High-bearing separation device for falling-off socket and base

Abstract

The invention discloses a high-bearing shedding socket base separating device, which comprises a separating base, an initiating explosive device actuating mechanism and a connecting element, and is characterized in that the separating base is mounted on the outer surface of an aircraft bulkhead, the initiating explosive device actuating mechanism is mounted on the inner surface of the aircraft bulkhead, and the separating base is connected with the initiating explosive device actuating mechanism through the connecting element; the separation base is provided with a drop-off socket used for being connected with a drop-off plug on a transmitting device, and the drop-off plug and the drop-off socket are assisted in aligned connection through the guide groove. The initiating explosive device actuating mechanism is internally provided with an exploder and a piston, and the exploder is detonated to drive the piston to move to sequentially cut off the cable falling off the socket and the connecting element in the process of moving; and fuel gas generated after detonation is guided to the bottom of the separation base through a fuel gas guide hole in the driving piston through a bulkhead of the aircraft and a gas injection hole in a shell of the initiating explosive device actuating mechanism. The invention has the advantages of simple structure, light weight, easy realization of manufacturing process, high assembly accessibility and the like.

Description

Technical Field

[0001] The invention belongs to the field of aircraft structure design, and in particular relates to a high-load-bearing drop-off socket base separation device. Background Art

[0002] The aircraft completes electrical communication with the launch device through the drop-out socket located on its head. The drop-out socket must be connected to the fixed plug on the launch device through a fixed height base. On the other hand, considering the aerodynamic drag reduction and range increase effect, the aircraft head is generally designed to be conical, and the smaller the taper, the more conducive to drag reduction. However, the base of the current fixed drop-out socket is highly raised compared to the cone surface of the aircraft head, which will have a great impact on the aerodynamic characteristics of the aircraft. Summary of the invention

[0003] The purpose of the present invention is to provide a high-load-bearing drop-off socket base separation device, which separates the entire base from the aircraft after the aircraft is launched, thereby ensuring that the aerodynamic shape of the aircraft is smooth during flight.

[0004] In order to achieve the above tasks, the present invention adopts the following technical solutions:

[0005] A high-load drop-out socket base separation device comprises a separation base, an pyrotechnic actuating mechanism and a connecting element, wherein the separation base is mounted on the outer surface of an aircraft cabin wall, the pyrotechnic actuating mechanism is mounted on the inner surface of the aircraft cabin wall, and the separation base and the pyrotechnic actuating mechanism are connected via the connecting element; a drop-out socket for connecting to a drop-out plug on a launch device is provided on the separation base, and the drop-out plug is assisted in alignment and connection with the drop-out socket via a guide groove; a detonator and a piston are arranged in the pyrotechnic actuating mechanism, and the cable of the drop-out socket and the connecting element are cut off in turn during the process of driving the piston to move after the detonator is detonated, and the gas generated after the detonation is guided to the bottom of the separation base via the jet holes on the aircraft cabin wall and the shell of the pyrotechnic actuating mechanism via the gas guide hole on the driving piston.

[0006] Furthermore, the separation base includes a base, the bottom surface of the base is conformal with the outer surface of the aircraft, the guide groove is provided on the front upper surface of the base, and a square step groove is provided on the rear upper surface of the separation base, and the drop-out socket is installed on the step inside the step groove; the cable at the bottom of the drop-out socket passes through the separation base, the aircraft cabin wall and the wire holes on the pyrotechnic actuation mechanism, extends into the interior of the aircraft and is connected to the equipment carried in the aircraft; a first pin hole is opened on the bottom surface of the step groove.

[0007] Furthermore, a metal block is embedded in the guide groove, and the lower end of the metal block is in contact with the outer surface of the aircraft cabin wall.

[0008] Furthermore, the upper surface of the shell of the pyrotechnic actuating mechanism is conformal to the inner surface of the aircraft cabin wall, and the shell is divided into a front cylindrical inner cavity and a rear actuating cavity by a perforated partition; the cylindrical inner cavity is used to install a piston, and the piston rod of the piston passes through the hole on the perforated partition; the piston is provided with a shaped gas guide hole, and both ends of the gas guide hole pass through the front end face and the side face of the piston, and the jet hole is located below the base of the separation base.

