Aerodynamic pusher device and system for preventing rapid drop in air pressure

Abstract

The application provides a kind of air pressure rapid drop prevention pneumatic push-pull device and system, it is related to aircraft technical field, the push-pull device includes base and push cylinder, one end of the base is provided with a limiting end face, a gas delivery hole is arranged in the middle of the limiting end face, the push cylinder is connected to the other end of the base, including outer cylinder, inner cylinder, end head, push piece and spring, outer cylinder is cylindrical structure, the rear end of outer cylinder is sealingly connected to the base, a coaxial inner cylinder is slidingly connected in the outer cylinder, the inner cylinder reciprocates in the outer cylinder to make the front part of the inner cylinder extend or retract into the outer cylinder;The inner cavity of the inner cylinder is in communication with the inner cavity of the outer cylinder;A push piece is arranged in the middle of the inner cavity of the inner cylinder, the push piece is sealingly engaged with the inner cavity of the inner cylinder and slidingly connected, a spring is installed between the inner cylinder and the inner wall of the front end of the inner cavity of the inner cylinder.Solve the existing separation device air pressure rapid drop and lead to insufficient thrust, gas cylinder installation after leakage and air pressure shortage and other key problems.

Description

Technical Field

[0001] This application belongs to the field of aircraft technology, specifically a pneumatic thrust device and system for preventing rapid air pressure drop. Background Technology

[0002] Non-pyrotechnic pneumatic separation systems, as an advanced aircraft separation method, are used for the separation of various aircraft components. Compared to traditional solid explosives, which generate large impulses, pose safety hazards, and may produce pollution during operation, potentially affecting the aircraft's trajectory, non-pyrotechnic pneumatic separation devices significantly improve efficiency. While mechanical separation springs do not produce pollution and offer higher reliability, non-pyrotechnic pneumatic separation systems significantly reduce impact loads, improve the aircraft's impact environment, eliminate safety hazards, reduce environmental pollution, and are reusable.

[0003] However, existing non-pyrotechnic aerodynamic separation systems also have drawbacks: they have a smaller separation impulse, are heavier, and have a greater impact on the payload capacity of the aircraft.

[0004] Current pneumatic separation systems mostly utilize high-pressure gas as an energy source. The gas expands through a nozzle, converting pressure energy into velocity energy to generate impulse. However, as the gas is expelled, the pressure decreases, leading to a rapid reduction in thrust, which becomes smaller and more unstable. The rapid pressure drop within the thrust device after separation can also negatively impact the thrust effect in the short term. This is a drawback in separation; insufficient thrust could prevent the aircraft from separating as planned, potentially causing even greater problems. Secondly, the pressure inside the gas cylinders in most pneumatic separation systems may leak due to improper placement or other reasons. Finally, using solenoid valves can better adapt to high-pressure conditions, improving the overall system performance of the pneumatic separation system. Summary of the Invention

[0005] This application provides a pneumatic thruster and system for preventing rapid air pressure drop, employing the following technical solution: A pneumatic thruster for preventing rapid pressure drop, comprising: The base has a limiting end face at one end, and an air inlet is provided in the middle of the limiting end face. A push cylinder is connected to the other end of the base. The specific structure of the push cylinder includes an outer cylinder, an inner cylinder, an end head, a push plate, and a first spring. The outer cylinder is a cylindrical structure, and its rear end is sealed to the base. An inner cylinder is slidably connected coaxially inside the outer cylinder. The inner cylinder slides back and forth inside the outer cylinder so that its front end can extend or retract into the outer cylinder. The inner cylinder is a cylindrical structure with a closed front end and an open rear end. The inner cavity of the inner cylinder is connected to the inner cavity of the outer cylinder, and the gas injected by the base can fill the inner cavity of the inner cylinder. A push plate is provided in the middle of the inner cavity of the inner cylinder. The push plate is sealed and slidably connected to the inner cavity of the inner cylinder. A first spring is installed between the inner cylinder and the inner wall of the front end of the inner cavity of the inner cylinder.

