Pneumatic ejection launching device

Abstract

The utility model discloses a pneumatic ejection launching device which comprises a launching cylinder and a piston arranged in the launching cylinder. The launching barrel comprises a barrel body and a buffering section arranged at the front end of the barrel body, a weakening structure is arranged on the buffering section in the circumferential direction of the buffering section, a blocking structure used for limiting movement of the piston is arranged in the buffering section, and when the piston moves to the position of the blocking structure and is blocked, the piston is blocked. And the buffer section is damaged at the position of the weakening structure under the action of the piston. The buffer section is arranged at the front end of the launch canister body to limit the piston to move along with the aircraft, so that the aircraft can be quickly separated from the piston after being launched out of the launch canister, and the influence on flight of the aircraft is reduced.

Description

Technical Field

[0001] The utility model belongs to the technical field of aircraft, and in particular relates to a pneumatic ejection launching device for launching an aircraft. Background Art

[0002] In order to meet the launch requirements of future micro-UAVs and cruise missiles, pneumatic ejection technology has become an important research direction; pneumatic ejection launchers can meet the needs of individual soldiers, vehicles, aircraft and ships. As an important part of the launcher, the pneumatic ejection launch tube can provide ejection power for the missile body and play the role of storage, transportation and ejection guidance.

[0003] Existing pneumatic ejection launch devices usually have the following problems: when the pneumatic ejection launch tube is launched, the piston is ejected out of the tube together with the UAV / cruise missile, and is separated from the missile body by the air resistance of the piston itself. The separation time is long, the UAV tail wing starts to rotate late, and the posture is prone to instability, affecting the normal launch of the UAV; a pull rope or metal buffer is used in the launch tube to keep the piston in the launch tube during launch. The use of a pull rope buffer has high requirements on the structural strength of the launch tube and the pull rope, and the reuse rate of the pull rope is low, and it is difficult to tie the rope when reloading; the use of a metal buffer is costly, the process is complicated, and it is inconvenient to install and disassemble. Utility Model Content

[0004] The utility model aims to provide a pneumatic ejection launching device to solve the above-mentioned problems existing in the existing pneumatic ejection launching device during the pneumatic ejection process.

[0005] The utility model is realized by the following technical solutions:

[0006] A pneumatic ejection launching device comprises a launching tube and a piston arranged in the launching tube;

[0007] The launching tube comprises a tube body and a buffer section arranged at the front end of the tube body, a weakening structure is arranged on the buffer section along its circumferential direction, a blocking structure for limiting the movement of the piston is arranged in the buffer section, when the piston moves to the position of the blocking structure and is blocked, the buffer section is destroyed at the position of the weakening structure under the action of the piston.

[0008] In some embodiments, the weakening structure is a weakening groove arranged on the buffer segment along the circumference of the buffer segment, and the blocking structure is arranged outside the weakening groove; or

[0009] The buffer section includes a connecting portion and a buffer portion, the connecting portion is used to be connected to the cylinder, the blocking structure is arranged on the buffer portion, the weakening structure is a plurality of breaking ribs arranged between the connecting portion and the buffer portion, the connecting portion and the buffer portion are connected by the breaking ribs, and the breaking ribs are arranged circumferentially at the ends of the connecting portion and the buffer portion.

[0010] In some embodiments, the blocking structure is a plurality of blocks disposed on the buffer segment and located outside the weakened structure.

[0011] In some embodiments, the blocking surface on the stopper is inclined toward one side of the inner part of the cylinder along the axial direction of the cylinder.

[0012] In some embodiments, the buffer section and the cylinder are detachably connected.

[0013] In some embodiments, an air inlet connector is provided at the bottom of the cylinder.

[0014] In some embodiments, an exhaust valve is provided at the bottom of the cylinder.

[0015] In some embodiments, a guide and limit structure is provided between the piston and the launch tube, and the guide and limit structure is configured to enable the piston to move linearly only along the axial direction of the launch tube.

[0016] In some embodiments, an electrical connection connector assembly is provided on the piston, and the electrical connection connector assembly includes a first male connector and a first female connector connected by a cable, the first female connector is used to connect to a second male connector provided on the aircraft, and the first male connector is used to connect to a second female connector provided at the bottom of the cylinder.

[0017] In some embodiments, a limit support column is provided on the piston, and a limit piece capable of rotationally limiting the aircraft is provided at the end of the limit support column.

[0018] Compared with the prior art, the utility model has the following advantages and beneficial effects:

[0019] 1) By setting a buffer section at the front end of the launch tube body, the piston is restricted from moving with the aircraft, so that the aircraft can be quickly separated from the piston after being ejected from the launch tube, reducing the impact on the flight of the aircraft.