[0009] Furthermore, a detonator is provided at the front end of the cylindrical inner cavity; the cable passes through the rear end of the piston and the perforated partition; a third pin hole is provided on the upper wall of the actuating cavity, and a threaded blind hole and a second pin hole corresponding to the third pin hole are provided on the lower wall of the actuating cavity and the cabin wall of the aircraft respectively; wherein the first pin hole, the second pin hole, the third pin hole and the threaded blind hole are coaxially arranged and are used together for the penetration and fixation of the shear screw in the connecting element; the actuating cavity is sealed by a rear cover plate.

[0010] Furthermore, the connecting element includes a shear screw and a spring; the shear screw passes through a first pin hole on the bottom surface of the step groove, a second pin hole on the aircraft cabin wall, and a third pin hole on the upper wall of the actuating cavity in sequence; the lower end of the shear screw is a threaded end and is assembled into a threaded blind hole on the lower wall of the actuating cavity; an annular stress groove is provided on the outer circumference of the part of the shear screw located in the actuating cavity.

[0011] Furthermore, the upper end of the shear screw is a shaped structure and is located above the first pin hole; the spring in a compressed state is arranged between the upper end of the shear screw and the second pin hole, and after the shear screw breaks, the spring releases elastic force to lift the broken upper half of the shear screw.

[0012] Furthermore, when the aircraft is being loaded, the separation base and the pyrotechnic actuating mechanism are connected by the shear screw in the connecting element passing through the first pin hole, the second pin hole, and the third pin hole in sequence, and the lower end of the shear screw is assembled into the threaded blind hole on the lower wall of the actuating cavity; during the loading process, the detachable socket is positioned and plugged with the detachable plug on the launching device through the guide groove on the separation base and the guide pin on the launching device, and the communication between the launching device and the onboard equipment in the aircraft is realized through the cable at the bottom of the detachable socket.

[0013] Furthermore, after the aircraft is launched, when the detonator in the pyrotechnic actuating mechanism receives the detonation signal, it detonates, generating gas to push the piston to move backward. During the movement, the rear end of the piston interacts with the wire hole on the pyrotechnic actuating mechanism to squeeze the cable, and the cable is cut by the edge of the wire hole, thereby realizing the separation of the cables inside and outside the aircraft cabin; thereafter, the piston continues to move, and the piston rod hits the shear screw, causing the shear screw to break at the stress groove, thereby releasing the constraint state on the separation base, and at the same time, the shear screw is lifted up by the action of the spring; in addition, after the piston rod hits the shear screw and breaks the shear screw, the piston is located at a position where the gas guide hole is connected to the jet hole on the aircraft cabin wall, then the gas generated by the detonator enters the jet hole from the front end of the piston through the shaped gas guide hole, acts on the bottom of the separation base from the jet hole, and drives the separation base to quickly leave the aircraft.

[0014] An aircraft adopts the high-load shedding socket base separation device to connect with the shedding plug on the launching device.

[0015] Compared with the prior art, the present invention has the following technical features:

[0016] The device of the present invention can not only realize the electrical connection between the aircraft and the launch device in the loaded state, but also ensure that the conical surface of the head of the aircraft is smooth and has no protrusions during the flight of the aircraft. It is an integrated device of electrical communication and aerodynamic drag reduction. The present invention has the advantages of simple structure, easy processing and manufacturing, convenient installation, high assembly accessibility, etc., and effectively solves the contradiction between the protrusion of the head falling off the socket base during electrical communication between the aircraft and the launch device and the demand for increased range and drag reduction. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 is a schematic diagram of a high-load shedding socket base separation device;

[0018] Figure 2 It is a schematic diagram of the installation of connecting components;

[0019] Figure 3 It is a schematic diagram of the appearance of the cone section of the aircraft head in the loaded state;

[0020] Figure 4 It is a schematic diagram of the appearance of the cone section of the aircraft's head during flight.

