Adjustable locking and releasing mechanism for spacecraft

Abstract

A spacecraft adjustable locking and releasing mechanism includes a shaft system, a pin puller locking sleeve, a pyrotechnic pin puller, an adjusting assembly, a pin puller pressing sleeve and a base; the relative position between the pyrotechnic pin puller and the shaft system can be adjusted by the adjusting assembly, and the pyrotechnic pin puller presses against the shaft system after the adjusting assembly applies a specified preload, thereby realizing the locking function of the spacecraft launch section; the adjusting assembly is rotated in the opposite direction to realize the manual unlocking function on the ground; after the spacecraft enters orbit, the pin puller igniter is detonated, and the high-temperature and high-pressure gas generated pushes the pin puller piston to move, overcoming the friction force while cutting off the locking pin, and the piston retracts into the pin puller body, thereby realizing the function of releasing the shaft system. The present invention can lock when the shaft system is in an orthogonal retracted state, reducing the overall range envelope of the spacecraft, which is conducive to the spacecraft system to coordinate the position planning of each single machine; the unlocking and releasing function relies on the pyrotechnic pin puller to cut off the locking pin, does not rely on other auxiliary parts, and has a high degree of reliability.

Description

Technical Field

[0001] The invention relates to an adjustable locking and releasing mechanism for a spacecraft, belonging to the field of aerospace electromechanical technology. Background Art

[0002] The pointing mechanism is an important executive component of the satellite antenna to achieve target capture and tracking, inter-satellite and ground signal transmission, and is an indispensable part of the spacecraft system. The spacecraft is subject to harsh environmental conditions during the launch phase and is subject to large vibration and shock. In order to ensure the reliable driving and high-precision directional function of the pointing mechanism after entering orbit, the method of relying solely on the holding torque of the motor to keep the pointing mechanism in a fixed position has low reliability. Therefore, a mechanism is needed to achieve locking during the launch phase and release after entering orbit. The existing locking and releasing mechanism arranges the corresponding installation interface on the satellite antenna, rotates it to the extreme position to lock it, greatly increases the overall envelope size of the pointing mechanism, and causes certain difficulties for the spacecraft system to coordinate the arrangement of each single machine position. In addition, weight is an important assessment indicator of the spacecraft system. The added locking and releasing mechanism requires a structure that is not too complicated and easy to operate. In view of the existing problems of the above locking and releasing mechanism, a safe, reliable and easy-to-operate locking and releasing mechanism is needed to achieve the functions of locking during the launch phase of the spacecraft and releasing after entering orbit. Summary of the invention

[0003] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art and to propose an adjustable locking and releasing mechanism for a spacecraft, which is safe, reliable, and easy to operate, and can realize the functions of locking the launch stage of the spacecraft and releasing it after entering orbit.

[0004] The technical solution of the present invention is:

[0005] An adjustable locking and releasing mechanism for a spacecraft includes: a shaft system, a locking sleeve of a pin puller, a pyrotechnic pin puller, an adjusting assembly, and a base;

[0006] A mounting hole is machined on the shaft system, and the pin puller locking sleeve is connected to the internal thread of the shaft system mounting hole through an external thread;

[0007] The pyrotechnic pin puller comprises a piston, a locking pin, a body, an igniter and a plug cover; a cavity is processed inside the body, the piston is installed in the cavity, the locking sleeve of the pin puller has a conical hole inside, the conical head of the piston is inserted into the conical hole of the locking sleeve of the pin puller, and the bottom of the cavity is sealed by the plug cover; an igniter is installed on the side wall of the body, and the outlet of the igniter is connected to the cavity; a groove is processed on the upper part of the piston, a locking pin mounting hole is processed on the upper side wall of the body, and the locking pin passes through the locking pin mounting hole and is inserted into the groove processed on the upper part of the piston;