[0006] By adopting the above technical solution, as the internal air pressure of the pushing device changes, the inner cylinder slides coaxially back and forth within the outer cylinder, thereby changing the overall length of the pushing cylinder. The innovation of this technical solution also lies in the fact that the pushing plate is slidably connected inside the inner cavity, and the gas injected into the base can fill the inner cavity between the inner cylinder and the base. When the air pressure fills the inner cavity, the air pressure drives the pushing plate to move, thereby squeezing the spring and causing it to deform. At the same time, the spring always maintains its restoring force after deformation, which can drive the pushing plate to squeeze the gas in the inner cavity to move, thereby slowing down the rate of air pressure change inside the pushing device and outputting a more stable and longer-lasting thrust.

[0007] Preferably, the inner cylinder has an end head connected to its front end center, an end cap is fitted onto the front end of the end head, and a nut is fixed to the rear of the end cap, with the nut securely connected to the rear of the end head.

[0008] By adopting the above technical solution, the setting of the end head and end cap can make the impact force output by the punching device more concentrated, and the separation force is generated instantaneously through the impact of the end cap.

[0009] Preferably, the outer rear edge of the inner cylinder is provided with three raised rings spaced apart, and a sealing ring is embedded between adjacent raised rings.

[0010] By adopting the above technical solution, the contact surface between the inner cylinder and the outer cylinder is provided with double sealing rings, which effectively ensures the sealing of the contact surface between the inner cylinder and the outer cylinder, prevents gas leakage, and thus ensures the air pressure inside the pushing device.

[0011] Preferably, the base includes a cylindrical wall and a bottom plate. The cylindrical wall is a cylindrical structure. The bottom plate is fixedly installed at one axial end of the cylindrical wall. An air inlet is provided at the center of the bottom plate. Four bolt holes are provided at intervals on the outer periphery of the bottom plate.

[0012] By adopting the above technical solution, the base plate structure of the punching device ensures the firmness of the installation and prevents impact vibration from affecting the operation of the device.

[0013] A pneumatic thrust system for preventing rapid pressure drop, comprising: The thrust device is a pneumatic thrust device for preventing rapid air pressure drop as described above, and the thrust device is fixed inside the first-stage aircraft. An inflation assembly is connected to the thrust device via an air pipe. The inflation assembly is used to inflate the thrust device. The inflation assembly is reusable and is also fixed inside the first-stage aircraft. A separation device is fixed inside the second-stage aircraft. The separation device and the thrust device are arranged opposite each other and are not connected. The distance between the separation device and the thrust device is less than the deformation length of the thrust device.

[0014] By adopting the above technical solutions, both the pushing and punching device and the air-filling device can be reused multiple times, greatly saving costs. The separation device has a reasonable structural design and can output reverse thrust synchronously with the pushing and punching device, thereby making the separation efficiency higher.

[0015] Preferably, the inflation assembly includes a gas cylinder, a pressure sensor, a one-way valve, a four-way valve, and an electric explosion valve. The four channels of the four-way valve are respectively connected to the gas cylinder, the pressure sensor, the one-way valve, and the electric explosion valve through air pipes. The other end of the electric explosion valve is connected to the air supply port of the push-pump device through an air pipe. The gas cylinder is fixed inside the aircraft. The gas cylinder can be deflated and can be refilled after installation. The pressure sensor can display the pressure inside the gas cylinder and the filling assembly pipeline. The electric explosion valve is connected to the control system via a circuit. An electric explosion tube is installed inside the electric explosion valve. The electric explosion tube can self-explode, thereby allowing gas to flow through the gas pipes at both ends of the electric explosion valve. One end of the electric explosion valve is connected to a four-way valve, and the other end of the electric explosion tube is connected to a push-pump device. A check valve is a valve that allows external air to flow in one direction to a four-way pipe.

[0016] By adopting the above technical solution, the inflation device can accurately detect that the gas cylinder has reached the design pressure during inflation, ensuring the effectiveness of the operation. Moreover, the inflation and deflation can be used multiple times. Only the electric explosion valve needs to be replaced before the second use. It not only has a good separation effect, but also low subsequent costs.

[0017] Preferably, the separation device includes a shell, an electric detonator, and a push rod assembly. The shell is a cylindrical structure. One end of the shell is provided with a limiting end face, and a through hole is provided at the center of the limiting end face. An electric detonator is fixedly installed inside the other end of the shell. A push rod assembly is slidably arranged inside the shell between the electric detonator and the limiting end face. The push rod in the push rod assembly is coaxially arranged with the through hole, and the push rod can extend out of the through hole.