[0020] 2) The buffer section has a simple structure and can be quickly installed and replaced on the cylinder. While providing buffering and separation effects to the piston, it has little impact on the cylinder, so that the cylinder and the piston can be recycled repeatedly, reducing the launch cost.

[0021] 3) By configuring the structure of the piston, it can be stably connected and limited to the aircraft, ensuring the stability of the aircraft's movement during the launch process; at the same time, an electrical connection component is arranged on the piston to realize the charging operation of the UAV in the launch tube, further expanding its performance. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the technical solutions of the embodiments of the utility model, the drawings in the embodiments will be briefly introduced below. It should be understood that the following drawings only show certain embodiments of the utility model and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other related drawings can be obtained based on these drawings without creative work.

[0023] Figure 1 The utility model is a schematic diagram of the structure of the pneumatic ejection launching device.

[0024] Figure 2 This is a cross-sectional view of the structure of the pneumatic ejection launching device of the utility model.

[0025] Figure 3 for Figure 2 Partial schematic diagram at point A in the middle.

[0026] Figure 4 This is a schematic diagram of the installation structure of the UAV in the device.

[0027] Figure 5 for Figure 4 Partial schematic diagram at point B in the middle.

[0028] Figure 6 It is a schematic diagram of the structure of the buffer section in the device of the utility model.

[0029] Figure 7 This is a schematic diagram of the piston structure in the device of the utility model.

[0030] Figure 8 It is a cross-sectional view of the piston structure in the device of the utility model.

[0031] in:

[0032] 10. Launch tube, 11. Cylinder body, 111. Guide rail, 12. Buffer section, 121. Connecting part, 122. Buffer part, 123. Breaking rib, 13. Stopper, 131. Blocking surface, 14. Inlet connector, 15. Exhaust valve, 16. Second female connector;

[0033] 20. Piston, 21. Piston body, 211. Groove, 22. Skirt sealing ring, 23. Electrical connection mounting column, 241. First male connector, 242. First female connector, 25. Limiting support column, 251. Limiting member;

[0034] 30. UAV, 31. Second male connector. DETAILED DESCRIPTION

[0035] In order to make the purpose, technical solutions and advantages of the embodiments of the utility model clearer, the technical solutions in the embodiments of the utility model will be clearly and completely described below in conjunction with the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments.

[0036] Reference Figure 1 , Figure 2 and Figure 2 , a pneumatic ejection device, comprising a launching tube 10 and a piston 20 arranged in the launching tube;

[0037] The launching tube 10 comprises a tube body 11 and a buffer section 12 arranged at the front end of the tube body, a weakening structure is arranged on the buffer section along its circumferential direction, a blocking structure for limiting the movement of the piston is arranged in the buffer section 12, when the piston moves to the position of the blocking structure and is blocked, the buffer section is destroyed at the position of the weakening structure under the action of the piston.

[0038] During the launch process, under the action of instantaneous high-pressure airflow, the piston pushes the aircraft to move and ejects the aircraft out of the launch tube. When the piston moves to the blocking structure position, the movement of the piston is restricted, so that the aircraft and the piston can be quickly separated. At the same time, the interaction force between the piston and the buffer section causes the buffer section to be destroyed at the weakened position to absorb the impact force between the piston and the buffer section, providing buffering for the piston, thereby reducing damage to the cylinder and the piston.

[0039] In one embodiment, the weakening structure may be an annular weakening groove arranged on the buffer segment along the circumference of the buffer segment. By setting the annular weakening groove, the structural strength at that position on the buffer segment is reduced. At this time, the blocking structure is arranged on the outside of the weakening groove, so that when the piston is blocked by the blocking structure, the buffer segment is broken and damaged at the position of the weakening groove.

[0040] In one embodiment, if Figure 6 The buffer section 12 is configured to include a connecting portion 121 and a buffer section 122, wherein the connecting portion 121 is connected to the cylinder 11, and specifically, the connecting portion 121 and the cylinder 11 can be threadedly connected to facilitate the installation and replacement of the buffer section on the cylinder. At this time, the blocking structure is arranged on the buffer section 122; the weakening structure on the buffer section 12 is a plurality of breaking ribs 123 arranged between the connecting portion and the buffer section, and the connecting portion 121 and the buffer section 122 are connected by a plurality of breaking ribs 123, and a plurality of breaking ribs 123 are arranged circumferentially at the ends of the connecting portion 121 and the buffer section 122. Based on the same principle of action, when the buffer section is subjected to the impact force of the piston, the breaking ribs are broken, which can also provide a buffer for the piston.

[0041] In one embodiment, the blocking structure is a plurality of blocks 13 disposed on the buffer section and located outside the weakening structure, and the blocks 13 are circumferentially distributed on the inner wall of the buffer section. Of course, the blocking structure can also adopt other conventional structural forms, and while blocking the piston, it should try to avoid affecting the aircraft.