[0008] The bottom of the body is installed on the adjusting assembly, and the adjusting assembly is installed on the base; the adjusting assembly can adjust the relative position between the pyrotechnic pin puller and the shaft system, and apply a positive pre-tightening force to the adjusting assembly to make the pyrotechnic pin puller press against the shaft system to realize the locking function of the spacecraft launch section; apply a reverse force to the adjusting assembly, and the pyrotechnic pin puller and the pin puller locking sleeve are separated to realize the manual unlocking and releasing function on the ground; after the spacecraft enters orbit, the igniter is detonated, and the high-temperature and high-pressure gas generated pushes the piston to move upward, overcoming the friction while cutting off the locking pin, and the piston retracts into the body, thereby realizing the function of releasing the shaft system.

[0009] Preferably, the adjustment assembly includes an adjustment tray, a thin nut, and a fixing nut;

[0010] The fixing nut is fixed on the base, the upper part of the adjusting tray is a disc and the lower part is a threaded section, and the thin nut is installed on the threaded section;

[0011] Rotate the adjustment tray into the fixing nut. The adjustment tray can move up and down on the fixing nut through the thread. Before installing the pyrotechnic pin puller, ensure that the distance between the upper surface of the adjustment tray and the pin puller locking sleeve is greater than the total length of the pyrotechnic pin puller to ensure the installation space of the pyrotechnic pin puller.

[0012] Preferably, the thin nut is connected to the adjustment tray by threads, and before adjustment, the thin nut is rotated until its upper surface is 2 mm away from the lower surface of the disc, thereby ensuring a certain adjustment margin for the adjustment component.

[0013] Preferably, the adjustment assembly further comprises two pin puller compression sleeves;

[0014] Two pin puller clamping sleeves are fixed on the base. After the adjustment assembly adjusts the relative position between the pyrotechnic pin puller and the shaft system to the right position, the two pin puller clamping sleeves hold the pyrotechnic pin puller from both sides, so that the piston head of the pyrotechnic pin puller is aligned with the installed pin puller locking sleeve hole on the shaft system, and the pyrotechnic pin puller is reliably fitted to maintain the centering state;

[0015] At the same time, the pin puller clamping sleeve holds the pyrotechnic pin puller tightly to ensure that the pyrotechnic pin puller is always in a fixed state after being unlocked in orbit.

[0016] Preferably, the material of the thin nut is 2Gr13 stainless steel with a thickness of 5 mm. The internal thread of the thin nut cooperates with the threaded section of the adjustment tray to have the function of tightening and preventing loosening.

[0017] Preferably, the material of the adjustment tray is titanium alloy.

[0018] Preferably, the material of the fixing nut is titanium alloy.

[0019] The locking and releasing method of the adjustable locking and releasing mechanism of a spacecraft comprises:

[0020] By rotating the adjustment tray forward, the adjustment tray is pressed against the tail of the pyrotechnic pin puller, and the pyrotechnic pin puller is in a tightened state. Then, use an open-end torque wrench to apply a torque of 8±0.5Nm on the adjustment tray, so that the pyrotechnic pin puller is completely tightened.

[0021] Use an adjustable spanner to apply a preload of 15±0.5Nm to the thin nut, and completely tighten the thin nut and the fixed nut on the adjustment tray. The lower surface of the thin nut overlaps with the upper surface of the fixed nut to achieve locking and anti-loosening between the thin nut and the adjustment tray, and prevent the preload from changing due to thread loosening under the action of the mechanical environment.

[0022] The two pin puller clamping sleeves hold the pyrotechnic pin puller tightly from both sides, so that the piston head of the pyrotechnic pin puller is aligned with the installed pin puller locking sleeve hole on the shaft system, and make it fit reliably and maintain the centering state;

[0023] When manually unlocking on the ground, loosen the pin puller compression sleeve, first use an adjustable wrench to reversely rotate the thin nut until the upper surface is 2mm away from the lower surface of the disc, then use an open-end torque wrench to reversely rotate the adjustment tray, and the pyrotechnic pin puller moves downward with the adjustment tray to disengage from the pin puller locking sleeve, thereby realizing the manual unlocking function;

[0024] After the spacecraft enters orbit, the igniter explodes, and the high-temperature and high-pressure gas generated pushes the piston to move, overcoming the friction and cutting off the locking pin. The piston retracts into the body, and the pin puller loses connection with the shaft system, thereby achieving the function of releasing the shaft system.

