A high-load shedding socket base separation device

Abstract

The present invention discloses a high-load separation device for a socket base, which comprises a separation base, an explosive actuator mechanism and a connecting element. The separation base is installed on the outer surface of the aircraft cabin wall, and the explosive actuator mechanism is installed on the inner surface of the aircraft cabin wall. The separation base and the explosive actuator mechanism are connected through the connecting element. A dropout socket for connecting with a dropout plug on the launching device is arranged on the separation base, and the alignment connection between the dropout plug and the dropout socket is assisted by a guiding groove. An initiator and a piston are arranged in the explosive actuator mechanism. After the initiator is detonated, during the process of driving the piston to move, the cable of the dropout socket and the connecting element are cut off in sequence, and the gas generated after detonation is guided to the bottom of the separation base through the gas guiding holes on the driving piston and the gas jet holes on the housing of the aircraft cabin wall and the explosive actuator mechanism. The present invention has the advantages of simple structure, light weight, easy implementation of manufacturing process, high assembly accessibility, etc.

Description

Technical Field

[0001] The present invention belongs to the field of aircraft structure design, and particularly relates to a high-load separation device for the base of a detachable socket. Background Art

[0002] An aircraft completes electrical communication with a launch device through a detachable socket located at its head. The detachable socket must be connected to a fixed plug on the launch device through a base with a fixed height to ensure reliable docking. On the other hand, considering the aerodynamic drag reduction and range extension effect, the head shape of the aircraft is generally designed as a cone, and the smaller the taper, the more beneficial it is for drag reduction. Currently, the base of the fixed detachable socket protrudes significantly compared to the conical 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 separation device for the base of a detachable socket, which separates the entire base from the aircraft after the aircraft is launched to ensure a smooth aerodynamic shape during the flight of the aircraft.

[0004] To achieve the above task, the present invention adopts the following technical solutions:

[0005] A high-load separation device for the base of a detachable socket includes a separation base, a pyrotechnic actuating mechanism, and a connecting element. The separation base is installed on the outer surface of the aircraft cabin wall, the pyrotechnic actuating mechanism is installed on the inner surface of the aircraft cabin wall, and the separation base is connected to the pyrotechnic actuating mechanism through the connecting element. A detachable socket for connecting to a detachable plug on the launch device is provided on the separation base, and the alignment connection between the detachable plug and the detachable socket is assisted through a guiding groove. An initiator and a piston are arranged in the pyrotechnic actuating mechanism. After the initiator detonates, during the process of driving the piston to move, the cable of the detachable socket and the connecting element are successively cut off, and the gas generated after detonation is guided to the bottom of the separation base through the gas guiding holes on the driving piston and the air jet holes on the aircraft cabin wall and the shell of the pyrotechnic actuating mechanism.

[0006] Further, the separation base includes a base body. The bottom surface of the base body is conformal to the outer shape surface of the aircraft. The guiding groove is arranged on the upper surface of the front part of the base body. A square step groove is arranged on the upper surface of the rear part of the separation base, and the detachable socket is installed on the step inside the step groove. The cable at the bottom of the detachable socket extends into the aircraft through the wire passing holes penetrating the separation base, the aircraft cabin wall, and the pyrotechnic actuating mechanism and is connected to the equipment carried on the aircraft. A first pin hole is opened on the bottom surface of the step groove.

[0007] Further, a metal block is embedded in the guiding groove, and the lower end of the metal block contacts the outer surface of the aircraft cabin wall.

[0008] Furthermore, the upper surface of the housing of the pyrotechnic actuator mechanism is conformal with the inner surface of the aircraft bulkhead. The housing is divided into a front cylindrical inner cavity and a rear actuator 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 gas guiding hole in a shape, and both ends of the gas guiding hole penetrate through the front end face and the side face of the piston. The gas jet hole is located below the base body of the separation base.

[0009] Furthermore, there is an initiator at the front end inside the cylindrical inner cavity; the cable passes through the space between the rear end of the piston and the perforated partition; a third pin hole is provided on the upper wall surface of the actuator cavity, and a threaded blind hole and a second pin hole corresponding to the third pin hole are respectively provided on the lower wall surface of the actuator cavity and the aircraft bulkhead. Among them, the first pin hole, the second pin hole, the third pin hole, and the threaded blind hole are coaxially arranged and are jointly used for the penetration and fixation of the shear screw in the connecting element; the actuator cavity is sealed by a rear cover plate.