[0018] By adopting the above technical solution, the separation device is equipped with a push rod inside. During the operation, the push rod moves in the opposite direction to the end of the push-impact device, resulting in a strong impact.

[0019] Preferably, the push rod assembly includes a push rod, a telescopic rod, and a second spring. One circumferential end of the push rod is fixedly connected to the outer sleeve of the telescopic rod, and the shape of the outer sleeve matches the cross-sectional shape of the inner cavity of the outer shell. A sliding hole perpendicular to the push rod is provided inside the outer sleeve of the telescopic rod. Two inner rods of the telescopic rod are symmetrically arranged in the sliding hole, and the inner rods are slidably connected to the outer sleeve. The second spring abuts against the sliding hole between the two inner rods, and the second spring maintains a compressed state to keep the telescopic rod in a preloaded state of extension. A guide step is provided on the inner wall of the outer shell near the limiting end face. The end of the guide step near the electric detonator is a conical guide slope, and the end of the guide step near the limiting end face is a circular end face perpendicular to the central axis of the outer shell. The distance between the circular end face and the limiting end face is sufficient to accommodate the telescopic rod of the push rod assembly, while ensuring that the push rod can extend to the outside of the limiting end face.

[0020] By adopting the above technical solution, the push rod assembly is equipped with an elastic telescopic rod structure to maintain the stability of the push rod's movement during sliding and ensure that the push rod accurately collides with the pushing device.

[0021] Preferably, the inner wall of the middle part of the outer shell is provided with another guide step, the end of the guide step near the electric detonator is a conical guide slope, and the end of the guide step near the limiting end face is a ring structure perpendicular to the central axis of the outer shell.

[0022] Preferably, a first annular magnetic sheet is fixedly mounted on the outer periphery of the through hole on the inner side of the limiting end face of the housing, and a second magnetic sheet is fixedly mounted on the side of the push rod assembly near the limiting end face. The first magnetic sheet and the second magnetic sheet are matched in shape and their magnetic poles attract and cooperate with each other. Under the attraction of the magnetic sheets, it can also be ensured that the push rod assembly can move on the predetermined track.

[0023] In summary, the technical solutions provided in the embodiments of this application have the following technical effects or advantages: This application provides a pneumatic separation device and separation system to prevent the rapid drop in air pressure inside the push-impact device, solving key problems such as the rapid drop in air pressure inside the existing separation device leading to insufficient thrust, air leakage and insufficient air pressure after gas cylinder installation, and poor compatibility and insufficient performance of key valves. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of the thrusting device.

[0025] Figure 2 yes Figure 1 A sectional view along line AA.

[0026] Figure 3 This is a schematic diagram of the inner cylinder structure in the push cylinder.

[0027] Figure 4 This is a three-dimensional structural diagram of the thrusting device.

[0028] Figure 5 This is a schematic diagram of the separation system structure for installing this push-impact device.

[0029] Figure 5 This is a schematic diagram of the connection structure of the separation system.

[0030] Figure 6 This is a schematic diagram of the external structure of the separation device.

[0031] Figure 7 yes Figure 6 BB-direction sectional view.

[0032] Figure 8 This is a cross-sectional view of the separation device in another operating state.

[0033] Meaning of the labels in the attached figures: 1. Wearing a hat; 2. Push cylinder; 21. End; 22. Inner cylinder; 23. First spring; 24. Outer cylinder; 25. Push plate; 26. Convex ring; 3. Base; 31. Cylinder wall; 32. Base plate; 33. Air inlet; 34. Bolt holes; 4. Sealing ring; 5. Nuts; 6. Separation device; 61. Outer shell; 62. Electric detonator; 63. Telescopic rod; 64. Top rod; 65. Guide step; 66. First magnetic plate; 67. Through hole; 68. Second magnetic plate; 69. Second spring; Detailed Implementation

[0034] To enable those skilled in the art to better understand the technical solutions in this specification, the technical solutions in the embodiments of this specification will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments.