[0042] In one embodiment, a blocking surface 131 is provided on the stopper 13, and the blocking surface 131 is inclined toward one side of the cylinder body along the axial direction of the cylinder body. The blocking surface 131 is set as an inclined inclined surface. When the piston and the stopper interact with each other, the blocking surface 131 converts the impact force of the piston into a radial force in the radial direction and an axial force in the axial direction. The axial force breaks the ribs to absorb part of the impact energy, and the radial force causes the buffering part of the buffer section to be damaged in the circumferential direction, and also absorbs part of the impact energy. At this time, the kinetic energy of the piston can be greatly reduced, and the speed of the piston flying out of the cylinder body can be reduced to facilitate the recovery of the piston. At the same time, it can avoid the piston flying too close to the drone when flying out, which affects the movement of the tail wing of the aircraft.

[0043] Here, both the cylinder and the buffer section can be integrally injection molded with non-metallic composite materials such as PC / ABS. By adjusting the number of breaking ribs, the breaking force when the buffer section is broken can be controlled. By adjusting the density distribution of the breaking ribs at different positions in the circumferential direction, the falling direction of the piston after the piston breaks the breaking ribs can be controlled. At the same time, when the buffer section and the cylinder are connected by threads, the setting of the threads between the two is controlled, so that when the buffer section is installed on the cylinder, the block can be in a suitable position to avoid the block from interfering with the wings of the drone.

[0044] In one embodiment, an air intake connector 14 is provided at the bottom of the barrel 11 to facilitate the connection between the launch barrel and the air supply system. A metal insert may be provided at one end of the air intake connector 14, and the air intake connector is integrally formed and connected to the bottom of the barrel through the metal insert when the barrel is formed, which not only facilitates the connection between the air intake connector and the barrel, but also increases the structural strength of the bottom of the barrel and facilitates the connection and arrangement of other components on the bottom of the barrel.

[0045] In one embodiment, an exhaust valve 15 is provided at the bottom of the cylinder 11. The exhaust valve 15 can be provided to exhaust the gas in the cylinder in time when the piston is installed, so as to facilitate the installation of the piston into the cylinder.

[0046] In one embodiment, the piston 20 includes a piston body 21 and a skirt sealing ring 22 arranged at the end of the piston body. The skirt sealing ring 22 forms a sealing fit with the inner wall of the cylinder, so that a closed environment can be formed between the piston and the cylinder during firing, thereby pushing the piston out of the cylinder under the action of high-pressure gas.

[0047] Reference Figure 2 and Figure 7 As shown, a guide limit structure is provided between the piston and the launch tube, and the guide limit structure is configured to enable the piston to move linearly only along the axial direction of the launch tube. Specifically, as a feasible method, two or more grooves 211 can be provided on the piston body, and a guide rail 111 matching the grooves can be provided on the inner wall of the cylinder 11. Through the cooperation between the groove and the guide rail, the piston can only move linearly along the guide rail in the cylinder while limiting the rotation of the piston in the cylinder. Of course, a protrusion structure can also be provided on the piston body, and then a matching slide groove structure can be provided on the cylinder. Through the cooperation between the protrusion and the slide groove, the same effect as above can also be achieved.

[0048] Existing launch tubes usually do not have the function of charging drones. Usually, the drone needs to be charged before being loaded into the launch tube, which greatly limits the application of the launch device.

[0049] To address this problem, in one embodiment, Figure 4 , Figure 5 and Figure 8 An electrical connection mounting column 23 is provided on the piston body 21 of the piston 20, and an electrical connection connector assembly is provided on the electrical connection mounting column 23. The electrical connection connector assembly includes a first male connector 241 and a first female connector 242 relatively installed on the electrical connection mounting column. The first male connector and the first female connector are connected by a cable, and the cable is arranged in the electrical connection mounting column.

[0050] Correspondingly, the first female connector 242 is arranged on one end of the electrical connection mounting column extending into the cylinder, and is used to cooperate with the second male connector 31 arranged on the drone 30; the first male connector 241 is arranged at one end where the electrical connection mounting column is connected to the piston body, and is used to connect with the second female connector 16 arranged at the bottom of the cylinder.

[0051] The first male connector, the first female connector, the second male connector, and the second female connector are all made of magnetic materials or magnetic structures, so that when the piston is installed in the launch tube, the first male connector can form a quick-fit connection with the second female connector, and when the drone is installed in the barrel, the second male connector on the drone can form a quick-fit connection with the first female connector, so that a quick electrical connection can be formed between the drone and the piston, and between the piston and the launch tube, so that the connection between the drone and the external power supply is realized, thereby realizing the charging operation of the drone in the launch tube. At this time, due to the guide limit structure set between the piston and the launch tube, by limiting the position of the piston, when the piston is installed in the launch tube, the first male connector on the piston can achieve accurate docking and connection with the second female connector on the launch tube.