[0021] Explanation of the reference numerals in the accompanying drawings: 1 separation base, 2 pyrotechnic actuating mechanism, 3 connecting element, 4 aircraft, 1a base, 1b guide groove, 1c metal block, 1d drop-out socket, 1e step groove, 1f jet hole, 1g cable, 1h wire hole, 1i first pin hole, 2a shell, 2b initiator, 2c piston, 2d rear cover plate, 2e third pin hole, 2f threaded blind hole, 2g perforated partition plate, 2h cylindrical inner cavity, 2i actuating cavity, 3a shear screw, 3b spring, 3c stress groove, 4a second pin hole. DETAILED DESCRIPTION

[0022] In order to take into account the electrical compatibility between the aircraft range and the launch device, it is necessary to design a high-load-bearing detachable socket base separation device at the head of the aircraft. During loading, the device can be reliably fixed to the head of the aircraft and complete the self-guided plug-in with the electrical interface of the launch device. After launch, the entire base is separated from the aircraft through the drive unit to ensure a smooth aerodynamic shape during flight.

[0023] See attached Figures 1 to 4 The present invention provides a high-load-bearing socket base separation device, comprising a separation base 1, an pyrotechnic device actuating mechanism 2 and a connecting element 3, wherein:

[0024] The separation base 1 is installed on the outer surface of the aircraft 4 cabin wall, and the pyrotechnic actuator 2 is installed on the inner surface of the aircraft 4 cabin wall. The separation base 1 is connected to the pyrotechnic actuator 2 through a connecting element 3; a disengagement socket 1d for connecting to a disengagement plug on a launching device is provided on the separation base 1, and an alignment connection between the disengagement plug and the disengagement socket 1d is assisted by a guide groove 1b; a detonator 2b and a piston 2c are provided in the pyrotechnic actuator 2, and after the detonator 2b is detonated, the cable 1g of the disengagement socket 1d and the connecting element 3 are cut off in sequence during the process of driving the piston 2c to move, and the gas guide hole on the driving piston 2c is used to guide the gas generated after the detonation to the bottom of the separation base 1 through the aircraft 4 cabin wall and the jet hole 1f on the shell 2a of the pyrotechnic actuator 2; the specific implementation process of the present invention is described in detail below in conjunction with the accompanying drawings.

[0025] The separation base 1 includes a base 1a, a guide groove 1b, a metal block 1c and a drop-out socket 1d; the separation base 1 is installed on the outer surface of the wall of the aircraft 4 through the base 1a. The base 1a is a low-density non-metallic block structure, for example, it can be made of polyurethane foam or PMI foam. The bottom surface of the base 1a is conformal to the outer surface of the aircraft 4, see Figure 2In this embodiment, the bottom surface is an arc-shaped structure; a guide groove 1b is provided on the front upper surface of the base 1a, which is used to cooperate with the guide pin on the launch device of the aircraft 4 to adjust the posture of the aircraft 4 when the aircraft 4 is loaded, so that the drop-off plug on the launch device can be aligned with the drop-off socket 1d; a titanium alloy tubular metal block 1c is embedded in the guide groove 1b, and the lower end of the metal block 1c is in contact with the outer surface of the wall of the aircraft 4, which is used to withstand the impact force when colliding with the guide pin, and at the same time transfer the load to the cabin of the aircraft 4 to reduce the impact of the separation base 1 Load; a square step groove 1e is provided on the upper surface of the rear part of the separation base 1, and the drop-out socket 1d is installed on the step inside the step groove 1e. By controlling the height of the step, the upper surface of the drop-out socket 1d meets the insertion height requirement; the cable 1g at the bottom of the drop-out socket 1d passes through the separation base 1, the wall of the aircraft 4 and the wire hole 1h on the pyrotechnic actuating mechanism 2 and extends into the interior of the aircraft 4 to be connected with the equipment carried in the aircraft 4; a first pin hole 1i is provided on the bottom surface of the step groove 1e, which is used to pass the shear screw 3a in the connecting element 3.

[0026] The pyrotechnic device actuating mechanism 2 is installed inside the cabin of the aircraft 4 below the separation base 1. The pyrotechnic device actuating mechanism 2 includes a shell 2a, a detonator 2b, a piston 2c and a rear cover plate 2d. The shell 2a is installed on the inner surface of the cabin wall of the aircraft 4, and the upper surface of the shell 2a is conformal to the inner surface of the cabin wall; the shell 2a is divided into a front cylindrical cavity 2h and a rear actuating cavity 2i by a perforated partition 2g; the cylindrical cavity 2h is used to install the piston 2c, and the piston rod of the piston 2c passes through The hole on the perforated partition 2g; the outer shape of the piston 2c is adapted to the inner surface of the cylindrical inner cavity 2h, and the piston rod on the piston 2c is a rectangular parallelepiped structure, which is used to hit the shear screw 3a on the connecting element 3; the piston 2c is provided with an L-shaped gas guide hole, and the two ends of the gas guide hole pass through the front end face and the side of the piston 2c, and the gas guide hole is matched with the jet hole 1f opened on the aircraft 4 cabin wall and the shell 2a, and the jet hole 1f is located below the base 1a of the separation base 1. After receiving the ignition signal, the pyrotechnic actuator 2 can complete multiple tasks such as wire cutting, unlocking, and driving separation in a timed sequence. It is a multifunctional fusion mechanism that realizes the integrated design of structure and function.

