separating pin 10, a transmission shaft 9, and a driving motor 16. The flanged linear bearing 6 is fixedly connected to the separating deck by bolts 8 to reduce the friction generated when the separating pin 10 moves, and achieve smooth movement with high sensitivity and high precision. A part of the cylindrical structure 21 of the separating pin is matched with the flanged linear bearing 6 and slides within the linear bearing. A ring of strip-shaped solid self-lubricating material is inlaid on the inner wall of the flanged linear bearing 6 to lubricate the separating pin 10. Another part of the cylindrical structure of the separating pin is matched with the secondary aircraft 2. The spherical structure 20 on the outer end face of the separating pin is fully engaged with the locking of the secondary aircraft 2 to restrict the relative movement of the secondary aircraft 2, and realize the fixing effect of the separating device on the secondary aircraft 2 before separation.

[0040] As Figure 5 shown, the tail of the separating pin 10 is matched with the pin shaft 17 and the small end 12 of the connecting rod. The big end 13 of the connecting rod is matched with the boss on the turntable 15. By rotating the turntable 15, the movement of the connecting rod 11 is driven. According to the crank-slider principle, the connecting rod 11 drives the separating pin 10 to contract within the flanged linear bearing 6, so as to realize the unlocking and separation between the primary aircraft and the secondary aircraft 2.

[0041] As Figure 6 shown, the turntable 15 is provided with a limit groove 5, which can prevent the turntable from rotating excessively during operation. The turntable 15 and the transmission shaft 9 are connected by a flat key 18. The turntable 15 has a hub and the transmission shaft 9 has a shaft groove. The torque is transmitted through the contact between the side surface of the flat key 18 and the side surfaces of the shaft groove and the hub groove. A bushing 14 is arranged at the end of the transmission shaft 9. The bushing 14 is matched with the transmission shaft 9 through a positioning pin 19 to prevent the turntable 15 from generating offset during rotation. The transmission shaft 9 is driven to rotate by the driving motor 16. The driving motor 16 serves as the power system of the entire in-group synchronous unlocking and separating mechanism 4 to provide a power source for the separating device.

[0042] As Figure 7 shown, when the separating pin 10 retracts in the flanged linear bearing 6 until only the spherical structure 20 on the outer end face of the separating pin is matched with the secondary aircraft 2, the secondary aircraft 2 has a tendency to fly away from the primary aircraft under the action of the obtained lift. At this time, the spherical structure 20 on the outer end face of the separating pin will be subjected to an axial pressure under the upward movement of the secondary aircraft 2 relative to the primary aircraft. The compression spring 7 is compressed and shortened after being subjected to the pressure, and the separating pin 10 is passively retracted for the last remaining part.

[0043] The above are only the preferred embodiments of the present invention. It should be noted that for those of ordinary skill in the art, several improvements can be made without departing from the principle of the present invention, and these improvements should also be regarded as the protection scope of the present invention.

Claims

1. A two-stage orbital vehicle inter-stage active unlocking and separation device, characterized in that The described device includes a separation deck (3) with an in-group synchronous unlocking and separating mechanism (4) arranged inside it from front to back; the lower end of the separation deck (3) is fixedly connected to the separation platform (1) of the first-stage aircraft in a two-stage orbital aircraft; both of the two sets of in-group synchronous unlocking and separating mechanisms (4) include a flanged linear bearing (6), a turntable (15), a separating pin (10), a transmission shaft (9), a driving motor (16), and a connecting rod (11); the flanged linear bearing (6) is installed on the separation deck (3), and the connecting rods (11) are circumferentially distributed on the turntable (15) through the separating pins (10). The transmission shaft (9) is located at the center of the turntable (15). The separating pin (10) is provided at the end of the flanged linear bearing (6), and the turntable (15) is entirely located on the driving motor (16); the head of the separating pin (10) includes a separating pin cylindrical structure and a spherical structure (20) on the outer end face of the separating pin; the spherical structure (20) on the outer end face of the separating pin is fully engaged with the locking of the second-stage aircraft (2), restricting the relative movement between the first-stage aircraft and the second-stage aircraft (2), and realizing the fixing effect of the separating device on the second-stage aircraft (2) before separation; a part of the separating pin cylindrical structure (21) cooperates with the flanged linear bearing (6) and slides within the linear bearing, and another part of the separating pin cylindrical structure (21) cooperates with the second-stage aircraft (2); the tail of the separating pin (10) passes through the flanged linear bearing (6) and cooperates with one end of the connecting rod (11); the other end of the connecting rod (11) cooperates with the boss on the turntable (15). By rotating the turntable (15), the movement of the connecting rod (11) is driven. According to the crank-slider principle, the connecting rod (11) drives the separating pin (10) to contract within the flanged linear bearing (6), so as to realize the unlocking and separation between the first-stage aircraft and the second-stage aircraft (2).