[0035] A pneumatic thruster for preventing rapid pressure drop, see [link / reference]. Figure 1 As shown, it includes a base 3 and a push cylinder 2. The base 3 has a cavity inside. One end of the base 3 is sealed and connected to the push cylinder 2. The other end of the base 3 is provided with a limit end face. A gas supply hole 33 is provided in the middle of the limit end face. The gas supply hole 33 is used to connect to a gas source. Gas enters the base 3 through the gas supply hole 33, which can drive the push cylinder 2 to extend. See Figure 2As shown, the push cylinder 2 includes an outer cylinder 24, an inner cylinder 22, an end 21, a push plate 25, and a first spring 23. The outer cylinder 24 has a cylindrical structure. The rear end of the outer cylinder 24 is sealed and connected to the base 3. An inner cylinder 22 is slidably connected to the outer cylinder 24. The front part of the inner cylinder 22 can extend out of the outer cylinder 24. When the inner cylinder 22 slides back and forth within a limited length inside the outer cylinder 24, the front part of the inner cylinder 22 can extend out or retract into the outer cylinder 24, thereby changing the length of the push cylinder 2. See Figure 2 , 3 As shown, an end head 21 is coaxially fixed at the front center of the inner cylinder 22. The end head 21 is used to impact and collide with the separation device 6 of the other stage of the aircraft to achieve separation. In order to enhance the strength of the end head 21 and extend its service life, an end cap 1 is fitted at the front end of the end head 21. The rear part of the end cap 1 is connected to a nut 5. The nut 5 is fixedly connected to the root of the end head 21. The end cap 1 is used for direct contact and collision. The end head 21 is made of a strong material, and the end cap 1 can be replaced so that the device can be used multiple times.

[0036] See Figure 2 As shown, the inner cylinder 22 is a cylindrical structure with a closed front end and an open rear end. The inner cavity of the inner cylinder 22 is connected to the inner cavity of the outer cylinder 24, and the gas injected by the base 3 can fill the inner cavity of the inner cylinder 22. A pusher plate 25 is provided in the middle of the inner cavity of the inner cylinder 22. The pusher plate 25 is sealed and slidably connected to the inner cavity of the inner cylinder 22. A first spring 23 is installed between the inner cylinder 22 and the inner wall of the front end of the inner cavity. When the gas pressure fills the inner cavity, the gas pressure drives the pusher plate 25 to move, thereby squeezing the first spring 23 and deforming it. During disassembly, when the pressure of the gas decreases, the restoring force of the first spring 23 can drive the pusher plate 25 to squeeze the gas in the inner cavity, thereby maintaining a stable thrust of the gas pressure in the inner cavity on the inner cylinder 22, so that the gas pressure decreases slowly and the thrust remains stable.

[0037] See Figure 3 As shown, three raised rings 26 are spaced apart on the rear outer edge of the inner cylinder 22, and a sealing ring 4 is embedded between adjacent raised rings 26, thereby ensuring the sealing between the inner cylinder 22 and the outer cylinder 24 and ensuring the thrust of the internal air pressure.

[0038] See Figure 2 As shown, the base 3 includes a cylindrical wall 31 and a bottom plate 32. The cylindrical wall 31 is a cylindrical structure. The bottom plate 32 is fixed at one axial end of the cylindrical wall 31. The bottom plate 32 is a square flat plate structure that completely encloses the end of the cylindrical wall 31. An air inlet 33 is provided at the center of the bottom plate 32. The air inlet 33 communicates with the cavity inside the cylindrical wall 31.

[0039] See Figure 4 As shown, in order to facilitate the fixing of the punching device, four bolt holes 34 are evenly spaced on the base plate 32.

[0040] See Figure 5 As shown, this embodiment also provides a pneumatic separation system using the above-mentioned pneumatic thrusting device, including a separation device 6, a thrusting device, and an inflation assembly. The inflation assembly is connected to the thrust device. The thrust device and the separation device 6 are respectively fixed inside the two-stage aircraft that need to be separated. The separation device 6 and the thrust device are coaxially opposite each other and there is no connection between them. When the inflation assembly inflates the thrust device, the thrust device is driven by air pressure to impact the separation device 6, thereby separating the separation device 6 from the thrust device, and then driving the two-stage aircraft to separate.