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

[0011] Furthermore, the upper end of the shear screw is in a shape 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 push up the upper half part of the shear screw after it breaks.

[0012] Furthermore, when the aircraft is being loaded, the separation base and the pyrotechnic actuator mechanism are connected by sequentially passing the shear screw in the connecting element through the first pin hole, the second pin hole, and the third pin hole, and the lower end of the shear screw is assembled into the threaded blind hole on the lower wall surface of the actuator cavity; during the loading process, the drop socket realizes the positioning and mating with the drop plug on the launch device through the guiding groove on the separation base and the guiding pin on the launch device, and realizes the communication between the launch device and the equipment carried on the aircraft through the cable at the bottom of the drop socket.

[0013] Further, after the aircraft is launched, when the detonator in the pyrotechnic actuator 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 passing hole on the pyrotechnic actuator to squeeze the cable, and the cable is cut by the edge of the wire passing hole, realizing the separation of the cables inside and outside the aircraft cabin; then 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 of the separation base, and at the same time, the shear screw is jacked up under the action of the spring; in addition, after the piston rod breaks the shear screw, at this time the piston is located at the part where the gas guiding hole communicates with the air jet hole on the aircraft cabin wall, then the gas generated by the detonator enters the air jet hole from the front end of the piston through the shaped gas guiding hole, and acts on the bottom of the separation base from the air jet hole, driving the separation base to quickly leave the aircraft.

[0014] An aircraft, which is connected to the dropout plug on the launch device by using the high-load dropout socket base separation 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 loading state, but also ensure that the head cone surface is smooth and without protrusions during the flight of the aircraft. It is a device integrating electrical communication and pneumatic drag reduction; the structure of the present invention has the advantages of simple structure, easy processing and manufacturing, convenient installation, high assembly accessibility, etc., effectively solving the contradiction between the protrusion of the head dropout socket base and the demand for range extension and drag reduction during the electrical communication between the aircraft and the launch device. Description of the Drawings

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

[0018] Figure 2 It is a schematic diagram of the connection element installation;

[0019] Figure 3 It is a schematic diagram of the outer shape of the head cone section of the aircraft in the loading state;

[0020] Figure 4 It is a schematic diagram of the outer shape of the head cone section of the aircraft during flight.

[0021] Description of the reference numerals: 1 separation base, 2 pyrotechnic actuator, 3 connection element, 4 aircraft, 1a base body, 1b guide groove, 1c metal block, 1d dropout socket, 1e step groove, 1f air jet hole, 1g cable, 1h wire passing hole, 1i first pin hole, 2a housing, 2b detonator, 2c piston, 2d rear cover plate, 2e third pin hole, 2f threaded blind hole, 2g perforated partition, 2h cylindrical inner cavity, 2i actuating cavity, 3a shear screw, 3b spring, 3c stress groove, 4a second pin hole. Specific embodiments

[0022] To balance the electrical compatibility between the flight range of the aircraft and the launcher, it is very necessary to design a high-load shedding socket base separation device at the head of the aircraft. During loading, this device can be reliably fixed to the head of the aircraft to complete the self-guided docking with the electrical interface of the launcher. After launch, the entire base is separated from the aircraft through the drive unit to ensure a smooth aerodynamic shape during flight.

[0023] See the appendix Figures 1 to 4 , the present invention provides a high-load shedding socket base separation device, including a separation base 1, an initiator actuating mechanism 2, and a connecting element 3, wherein:

[0024] The separation base 1 is installed on the outer surface of the cabin wall of the aircraft 4, and the initiator actuating mechanism 2 is installed on the inner surface of the cabin wall of the aircraft 4. The separation base 1 and the initiator actuating mechanism 2 are connected through the connecting element 3; a shedding socket 1d for connecting with the shedding plug on the launcher is provided on the separation base 1, and the alignment connection between the shedding plug and the shedding socket 1d is assisted by the guide groove 1b; an initiator 2b and a piston 2c are arranged in the initiator actuating mechanism 2. During the process of the piston 2c being driven to move after the initiator 2b detonates, the cable 1g of the shedding socket 1d and the connecting element 3 are successively cut off, and the gas generated after detonation is guided to the bottom of the separation base 1 through the gas guiding holes on the piston 2c and the jet holes 1f on the housing 2a of the cabin wall of the aircraft 4 and the initiator actuating mechanism 2. The following will describe the specific implementation process of the present invention in detail with reference to the accompanying drawings.