[0025] The beneficial effects of the present invention compared with the prior art are:

[0026] The adjustable locking and releasing mechanism provided by the present invention can stably and reliably realize the locking function of the spacecraft in the on-orbit section and the releasing function in the on-orbit section, ensure the reliable driving and high-precision orientation function of the pointing mechanism after being on-orbit, and effectively protect the internal power transmission components;

[0027] The locking and releasing mechanism provided by the present invention has an adjustable function. The relative distance between the pyrotechnic pin puller and the shaft system is adjusted by the adjusting component, so that the locking and manual unlocking and releasing functions of the shaft system can be realized, and the operation is convenient.

[0028] The adjustable locking release mechanism provided by the present invention only relies on the detonation of pyrotechnics to complete unlocking, without relying on other auxiliary parts, which greatly improves the reliability of the unlocking function;

[0029] The adjustable locking and releasing mechanism provided by the present invention can realize the locking of the axis system, and can be locked when the envelope of the spacecraft's folded state range is small, which is beneficial to the overall arrangement of the positions of each single machine in the spacecraft system. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1It is a schematic diagram of the appearance of the adjustable locking and releasing mechanism of a spacecraft provided by the present invention;

[0031] Figure 2 It is a cross-sectional view of the adjustable locking and releasing mechanism of a spacecraft provided by the present invention;

[0032] Figure 3 It is a schematic diagram of the adjustment process of the adjustment component provided by the present invention;

[0033] Figure 4 It is a schematic cross-sectional view of the adjustment component provided by the present invention after adjustment is completed;

[0034] Illustration Description:

[0035] 1—shaft system, 2—pin puller locking sleeve, 3—pyrotechnic pin puller, 4—M4 mounting screws for clamping sleeve, 5—pin puller clamping sleeve, 6—adjustment assembly, 7—M4 mounting screws for base, 8—base; 201—piston, 202—locking pin, 203—body, 204—igniter, 205—blocking cover; 301-adjustment tray, 302-thin nut, 303-fixing nut, 304-M4 mounting screws for fixing nut. DETAILED DESCRIPTION

[0036] The present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0037] like Figure 1 As shown, the adjustable locking and releasing mechanism for a spacecraft of the present invention comprises: a shaft system 1, a locking sleeve of a pin puller 2, a pin puller 3 for explosives, an M4 mounting screw 4 for a compression sleeve, a pin puller compression sleeve 5, an adjustment tray 6, an M4 mounting screw 7 for a base, and a base 8;

[0038] The pin puller locking sleeve 2 is connected to the internal thread of the mounting hole of the shaft system 1 through an external thread. The pin puller locking sleeve 2 is tightly matched with the shaft system 1. The interior of the pin puller locking sleeve 2 is a tapered hole, which is conically matched with the head of the piston 201.

[0039] The pyrotechnic pin puller 3 comprises a piston 201, a locking pin 202, a body 203, an igniter 204, and a plug cover 205; a cavity is machined inside the body 203, the piston 201 is installed in the cavity, the inside of the pin puller locking sleeve 2 is a tapered hole, the tapered head of the piston 201 is inserted into the tapered hole of the pin puller locking sleeve 2, and the bottom of the cavity is sealed by the plug cover 205; the igniter 204 is installed on the side wall of the body 203, and the outlet of the igniter 204 is connected to the cavity; a groove is machined on the upper part of the piston 201, and a locking pin mounting hole is machined on the upper side wall of the body, and the locking pin 202 passes through the locking pin mounting hole and is inserted into the groove machined on the upper part of the piston 201;