[0027] There is a detonator 2b at the front end of the cylindrical inner cavity 2h; the cable 1g passes through the rear end of the piston 2c and the perforated partition 2g; the actuating cavity 2i provides movement space for the piston 2c; a third pin hole 2e is arranged on the upper wall of the actuating cavity 2i, and a threaded blind hole 2f and a second pin hole 4a corresponding to the third pin hole 2e are respectively arranged on the lower wall of the actuating cavity 2i and the cabin wall of the aircraft 4; wherein the first pin hole 1i, the second pin hole 4a, the third pin hole 2e and the threaded blind hole 2f are coaxially arranged, and are commonly used for the penetration and fixation of the shear screw 3a in the connecting element 3; the actuating cavity 2i is sealed by the rear cover plate 2d.

[0028] The connecting element 3 is assembled in the pyrotechnic actuating mechanism 2, and the connecting element 3 includes a shear screw 3a and a spring 3b; the shear screw 3a fixes the separation base 1 and the pyrotechnic actuating mechanism 2 together, and the shear screw 3a passes through the first pin hole 1i on the bottom surface of the step groove 1e, the second pin hole 4a on the cabin wall of the aircraft 4, and the third pin hole 2e on the upper wall of the actuating cavity 2i in sequence; the lower end of the shear screw 3a is a threaded end and is assembled into the threaded blind hole 2f on the lower wall of the actuating cavity 2i; the upper end of the shear screw 3a is a T-shaped structure and is located above the first pin hole 1i; the spring 3b in a compressed state is arranged between the upper end of the shear screw 3a and the second pin hole 4a; an annular stress groove 3c is provided on the outer circumference of the part of the shear screw 3a located in the actuating cavity 2i, so that the shear screw 3a is cut off from the stress groove 3c after being hit by the piston rod, and after the shear screw 3a is broken, the spring 3b releases the elastic force to lift the upper half of the shear screw 3a after it is broken.

[0029] When the aircraft 4 is being loaded, the separation base 1 and the pyrotechnic actuating mechanism 2 are connected by the shear screw 3a in the connecting element 3 passing through the first pin hole 1i, the second pin hole 4a, and the third pin hole 2e in sequence, and the lower end of the shear screw 3a is assembled into the threaded blind hole 2f on the lower wall of the actuating cavity 2i; during the loading process, the detachable socket 1d is positioned and plugged with the detachable plug on the launching device through the guide groove 1b on the separation base 1 and the guide pin on the launching device, and the communication between the launching device and the equipment on board the aircraft 4 is realized through the cable 1g at the bottom of the detachable socket 1d.

[0030] After the aircraft 4 is launched, when the detonator 2b in the pyrotechnic actuator 2 receives the detonation signal, it detonates, and the generated gas pushes the piston 2c to move backward. During the movement, the rear end of the piston 2c interacts with the wire hole 1h on the pyrotechnic actuator 2 to squeeze the cable 1g, and the cable 1g is cut by relying on the edge of the wire hole 1h, so as to separate the cables 1g inside and outside the cabin of the aircraft 4; then the piston 2c continues to move, and the piston rod hits the shear screw 3a, causing the shear screw 3a to break at the stress groove 3c, thereby releasing the constraint state of the separation base 1, and at the same time, the shear screw is The pin 3a is lifted up to avoid the shear screw 3a and the hole walls of the first pin hole 1i, the second pin hole 4a and the third pin hole 2e from getting stuck during the separation process; in addition, after the piston rod breaks the shear screw 3a, the piston 2c is located at the position where the gas guide hole and the jet hole 1f on the wall of the aircraft 4 are connected, then the gas generated by the detonator 2b enters the jet hole 1f from the front end of the piston 2c through the L-shaped gas guide hole, and acts on the bottom of the separation base 1 from the jet hole 1f, driving the separation base 1 to quickly leave the aircraft 4, and finally achieving a smooth outer surface of the aircraft 4 during flight, reducing resistance and increasing the range of the aircraft.