[0025] The separation base 1 includes a base body 1a, a guide groove 1b, a metal block 1c, and a shedding socket 1d; the separation base 1 is installed on the outer surface of the cabin wall of the aircraft 4 through the base body 1a. The base body 1a is a low-density non-metallic block structure, for example, it can be made of materials such as polyurethane foam or PMI foam. The bottom surface of the base body 1a is conformal to the outer shape surface of the aircraft 4. See Figure 2, in this embodiment, the bottom surface is an arc-shaped structure; a guiding groove 1b is provided on the upper surface of the front part of the base body 1a, which is used to cooperate with the guiding pin on the launching device of the aircraft 4 to adjust the attitude of the aircraft 4 during the loading of the aircraft 4, so that the separating plug on the launching device can be aligned with the separating socket 1d; a titanium alloy tubular metal block 1c is embedded in the guiding groove 1b, and the lower end of the metal block 1c contacts the outer surface of the cabin wall of the aircraft 4, which is used to bear the impact force when colliding with the guiding pin, and at the same time transfer the load to the cabin body of the aircraft 4 to reduce the load on the separating base 1; a square step groove 1e is provided on the upper surface of the rear part of the separating base 1, and the separating socket 1d is installed on the step inside the step groove 1e, and the height of the step is controlled so that the upper surface of the separating socket 1d meets the requirements of the insertion height; the cable 1g at the bottom of the separating socket 1d extends into the aircraft 4 through the wire passing holes 1h in the separating base 1, the cabin wall of the aircraft 4 and the pyrotechnic actuator mechanism 2 and is connected to 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 through the shear screw 3a in the connecting element 3.

[0026] The pyrotechnic actuator mechanism 2 is installed inside the cabin body of the aircraft 4 below the separating base 1. The pyrotechnic actuator mechanism 2 includes a housing 2a, a detonator 2b, a piston 2c and a rear cover plate 2d. The housing 2a is installed on the inner surface of the cabin wall of the aircraft 4, and the upper surface of the housing 2a is conformal with the inner surface of the cabin wall; the inside of the housing 2a is separated into a front cylindrical inner cavity 2h and a rear actuating cavity 2i by a perforated partition plate 2g; the cylindrical inner 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 plate 2g; the outer shape of the piston 2c is adapted to the inner shape surface of the cylindrical inner cavity 2h, and the piston rod on the piston 2c is a cuboid structure, which is used to strike the shear screw 3a on the connecting element 3; an L-shaped gas guiding hole is provided on the piston 2c, and both ends of the gas guiding hole penetrate through the front end surface and the side surface of the piston 2c, and the gas guiding hole cooperates with the gas jet holes 1f provided on the cabin wall of the aircraft 4 and on the housing 2a. The gas jet holes 1f are located below the base body 1a of the separating base 1. After receiving the ignition signal, the pyrotechnic actuator mechanism 2 can complete multiple tasks such as wire cutting, unlocking, and driving separation in sequence, which is a multi-functional integrated mechanism, realizing the integrated design of structural functions.

[0027] There is a detonator 2b at the front end in the cylindrical inner cavity 2h; the cable 1g passes through the space between the rear end of the piston 2c and the perforated partition plate 2g; the actuating cavity 2i provides a moving space for the piston 2c; a third pin hole 2e is provided on the upper wall surface 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 provided on the lower wall surface of the actuating cavity 2i and the cabin wall of the aircraft 4; among them, the first pin hole 1i, the second pin hole 4a, the third pin hole 2e and the threaded blind hole 2f are coaxially arranged, which are jointly 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. The connecting element 3 includes a shear screw 3a and a spring 3b. The shear screw 3a fixedly connects the separation base 1 and the pyrotechnic actuating mechanism 2 together. The shear screw 3a sequentially passes through the first pin hole 1i on the bottom surface of the stepped 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 surface of the actuating cavity 2i. 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 surface 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, which is convenient for the shear screw 3a to be cut off from the stress groove 3c after being impacted by the piston rod. After the shear screw 3a breaks, the spring 3b releases elastic force to push up the upper half of the shear screw 3a after fracture.