[0040] The bottom of the main body 203 is installed on the adjustment component 6, and the adjustment component 6 is installed on the base 8; the adjustment component 6 can adjust the relative position between the pyrotechnic pin puller 3 and the shaft system 1, and apply a positive pre-tightening force to the adjustment component 6 to make the pyrotechnic pin puller 3 press against the shaft system 1, thereby realizing the locking function of the spacecraft launch section; applying a reverse force to the adjustment component 6, the pyrotechnic pin puller 3 is separated from the pin puller locking sleeve 2, thereby realizing the ground manual unlocking and releasing function; after the spacecraft enters orbit, the igniter 204 is detonated, and the high-temperature and high-pressure gas generated pushes the piston 201 to move upward, overcoming the friction force while cutting off the locking pin 202, and the piston retracts into the main body 203, thereby realizing the function of releasing the shaft system.

[0041] The adjustment assembly 6 includes an adjustment tray 301, a thin nut 302, and a fixed nut 303. The fixed nut 303 is fixed to the base through the base with an M4 mounting screw 7. The upper part of the adjustment tray 301 is a disc and the lower part is a threaded section. The main body of the pyrotechnic pin puller 3 is fixed to the upper surface of the adjustment tray 301, and the thin nut 302 is installed in the threaded section. Before adjustment, the thin nut 303 is rotated to a position where the upper surface is about 2 mm away from the lower surface of the disc on the A side of the adjustment tray 301, so as to ensure a certain adjustment margin of the adjustment assembly 6.

[0042] Rotate the threaded section of the adjusting tray 301 into the fixing nut 303, and the adjusting tray 301 can move up and down on the fixing nut 303 through the thread, ensuring that the distance between the upper surface of the tray and the pin puller locking sleeve 2 is greater than the total length of the pin puller, and the pin puller 3 is placed on the adjusting tray 301 in a vertical state with the piston facing the axis direction.

[0043] To prevent the shaft system from being offset when the pin puller is locked, two pin puller clamping sleeves 5 should be installed on the base in advance before adjusting the tray 301 to tighten the pin puller, so that the pin puller piston head is aligned with the installed pin puller locking sleeve hole on the shaft, and the pin puller is reliably fitted to maintain the centering state.

[0044] The locking and releasing method of the present invention is as follows:

[0045] Align the pin puller piston head with the installed pin puller locking sleeve hole on the shaft and make them fit securely, then adjust the pin puller adjustment assembly 6 so that the adjustment tray 301 supports the tail of the pin puller and the pin puller 3 is in a tightened state, then use an open-end torque wrench to apply a torque of 8±0.5Nm on the adjustment tray 301 to make the pin puller 3 completely in a tightened state;

[0046] Use an adjustable spanner to apply a pre-tightening force of 15±0.5Nm to the thin nut 302, and completely tighten the thin nut 302 and the fixed nut 303 on the adjustment tray. The lower surface of the thin nut overlaps with the B surface of the fixed nut, which plays a role in tightening the thread and preventing it from loosening;

[0047] Two pin puller clamping sleeves 5 are used to hold the pyrotechnic pin puller 3 tightly, which plays the role of fixing the pyrotechnic pin puller after unlocking it in the track. The pin puller clamping sleeve is fixed to the base 8 using the base M4 mounting screw 7, thereby realizing the function of locking the shaft system;

[0048] When manually unlocking on the ground, the pin puller pressing sleeve 5 can be temporarily not installed, first reversely rotate the thin nut 302 until the upper surface is about 2 mm away from the A surface of the adjustment tray, reversely rotate the adjustment tray 301, and the pin puller 3 moves downward with the adjustment tray 301 to disengage from the locking sleeve, thereby realizing the manual unlocking function;

[0049] After the spacecraft enters orbit, the pin puller igniter 204 is detonated, and the high-temperature and high-pressure gas generated pushes the pin puller piston 201 to move, overcoming the friction force and cutting off the locking pin 202. The piston 201 retracts into the pin puller body 203, and the connection between the pin puller 3 and the shaft system 1 is lost, thereby realizing the function of releasing the shaft system.