[0031] To sum up, in the present invention, the pyrotechnic actuator 2 is mounted on the inner wall of the cabin of the aircraft 4, and the separation base 1 is located on the outer surface of the cabin of the aircraft 4, and is fixedly connected to the pyrotechnic actuator 2 by passing through the cabin wall through the connecting element 3; the base 1a of the separation base 1 is molded by low-density non-metallic material with high molding efficiency, and a tubular metal block 1c is embedded in the guide groove 1b docking with the launch device, and its through-type structure can transfer the impact load when the guide pin of the launch device is docked to the cabin of the aircraft 4, thereby reducing the load on the separation base 1; the pyrotechnic actuator 2 plays the role of unlocking and driving separation, and has the characteristics of small size, fast response and high technical maturity; each part is processed independently, and each part is made of common materials and mature processes, and the installation method is simple and quick, and it only needs to be assembled with the cabin in the assembly link, and the processability is good.

[0032] The high-load-bearing drop-off socket base separation device provided by the present invention has been successfully applied to a certain aircraft, can achieve reliable electrical communication with the launch device, and reduce the overall flight resistance by more than 8%; after ground and flight tests, it has good applicability.

[0033] The above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit them. Although the present application has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. These modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present application, and should all be included in the protection scope of the present application.

Claims

1. A high-load-carrying socket base separation device, characterized in that: The invention comprises a separation base (1), an pyrotechnic device actuating mechanism (2) and a connecting element (3), wherein the separation base (1) is mounted on the outer surface of the wall of an aircraft (4), the pyrotechnic device actuating mechanism (2) is mounted on the inner surface of the wall of the aircraft (4), and the separation base (1) and the pyrotechnic device actuating mechanism (2) are connected via the connecting element (3); a drop-out socket (1d) for connecting to a drop-out plug on a launching device is arranged on the separation base (1), and a guide groove (1b) is used to assist the drop-out plug and the drop-out socket (1d) to be connected. d) alignment connection; a detonator (2b) and a piston (2c) are arranged in the pyrotechnic device actuating mechanism (2); after the detonator (2b) is detonated, the cable (1g) of the detached socket (1d) and the connecting element (3) are cut off in sequence during the movement of the driving piston (2c) and the gas guide hole on the driving piston (2c) is used to guide the gas generated after the detonation through the aircraft (4) cabin wall and the gas injection hole (1f) on the shell (2a) of the pyrotechnic device actuating mechanism (2) to the bottom of the separation base (1).

2. The high-load-carrying drop-off socket base separation device according to claim 1, characterized in that: The separation base (1) comprises a base (1a), the bottom surface of the base (1a) is conformal to the outer surface of the aircraft (4), the guide groove (1b) is provided on the front upper surface of the base (1a), and a square step groove (1e) is provided on the rear upper surface of the separation base (1), and the drop-out socket (1d) is installed on the step inside the step groove (1e); the cable (1g) at the bottom of the drop-out socket (1d) passes through the separation base (1), the aircraft (4) cabin wall and the pyrotechnic device actuation mechanism (2) and extends into the aircraft (4) to connect with the equipment carried in the aircraft (4); a first pin hole (1i) is provided on the bottom surface of the step groove (1e).

3. The high-load-carrying drop-off socket base separation device according to claim 2, characterized in that: A metal block (1c) is embedded in the guide groove (1b), and the lower end of the metal block (1c) is in contact with the outer surface of the cabin wall of the aircraft (4).

4. The high-load-carrying drop-off socket base separation device according to claim 2, characterized in that: The upper surface of the shell (2a) of the pyrotechnic device actuating mechanism (2) is conformal to the inner surface of the aircraft (4) cabin wall, and the shell (2a) is divided into a front cylindrical inner cavity (2h) and a rear actuating cavity (2i) by a perforated partition (2g); the cylindrical inner cavity (2h) is used to install a piston (2c), and the piston rod of the piston (2c) passes through the hole on the perforated partition (2g); the piston (2c) is provided with an L-shaped gas guide hole, and the two ends of the gas guide hole pass through the front end face and the side face of the piston (2c), and the gas injection hole (1f) is located below the base (1a) of the separation base (1).