[0041] The inflation assembly specifically includes a gas cylinder, a pressure sensor, a one-way valve, a four-way valve, and an electric explosion valve. The four channels of the four-way valve are respectively connected to the gas cylinder, the pressure sensor, the one-way valve, and the electric explosion valve through air pipes. The other end of the electric explosion valve is connected to the air supply port 33 of the push-pump device through an air pipe. The gas cylinder is stably fixed inside the aircraft. There are fixed brackets and anti-vibration structures such as thrust plates 25 between the gas cylinder and the aircraft. The gas cylinder can be filled and released multiple times. The pressure sensor can display the pressure inside the gas cylinder and the filling assembly lines; The electric explosion valve is connected to the control system via a circuit. An electric explosion tube is installed inside the electric explosion valve. When the electric explosion tube receives an electrical control signal, it can self-detonate, thereby allowing gas to flow through the gas pipes at both ends of the electric explosion valve. One end of the electric explosion valve is connected to a four-way valve, and the other end of the electric explosion valve is connected to a push-pump device.

[0042] A check valve is a valve that allows external air to flow in one direction to a four-way pipe.

[0043] The gas cylinders shown in the attached diagram of this embodiment are two connected in parallel by gas pipes. Depending on the actual design requirements, there can be one or more gas cylinders.

[0044] The pusher device shown in the attached diagram of this embodiment consists of two gas cylinders connected in parallel. Depending on the actual design requirements, there can be one or more gas cylinders.

[0045] See appendix Figure 6 , 7 The diagram shows the structure of the separation device 6. The separation device 6 includes a housing 61, an electric detonator 62, and a push rod assembly. The housing 61 is a cylindrical structure. One end of the housing 61 is provided with a limiting end face, and a through hole 67 is provided at the center of the limiting end face. An electric detonator 62 is fixedly installed inside the other end of the housing 61. The electric detonator 62 is connected to the control system through a wire. A push rod assembly is slidably arranged inside the housing 61 between the electric detonator 62 and the limiting end face. The push rod 64 in the push rod assembly is coaxially arranged with the through hole 67 and can extend out of the through hole 67.

[0046] See Figure 7 , Figure 8 As shown, the push rod assembly includes a push rod 64, a telescopic rod 63, and a second spring 69. One circumferential end of the push rod 64 is fixedly connected to the outer sleeve of the telescopic rod 63, and the shape of the outer sleeve matches the cross-sectional shape of the inner cavity of the outer shell 61. A sliding hole perpendicular to the push rod 64 is provided inside the outer sleeve of the telescopic rod 63. Two inner rods of the telescopic rod 63 are symmetrically arranged in the sliding hole and are slidably connected to the outer sleeve. A second spring 69 abuts in the sliding hole between the two inner rods. The second spring 69 is kept in a compressed state to keep the telescopic rod 63 in a pre-tensioned state of extension.

[0047] A guide step 65 is provided on the inner wall of the outer shell 61 near the limiting end face. The end of the guide step 65 near the electric detonator is a conical guide slope, and the end of the guide step 65 near the limiting end face is a circular end face perpendicular to the central axis of the outer shell 61. The distance between the circular end face and the limiting end face is sufficient to accommodate the telescopic rod 63 of the push rod assembly, while ensuring that the push rod 64 can extend to the outside of the limiting end face.

[0048] To ensure the coaxiality of the movement of the push rod assembly, another guide step 65 is provided on the inner wall of the middle part of the housing 61. The end of the guide step 65 near the electric detonator is a conical guide slope, and the end of the guide step 65 near the limiting end face is a ring structure perpendicular to the central axis of the housing 61. Depending on the length of the housing 61, multiple guide steps 65 can also be provided in the design.

[0049] See Figure 7 , Figure 8 As shown, a first annular magnetic sheet 66 is fixedly mounted on the outer periphery of the through hole 67 on the inner side of the limiting end face of the outer shell 61, and a second magnetic sheet 68 is fixedly mounted on the side of the push rod assembly near the limiting end face. The first magnetic sheet 66 and the second magnetic sheet 68 are matched in shape and their magnetic poles attract and cooperate with each other, further ensuring that the push rod assembly can be aligned with the through hole 67.

[0050] The electric detonator 62 is existing technology; it is a device that uses electrical energy to trigger an explosion, also known as an electric detonator or electric detonator. The separation device 6 is for single use only.