[0050] Example

[0051] like Figure 1 and Figure 2 As shown, the pin puller locking sleeve 2 is connected to the internal thread of the mounting hole of the shaft system 1 through an external thread, and the locking sleeve 2 is tightly matched with the shaft system 1; the adjustment component 6 adjusts the relative position between the pyrotechnic pin puller 3 and the shaft system 1, thereby realizing the locking and release of the shaft system; the two pin puller clamping sleeves 5 hold the pin pullers tightly, playing the role of fixing the pyrotechnic pin pullers after detonation and unlocking.

[0052] Further, if Figure 3 As shown, the fixing nut 303 is fixed to the base by four fixing nuts and M4 mounting screws 304, and the thin nut 302 can move up and down the adjustment tray 301 through the thread, and the thin nut 302 is rotated to a position where the upper surface is about 2 mm away from the A surface of the adjustment tray;

[0053] Further, the adjustment tray 301 is rotated into the fixing nut 303, and the adjustment tray 301 can move up and down on the fixing nut 303 through the thread, ensuring that the distance between the upper surface of the tray and the locking sleeve of the pin puller is greater than the total length of the pin puller, and the pyrotechnic pin puller 3 is placed on the tray in a vertical state with the piston facing the axis direction;

[0054] Before adjusting the tray 301 to tighten the pin puller, two pin puller clamping sleeves 5 should be pre-installed to hold the pin puller tightly, so that the pin puller piston head is aligned with the installed pin puller locking sleeve hole on the shaft, and the pin puller is reliably fitted to maintain the centering state, so as to avoid the shaft system offset when locking;

[0055] Further, the pin puller adjustment assembly 6 is adjusted so that the adjustment tray 303 is against the tail of the pin puller and the pin puller 3 is in a tightened state. Then, an open-end torque wrench is used to apply a torque of 8±0.5Nm on the adjustment tray so that the pin puller is completely in a tightened state.

[0056] Further, if Figure 4 As shown, a pre-tightening force of 15±0.5Nm is applied to the thin nut 302 using an adjustable spanner, and the thin nut 302 and the fixed nut 303 on the adjustment tray 301 are completely tightened, and the lower surface of the thin nut coincides with the B surface of the fixed nut, which plays a role in tightening and preventing loosening;

[0057] Two pin puller clamping sleeves 5 are used to hold the pyrotechnic pin puller 3 tightly. The pin puller clamping sleeve 5 is fixed to the base 8 using four base M4 mounting screws 7. Two clamping sleeves are connected using two M4 mounting screws 4 to achieve the function of locking the shaft system.

[0058] When manually unlocking on the ground, the pin puller pressing sleeve 5 can be temporarily not installed. First, the thin nut 303 is rotated in the opposite direction until the upper surface is about 2 mm away from the A surface of the adjustment tray, and the adjustment tray 301 is rotated in the opposite direction. The pin puller 3 moves downward with the adjustment tray 301 and disengages from the locking sleeve 2, thereby realizing the manual unlocking function on the ground;

[0059] After the spacecraft enters orbit, the pin puller igniter 204 is detonated, and the high-temperature and high-pressure gas generated pushes the pin puller piston 201 to move, overcoming the friction force and cutting off the locking pin 202. The piston 201 retracts into the pin puller body 203, and the connection between the pin puller 3 and the shaft system 1 is lost, thereby realizing the function of releasing the shaft system.