[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 surface of the actuating cavity 2i. During the loading process, the dropout socket 1d is positioned and inserted into the dropout plug on the launch device through the guide groove 1b on the separation base 1 and the guide pin on the launch device, and communication between the launch device and the equipment carried in the aircraft 4 is achieved through the cable 1g at the bottom of the dropout socket 1d.

[0030] After the aircraft 4 is launched, when the initiator 2b in the pyrotechnic actuating mechanism 2 receives the initiation signal, it initiates an explosion, generating gas to push the piston 2c to move backward. During the movement, the rear end of the piston 2c interacts with the wire passing hole 1h on the pyrotechnic actuating mechanism 2 to squeeze the cable 1g, and the cable 1g is cut off by the edge of the wire passing hole 1h, realizing the separation of the cables 1g inside and outside the cabin of the aircraft 4. Then the piston 2c continues to move, and the piston rod impacts 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. At the same time, under the action of the spring 3b, the shear screw 3a is pushed up to avoid jamming caused by the interaction between 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 during the separation process. In addition, after the piston rod breaks the shear screw 3a, if the piston 2c is located at the part where the gas guiding hole communicates with the air jet hole 1f on the cabin wall of the aircraft 4 at this time, the gas generated by the initiator 2b enters the air jet hole 1f from the front end of the piston 2c through the L-shaped gas guiding hole, and acts on the bottom of the separation base 1 from the air jet hole 1f, driving the separation base 1 to quickly leave the aircraft 4, finally realizing the smoothness of the outer surface of the aircraft 4 during flight, reducing resistance and increasing the range of the aircraft.

[0031] In summary, in the present invention, the pyrotechnic actuating mechanism 2 of the pyrotechnic device is mounted against 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. The connecting element 3 passes through the cabin wall and is fixedly connected to the pyrotechnic actuating mechanism 2. The base body 1a of the separation base 1 is molded by a low-density non-metallic material, with high molding efficiency. A tubular metal block 1c is embedded at the guiding groove 1b for docking with the launching device. Its through-type structural form can transfer the impact load during the docking of the guiding pin of the launching device to the cabin of the aircraft 4, reducing the load on the separation base 1. The pyrotechnic actuating mechanism 2 plays a role in unlocking and driving the separation, and has the characteristics of small volume, fast response, and high technology readiness level. Each part is independently processed, and each part is made of common materials and mature processes, and the installation method is simple and fast. It only needs to be assembled with the cabin during the assembly process, and the processability is good.

[0032] The high-load shedding socket base separation device provided by the present invention has been successfully applied to a certain aircraft, which can achieve reliable electrical communication with the launching device and reduce the overall flight resistance by more than 8%. After the 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 foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions recorded in the foregoing embodiments, or perform equivalent replacements for some of the technical features. And these modifications or replacements do not make the essence of the corresponding technical solutions deviate 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 shedding socket base separation device, characterized in that, It includes a separation base (1), an explosive actuating mechanism (2) and a connecting element (3). The separation base (1) is installed on the outer surface of the cabin wall of the aircraft (4), and the explosive actuating mechanism (2) is installed on the inner surface of the cabin wall of the aircraft (4). The separation base (1) and the explosive actuating mechanism (2) are connected by the connecting element (3). A detachable socket (1d) for connecting with a detachable plug on the launching device is provided on the separation base (1), and the alignment connection between the detachable plug and the detachable socket (1d) is assisted by a guiding groove (1b). An initiator (2b) and a piston (2c) are arranged in the explosive actuating mechanism (2). During the process of the piston (2c) being driven to move after the initiator (2b) detonates, the cable (1g) of the detachable socket (1d) and the connecting element (3) are successively cut off, and the gas generated after detonation is guided to the bottom of the separation base (1) through the gas guiding holes on the piston (2c) and the gas ejection holes (1f) on the housing (2a) of the cabin wall of the aircraft (4) and the explosive actuating mechanism (2). The separation base (1) includes a base body (1a). The bottom surface of the base body (1a) is conformal to the outer surface of the aircraft (4). The guiding groove (1b) is provided on the upper surface of the front part of the base body (1a). A square step groove (1e) is provided on the upper surface of the rear part of the separation base (1). The detachable socket (1d) is installed on the step inside the step groove (1e). The cable (1g) at the bottom of the detachable socket (1d) extends into the aircraft (4) through the wire passing hole (1h) penetrating the separation base (1), the cabin wall of the aircraft (4) and the explosive actuating mechanism (2) and is connected to the equipment carried in the aircraft (4). A first pin hole (1i) is provided on the bottom surface of the step groove (1e). The upper surface of the housing (2a) of the explosive actuating mechanism (2) is conformal to the inner surface of the cabin wall of the aircraft (4). The inside of the housing (2a) is divided into a front cylindrical inner cavity (2h) and a rear actuating cavity (2i) by a perforated partition plate (2g). The cylindrical inner 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 plate (2g). The piston (2c) is provided with an L-shaped gas guiding hole, and both ends of the gas guiding hole penetrate the front end face and the side face of the piston (2c). The gas ejection hole (1f) is located below the base body (1a) of the separation base (1).