2. The active unlocking and separating device between stages of a two-stage orbital vehicle according to claim 1, characterized in that, The connecting rods (11) are provided in four groups and are circumferentially evenly distributed on the turntable (15).

3. The active unlocking and separation device between stages of a two-stage orbital vehicle according to claim 1, characterized in that, One end of the connecting rod (11) is the small end (12) of the connecting rod and a pin shaft (17); the tail of the separating pin (10) passes through the flanged linear bearing (6) and cooperates with the pin shaft (17) and the small end (12) of the connecting rod at one end of the connecting rod (11) through a compression spring (7); the other end of the connecting rod (11) is the large end (13) of the connecting rod, and it cooperates with the boss on the turntable (15) through the large end (13) of the connecting rod.

4. A two-stage orbit vehicle inter-stage active unlocking and separation device according to claim 3, characterized in that, The turntable (15) is provided with a limiting groove (5) to prevent the turntable (15) from rotating excessively during operation; the turntable (15) and the transmission shaft (9) are connected by a flat key (18). The turntable (15) has a hub and the transmission shaft (9) has a shaft groove. Torque is transmitted through the side surfaces of the flat key (18) contacting the side surfaces of the shaft groove and the hub groove; a bushing (14) is provided at the end of the transmission shaft (9), and the bushing (14) cooperates with the transmission shaft (9) through a positioning pin (19) to prevent the turntable (15) from shifting during rotation.

5. A two-stage orbit transfer vehicle inter-stage active unlocking and separation device according to claim 1, characterized in that, The described flanged linear bearing (6) is fixed to the separation deck by bolts (8), reducing the frictional force of the separation pin (10) during movement and achieving smooth movement with high sensitivity and high precision; the separation pin (10) cooperates with the flanged linear bearing (6); a ring of strip-shaped solid self-lubricating material is inlaid on the inner wall of the flanged linear bearing (6) to lubricate the separation pin (10).

6. The active unlocking and separation device between stages of a two-stage orbital vehicle according to claim 1, characterized in that, The described transmission shaft (9) is driven to rotate by a drive motor (16), and the drive motor (16) serves as the power system of the synchronous unlocking separation mechanism (4) within the entire group to provide a power source for the separation device.

7. A two-stage orbital vehicle inter-stage active unlocking and separation device according to claim 1, characterized in that, The described secondary aircraft (2) cooperates with a part of the spherical structure (20) on the outer end face of the separation pin and the cylindrical structure (21) of the separation pin to mutually restrain before the separation of the primary aircraft and the secondary aircraft; the separation pin (10) starts to retract under the drive of the connecting rod (11) when the primary aircraft and the secondary aircraft begin to separate. When the separation pin (10) retracts to a certain position, that is, when only the spherical structure (20) on the outer end face of the separation pin cooperates with the secondary aircraft (2), the secondary aircraft has a tendency to fly away from the primary aircraft under the action of the obtained lift. At this time, the spherical structure (20) on the outer end face of the separation pin will be subjected to an axial pressure under the upward separation movement of the secondary aircraft (2) relative to the primary aircraft. After the compression spring (7) is subjected to the pressure, it is compressed and shortened, and the separation pin (10) is driven to complete the retraction of the remaining part passively.

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