[0051] The working steps of this pneumatic separation system are as follows: S1 First, fix the inflation assembly, the thrust device, and the separation device 6 to the preset positions in the cabin, and connect the air pipes; S2 inflates the air-filled component to reach the preset pressure; An external gas source fills the gas cylinder through a one-way valve. After passing through a four-way fitting, the gas enters the gas cylinder. At the same time, a pressure sensor can monitor the gas pressure in the system in real time. This pressure is the gas pressure inside the gas cylinder. When the gas pressure in the gas cylinder reaches the design pressure, the filling stops. At this time, the electric explosion valve is in the locked state, and the gas will not enter the push-pump device. When S3 needs to be separated, the control system issues a working command, and the inflation component quickly inflates the push-flush device; When the electric explosion valve is activated, gas flows through the inner cavity of the electric explosion valve, and the gas in the gas cylinder is quickly filled into the pusher device. S4 The pusher device is activated by the pneumatic action. The pneumatic pressure drives the inner cylinder 22 to extend out of the outer cylinder 24 and quickly extend towards the separation device 6. The pusher device then hits the separation device 6. During this process, the pusher plate 25 moves slower than the inner cylinder 22 under the action of the first spring 23. The gas space in the inner cavity space connected to the base 3 expands at a slower speed than in the structure without springs. At the moment the inner cylinder 22 is pushed out, the expansion speed of the inner cavity space slows down, and the amount of gas remains unchanged, so that the gas pressure in the cavity will not drop sharply, and the stable output of thrust is maintained.

[0052] As the S5 thrusting device collides with the separating device 6, the separating device 6 generates a thrust opposite to that of the thrusting device. Specifically, the electric detonator inside the separation device 6 is activated, and the push rod 64 inside the separation device 6 moves towards the pushing device, extending the push rod 64 out of the outer casing 61 of the separation device 6. When the S6 top rod 64 collides with the end cap 1, the powerful impact causes the separation device 6 to separate from the thrust device in the opposite direction, thereby driving the two stages of the aircraft to separate.

[0053] The foregoing description is merely an exemplary embodiment of this disclosure and should not be construed as limiting the scope of this disclosure. Any equivalent changes and modifications made in accordance with the teachings of this disclosure shall still fall within the scope of this disclosure. Those skilled in the art will readily conceive of other embodiments of this disclosure upon considering the specification and the disclosure of practical truths. This application is intended to cover any variations, uses, or adaptations of this disclosure that follow the general principles of this disclosure and include common knowledge or customary techniques in the art not described in this disclosure. The specification and embodiments are considered exemplary only.

Claims

1. A pneumatic thrust system for preventing rapid air pressure drop, characterized in that, include: A thruster device, fixed within the first-stage aircraft, comprising: The base (3) has a limiting end face at one end, and an air inlet (33) is provided in the middle of the limiting end face. A push cylinder (2) is connected to the other end of the base (3). The specific structure of the push cylinder (2) includes an outer cylinder (24), an inner cylinder (22), an end (21), a push plate (25), and a first spring (23). The outer cylinder (24) is a cylindrical structure. The rear end of the outer cylinder (24) is sealed to the base (3). An inner cylinder (22) is coaxially slidably connected inside the outer cylinder (24). The inner cylinder (22) slides back and forth inside the outer cylinder (24). The movement allows the front part of the inner cylinder (22) to extend or retract into the outer cylinder (24); the inner cylinder (22) is a cylindrical structure with a closed front end and an open rear end, and the inner cavity of the inner cylinder (22) is connected to the inner cavity of the outer cylinder (24); a push plate (25) is provided in the middle of the inner cavity of the inner cylinder (22), the push plate (25) is sealed and slidably connected to the inner cavity of the inner cylinder (22), and a first spring (23) is installed between the push plate (25) and the inner wall of the front end of the inner cavity of the inner cylinder (22); An inflation assembly is connected to the thrust device via an air pipe. The inflation assembly is used to inflate the thrust device. The inflation assembly is reusable and is also fixed inside the first-stage aircraft. Separation device (6), the separation device (6) is fixed inside the second stage aircraft, the separation device (6) is arranged opposite to the thrust device and there is no connection between the two, the distance between the separation device (6) and the thrust device is less than the deformation length of the thrust device; The separation device (6) includes a shell (61), an electric detonator (62), and a push rod assembly. The shell (61) is a cylindrical structure. One end of the shell (61) is provided with a limiting end face, and a through hole (67) is provided at the center of the limiting end face. An electric detonator (62) is fixedly installed inside the other end of the shell (61). A push rod assembly is slidably arranged inside the shell (61) between the electric detonator (62) and the limiting end face. The push rod (64) in the push rod assembly is coaxially arranged with the through hole (67), and the push rod (64) can extend out from the through hole (67).