[0060] The working principle of the present invention is as follows: the relative position between the pin puller and the shaft system is adjusted by the adjustment component, and the pin puller presses against the shaft system after the adjustment component applies the specified pre-tightening force, thereby realizing the locking function of the spacecraft launch section; the adjustment component is rotated in the opposite direction, and the pin puller is separated from the locking sleeve installed on the shaft system, realizing the manual unlocking and releasing function on the ground; after the spacecraft enters orbit, the pin puller igniter is detonated, and the high-temperature and high-pressure gas generated pushes the pin puller piston to move, overcoming the friction force while cutting off the locking pin, and the piston retracts into the pin puller body, thereby realizing the release function of the shaft system. The adjustable locking and releasing mechanism involved in the present invention can realize manual locking and releasing on the ground, is easy to operate, and has been verified many times that the locking and releasing function is safe and reliable; the pin puller relies on pyrotechnics to unlock, and does not rely on other parts. The successful detonation of pyrotechnics means that the release function of the entire mechanism is realized.

[0061] The spacecraft locking and releasing mechanism involved in the present invention has an adjustable function, and the adjusting component can realize the locking and releasing of the axis system; the mechanism can be locked when the axis system is in an orthogonal retracted state, thereby reducing the overall range envelope of the spacecraft, which is beneficial to the spacecraft system to coordinate the position planning of each single machine; the unlocking and releasing function relies on the pyrotechnic pin puller to cut off the locking pin, does not rely on other auxiliary parts, and has a high degree of reliability.

[0062] The contents not described in detail in the specification of the present invention belong to the well-known technologies of professionals in the field.

Claims

1. A spacecraft adjustable locking and releasing mechanism, characterized in that: include: A shaft system (1), a pin puller locking sleeve (2), an explosive device pin puller (3), an adjustment component (6), and a base (8); A mounting hole is processed on the shaft system (1), and the pin puller locking sleeve (2) is connected to the internal thread of the mounting hole of the shaft system (1) through an external thread; The pyrotechnic pin puller (3) comprises a piston (201), a locking pin (202), a body (203), an igniter (204), and a plug cover (205); a cavity is processed inside the body (203), the piston (201) is installed in the cavity, the pin puller locking sleeve (2) has a conical hole inside, the conical head of the piston (201) is inserted into the conical hole of the pin puller locking sleeve (2), and the bottom of the cavity is sealed by the plug cover (205); an igniter (204) is installed on the side wall of the body (203), and the outlet of the igniter (204) is connected to the cavity; a groove is processed on the upper part of the piston (201), a locking pin mounting hole is processed on the upper side wall of the body, and the locking pin (202) passes through the locking pin mounting hole and is inserted into the groove processed on the upper part of the piston (201); The bottom of the body (203) is mounted on an adjustment component (6), and the adjustment component (6) is mounted on a base (8); the adjustment component (6) can adjust the relative position between the pyrotechnic pin puller (3) and the shaft system (1), and a positive pre-tightening force is applied to the adjustment component (6) so that the pyrotechnic pin puller (3) presses against the shaft system (1), thereby realizing the locking function of the spacecraft launch section; a reverse force is applied to the adjustment component (6), so that the pyrotechnic pin puller (3) and the pin puller locking sleeve (2) are separated, thereby realizing the ground manual unlocking and releasing function; after the spacecraft enters orbit, the igniter (204) is detonated, and the high-temperature and high-pressure gas generated pushes the piston (201) to move upward, thereby overcoming the friction force and cutting off the locking pin (202), and the piston is retracted into the body (203), thereby realizing the shaft system release function.

2. The adjustable locking and releasing mechanism for a spacecraft according to claim 1, characterized in that: The adjustment component (6) comprises an adjustment tray (301), a thin nut (302), and a fixing nut (303); The fixing nut (303) is fixed on the base (8), the upper part of the adjusting tray (301) is a disc and the lower part is a threaded section, and the thin nut (302) is installed on the threaded section; The adjusting tray (301) is rotated into the fixing nut (303), and the adjusting tray (301) can move up and down on the fixing nut (303) through the thread. Before installing the pyrotechnic pin puller (3), ensure that the distance between the upper surface of the adjusting tray (301) and the pin puller locking sleeve (2) is greater than the total length of the pyrotechnic pin puller, so as to ensure the installation space of the pyrotechnic pin puller.