5. The high-load-carrying drop-off socket base separation device according to claim 4, characterized in that: A detonator (2b) is provided at the front end of the cylindrical inner cavity (2h); the cable (1g) passes through the rear end of the piston (2c) and between the perforated partition plate (2g); a third pin hole (2e) is provided on the upper wall of the actuating cavity (2i), and a threaded blind hole (2f) and a second pin hole (4a) corresponding to the third pin hole (2e) are provided on the lower wall of the actuating cavity (2i) and the cabin wall of the aircraft (4); wherein the first pin hole (1i), the second pin hole (4a), the third pin hole (2e) and the threaded blind hole (2f) are coaxially arranged and are used together for the penetration and fixation of the shear screw (3a) in the connecting element (3); the actuating cavity (2i) is sealed by a rear cover plate (2d).

6. The high-load-carrying drop-off socket base separation device according to claim 5, characterized in that: The connecting element (3) comprises a shear screw (3a) and a spring (3b); the shear screw (3a) passes through a first pin hole (1i) on the bottom surface of a stepped groove (1e), a second pin hole (4a) on the wall of an aircraft (4), and a third pin hole (2e) on the upper wall of an actuating cavity (2i) in sequence; the lower end of the shear screw (3a) is a threaded end and is assembled into a threaded blind hole (2f) on the lower wall of the actuating cavity (2i); and an annular stress groove (3c) is provided on the outer circumference of the portion of the shear screw (3a) located in the actuating cavity (2i).

7. The high-load-carrying drop-off socket base separation device according to claim 6, characterized in that: The upper end of the shear screw (3a) is a T-shaped structure and is located above the first pin hole (1i); the spring (3b) in a compressed state is arranged between the upper end of the shear screw (3a) and the second pin hole (4a); after the shear screw (3a) breaks, the spring (3b) releases elastic force to lift up the upper half of the shear screw (3a) after it breaks.

8. The high-load-carrying drop-off socket base separation device according to claim 7, characterized in that: When the aircraft (4) is being loaded, the separation base (1) and the pyrotechnic device actuating mechanism (2) are connected by the shear screw (3a) in the connecting element (3) passing through the first pin hole (1i), the second pin hole (4a), and the third pin hole (2e) in sequence, and the lower end of the shear screw (3a) is assembled into the threaded blind hole (2f) on the lower wall of the actuating cavity (2i); during the loading process, the dropout socket (1d) is positioned and plugged with the dropout plug on the launching device through the guide groove (1b) on the separation base (1) and the guide pin on the launching device, and the communication between the launching device and the equipment carried in the aircraft (4) is realized through the cable (1g) at the bottom of the dropout socket (1d).

9. The high-load-carrying drop-off socket base separation device according to claim 7, characterized in that: After the aircraft (4) is launched, the detonator (2b) in the pyrotechnic actuator (2) receives a detonation signal and detonates, generating combustion gas to push the piston (2c) to move backwards. During the movement, the rear end of the piston (2c) interacts with the wire hole (1h) on the pyrotechnic actuator (2) to squeeze the cable (1g), and the cable (1g) is cut by the edge of the wire hole (1h), thereby separating the cables (1g) inside and outside the aircraft (4) cabin. Afterwards, the piston (2c) continues to move, and the piston rod hits the shear screw (3a), causing the shear screw (3a) to be pressed in the desired direction. The force groove (3c) is broken, thereby releasing the restraint state of the separation base (1), and at the same time, the shear screw (3a) is lifted up under the action of the spring (3b); in addition, after the piston rod hits and breaks the shear screw (3a), the piston (2c) is located at a position where the gas guide hole and the jet hole (1f) on the wall of the aircraft (4) are connected, and the gas generated by the detonator (2b) enters the jet hole (1f) from the front end of the piston (2c) through the L-shaped gas guide hole, and acts on the bottom of the separation base (1) from the jet hole (1f), driving the separation base (1) to quickly leave the aircraft (4).

10. An aircraft, characterized in that: The aircraft uses the high-load shedding socket base separation device according to any one of claims 1 to 9 to connect with the shedding plug on the launching device.

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