2. The pneumatic thrust system for preventing rapid air pressure drop according to claim 1, characterized in that, The inner cylinder (22) has an end head (21) connected to its front end center. An end cap (1) is fitted on the front end of the end head (21). A nut (5) is fixed to the rear of the end cap (1). The nut (5) is fixedly connected to the rear of the end head (21).

3. The pneumatic thrust system for preventing rapid air pressure drop according to claim 1, characterized in that, The inner cylinder (22) has three raised rings (26) spaced apart on its rear outer edge, and a sealing ring (4) is embedded between each adjacent raised ring (26).

4. The pneumatic thrust system for preventing rapid air pressure drop according to claim 1, characterized in that, The base (3) includes a cylindrical wall (31) and a bottom plate (32). The cylindrical wall (31) is a cylindrical structure. The bottom plate (32) is fixed at one axial end of the cylindrical wall (31). An air supply hole (33) is provided at the center of the bottom plate (32). Four bolt holes (34) are provided at intervals on the outer periphery of the bottom plate (32).

5. The pneumatic thrust system for preventing rapid air pressure drop according to claim 1, characterized in that, The inflation assembly includes a gas cylinder, a pressure sensor, a one-way valve, a four-way valve, and an electric explosion valve. The four channels of the four-way valve are respectively connected to the gas cylinder, the pressure sensor, the one-way valve, and the electric explosion valve through air pipes. The other end of the electric explosion valve is connected to the air supply port (33) of the push-pump device through an air pipe. The gas cylinder is fixed inside the aircraft. The gas cylinder can be deflated and can be refilled after installation. The pressure sensor can display the pressure inside the gas cylinder and the filling assembly pipeline. The electric explosion valve is connected to the control system via a circuit. An electric explosion tube is installed inside the electric explosion valve. The electric explosion tube can self-explode, thereby allowing gas to flow through the gas pipes at both ends of the electric explosion valve. One end of the electric explosion valve is connected to a four-way valve, and the other end of the electric explosion tube is connected to a push-pump device. A check valve is a valve that allows external air to flow in one direction to a four-way pipe.

6. The pneumatic thrust system for preventing rapid air pressure drop according to claim 1, characterized in that, The top rod assembly includes a top rod (64), a telescopic rod (63), and a second spring (69). One circumferential end of the top rod (64) is fixedly connected to the outer sleeve of the telescopic rod (63), and the shape of the outer sleeve matches the cross-sectional shape of the inner cavity of the outer shell (61). A sliding hole perpendicular to the top rod (64) is provided inside the outer sleeve of the telescopic rod (63). Two inner rods of the telescopic rod (63) are symmetrically arranged in the sliding hole, and the inner rods are slidably connected to the outer sleeve. The second spring (69) abuts against the sliding hole between the two inner rods, and the second spring (69) maintains a compressed state to keep the telescopic rod (63) in a pre-tensioned state of elongation. A guide step (65) is provided on the inner wall of the outer shell (61) near the limiting end face. The end of the guide step (65) near the electric detonator is a conical guide slope, and the end of the guide step (65) near the limiting end face is a circular end face perpendicular to the central axis of the outer shell (61). The distance between the circular end face and the limiting end face is sufficient to accommodate the telescopic rod (63) of the top rod assembly, while ensuring that the top rod (64) can extend to the outside of the limiting end face.

7. The pneumatic thrust system for preventing rapid air pressure drop according to claim 6, characterized in that, Another guide step (65) is provided on the inner wall of the middle part of the outer shell (61). The end of the guide step (65) near the electric detonator is a conical guide slope, and the end of the guide step (65) near the limiting end face is a ring structure perpendicular to the central axis of the outer shell (61).

8. The pneumatic thrust system for preventing rapid air pressure drop according to claim 1, characterized in that, A first annular magnetic sheet (66) is fixedly mounted on the outer periphery of the through hole (67) on the inner side of the limiting end face of the outer shell (61), and a second magnetic sheet (68) is fixedly mounted on the side of the top rod assembly near the limiting end face. The first magnetic sheet (66) and the second magnetic sheet (68) are shaped to match each other and their magnetic poles attract and cooperate with each other.

Images