2. The high-load dropout socket base separation device according to claim 1, characterized in that, A metal block (1c) is embedded in the guiding groove (1b), and the lower end of the metal block (1c) contacts the outer surface of the cabin wall of the aircraft (4).

3. The high-load shedding socket base separation device according to claim 1, characterized in that, There is a detonator (2b) at the front end inside the cylindrical inner cavity (2h); the cable (1g) passes through the space between the rear end of the piston (2c) and the perforated partition plate (2g); a third pin hole (2e) is provided on the upper wall surface 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 provided on the lower wall surface of the actuating cavity (2i) and the cabin wall of the aircraft (4); among them, 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 jointly used 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).

4. The high-load shedding socket base separation device according to claim 3, characterized in that, The connecting element (3) includes a shear screw (3a) and a spring (3b); the shear screw (3a) sequentially passes through the first pin hole (1i) on the bottom surface of the stepped 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 surface of the actuating cavity (2i); 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 surface of the actuating cavity (2i); 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).

5. The high-load shedding socket base separation device according to claim 4, 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), and after the shear screw (3a) breaks, the spring (3b) releases elastic force to push up the upper half part after the shear screw (3a) breaks.

6. The high-load shedding socket base separation device according to claim 5, characterized in that, When the aircraft (4) is being loaded, the separation base (1) and the pyrotechnic actuating mechanism (2) are connected by sequentially passing the shear screw (3a) in the connecting element (3) through the first pin hole (1i), the second pin hole (4a), and the third pin hole (2e), and the lower end of the shear screw (3a) is assembled into the threaded blind hole (2f) on the lower wall surface of the actuating cavity (2i); during the loading process, the drop socket (1d) is positioned and inserted into the drop plug on the launch device through the guide groove (1b) on the separation base (1) and the guide pin on the launch device, and communication between the launch device and the equipment carried in the aircraft (4) is achieved through the cable (1g) at the bottom of the drop socket (1d).

7. The high-load shedding socket base separation device according to claim 5, characterized in that, After the aircraft (4) is launched, when the initiator (2b) in the pyrotechnic actuating mechanism (2) receives the initiation signal, it detonates, generating gas to push the piston (2c) to move rearward. During the movement, the rear end of the piston (2c) interacts with the wire passing hole (1h) on the pyrotechnic actuating mechanism (2) to squeeze the cable (1g), and the cable (1g) is cut by the edge of the wire passing hole (1h), realizing the separation of 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 (3a) is pushed up under the action of the spring (3b); in addition, after the piston rod breaks the shear screw (3a), at this time the piston (2c) is located at the part where the gas guiding hole communicates with the gas jet hole (1f) on the cabin wall of the aircraft (4), then the gas generated by the initiator (2b) enters the gas jet hole (1f) from the front end of the piston (2c) through the L-shaped gas guiding hole, and acts on the bottom of the separation base (1) from the gas jet hole (1f), driving the separation base (1) to quickly leave the aircraft (4).

8. An aircraft, characterized in that, The aircraft is connected to the drop plug on the launch device by using the high-load drop socket base separation device according to any one of claims 1-7.

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