3. The adjustable locking and releasing mechanism for a spacecraft according to claim 2, characterized in that: The thin nut (302) is connected to the adjustment tray (301) by threads. Before adjustment, the thin nut (303) is rotated until its upper surface is 2 mm away from the lower surface of the disc, so as to ensure a certain adjustment margin of the adjustment component (6).

4. The adjustable locking and releasing mechanism for a spacecraft according to claim 3, characterized in that: The adjustment assembly (6) further comprises two pin puller compression sleeves (5); Two pin puller clamping sleeves (5) are fixed on the base (8). After the adjusting assembly (6) adjusts the relative position between the pyrotechnic pin puller (3) and the shaft system (1) to the right position, the two pin puller clamping sleeves (5) hold the pyrotechnic pin puller tightly from both sides, so that the piston head of the pyrotechnic pin puller is aligned with the installed pin puller locking sleeve hole on the shaft system, and the pyrotechnic pin puller is reliably fitted and kept in a centered state; At the same time, the pin puller clamping sleeve holds the pyrotechnic pin puller tightly to ensure that the pyrotechnic pin puller is always in a fixed state after being unlocked in orbit.

5. The adjustable locking and releasing mechanism for a spacecraft according to claim 3, characterized in that: The material of the thin nut (302) is 2Gr13 stainless steel with a thickness of 5mm. The internal thread of the thin nut (302) cooperates with the thread section of the adjustment tray (301) to have the function of tightening and preventing loosening.

6. The adjustable locking and releasing mechanism for a spacecraft according to claim 3, characterized in that: The material of the adjustment tray (301) is titanium alloy.

7. The adjustable locking and releasing mechanism for a spacecraft according to claim 3, characterized in that: The material of the fixing nut (303) is titanium alloy.

8. The locking and releasing method of the adjustable locking and releasing mechanism of a spacecraft according to any one of claims 4 to 7, characterized in that: include: By rotating the adjustment tray (301) in the forward direction, the adjustment tray (301) is pressed against the rear end of the pyrotechnic pin puller, and the pyrotechnic pin puller (3) is in a tightened state. Then, an open-end torque wrench is used to apply a torque of 8±0.5 Nm on the adjustment tray (301), so that the pyrotechnic pin puller (3) is completely in a tightened state. Using an adjustable spanner, a pre-tightening force of 15±0.5 Nm is applied to the thin nut (302), and the thin nut (302) and the fixed nut (303) on the adjustment tray are completely tightened, so that the lower surface of the thin nut overlaps with the upper surface of the fixed nut, thereby achieving locking and anti-loosening between the thin nut (302) and the adjustment tray (301), and preventing the pre-tightening force from changing due to loosening of the thread under the action of a mechanical environment; Two pin puller pressing sleeves (5) hold the pyrotechnic pin puller tightly from both sides, so that the piston head of the pyrotechnic pin puller is aligned with the installed pin puller locking sleeve hole on the shaft system, and the pin puller locking sleeve hole is reliably fitted to maintain the centering state; When manually unlocking on the ground, loosen the pin puller clamping sleeve (5), first use an adjustable wrench to reversely rotate the thin nut (302) until the upper surface is 2 mm away from the lower surface of the disc, and then use an open-end torque wrench to reversely rotate the adjustment tray (301), and the pyrotechnic pin puller (3) moves downward with the adjustment tray (301) to separate from the pin puller locking sleeve, thereby realizing the manual unlocking function; After the spacecraft enters orbit, the igniter (204) detonates, and the high-temperature and high-pressure gas generated pushes the piston (201) to move, overcoming the friction force and cutting off the locking pin (202), and the piston (201) retracts into the body (203), and the connection between the pin puller (3) and the shaft system (1) is lost, thereby realizing the function of releasing the shaft system.

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