[0052] During installation, the first male connector is welded to the cable at one end and installed on the electrical connection mounting column, the electrical connection mounting seat is installed at the other end of the electrical connection mounting column, the first female connector is installed on the electrical connection mounting seat and the other end of the cable is welded to the first female connector; then, the skirt sealing ring and the metal pressure plate are fixed to the bottom of the piston body by screws. Since a step is provided on the electrical connection mounting seat, the electrical connection mounting seat can be fixed to the piston body by the skirt sealing ring and the metal pressure plate.

[0053] In one embodiment, a limit support column 25 is provided on the piston body of the piston, and the limit support column 25 is extended toward the inside of the cylinder body. A limit member 251 capable of rotationally limiting the aircraft is provided at one end of the limit support column. When the drone is installed in the launch tube, the aircraft is fixed by two limit members to limit the relative rotational movement between the aircraft and the piston, thereby ensuring the stability of the aircraft during the launch process. At the same time, the installation position of the aircraft on the piston is positioned by the limit member, so that the second male connector on the aircraft can form an accurate docking and connection with the first female connector on the piston.

[0054] When loading the UAV, open the exhaust valve, install the piston into the mouth of the cylinder, dock and install the UAV and the piston, and then install the UAV and the piston into the cylinder together; install the buffer section on the cylinder, install the foam plug into the buffer section, use the foam plug to limit and protect the end of the UAV, and then close the exhaust valve.

[0055] When launching the UAV, the foam plug is taken out and high-pressure gas is introduced into the launch tube. After the high-pressure gas flows into the launch tube, it pushes the piston and the UAV to move. When the piston moves to the buffer section position, it collides with the block. At this time, the UAV and the piston are separated, completing the pneumatic ejection operation of the UAV.

[0056] In the description of the present utility model, it should be noted that the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside", etc. used to indicate the orientation or position relationship are based on the orientation or position relationship shown in the accompanying drawings, or are the orientation or position relationship in which the utility model product is usually placed when used. They are only for the convenience of describing the present utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present utility model.

[0057] In addition, if the terms "horizontal" or "vertical" appear in the description of the present invention, it does not mean that the components are required to be absolutely horizontal or suspended, but can be slightly tilted. For example, "horizontal" only means that its direction is more horizontal than "vertical", and does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0058] In the description of the present invention, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "set", "install", "connect", and "connect" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0059] The above description is only a preferred embodiment of the present invention and does not limit the present invention in any form. Any simple modification or equivalent changes made to the above embodiments based on the technical essence of the present invention shall fall within the protection scope of the present invention.

Claims

1. A pneumatic ejection launcher, characterized in that: It comprises a launching tube and a piston arranged in the launching tube; The launching tube comprises a tube body and a buffer section arranged at the front end of the tube body, a weakening structure is arranged on the buffer section along its circumferential direction, a blocking structure for limiting the movement of the piston is arranged in the buffer section, when the piston moves to the position of the blocking structure and is blocked, the buffer section is destroyed at the position of the weakening structure under the action of the piston.

2. The pneumatic ejection launcher according to claim 1, characterized in that: The weakening structure is a weakening groove arranged on the buffer segment along the circumference of the buffer segment, and the blocking structure is arranged outside the weakening groove; or The buffer section includes a connecting portion and a buffer portion, the connecting portion is used to be connected to the cylinder, the blocking structure is arranged on the buffer portion, the weakening structure is a plurality of breaking ribs arranged between the connecting portion and the buffer portion, the connecting portion and the buffer portion are connected by the breaking ribs, and the breaking ribs are arranged circumferentially at the ends of the connecting portion and the buffer portion.

3. The pneumatic ejection launcher according to claim 1, characterized in that: The blocking structure is a plurality of blocking blocks arranged on the buffer section and located outside the weakening structure.

4. The pneumatic ejection launcher according to claim 3, characterized in that: The blocking surface on the stopper is arranged to be inclined toward one side of the inner part of the cylinder along the axial direction of the cylinder.

5. The pneumatic ejection launcher according to claim 1, characterized in that: The buffer section and the cylinder are detachably connected.

6. The pneumatic ejection launcher according to claim 1, characterized in that: An air inlet joint is arranged at the bottom of the cylinder.

7. The pneumatic ejection launcher according to claim 1, characterized in that: An exhaust valve is arranged at the bottom of the cylinder.

8. The pneumatic ejection launcher according to claim 1, characterized in that: A guide and limit structure is provided between the piston and the launch tube, and the guide and limit structure is configured to enable the piston to move linearly only along the axial direction of the launch tube.

9. The pneumatic ejection launcher according to claim 1, characterized in that: The piston is provided with an electrical connection joint assembly, which includes a first male joint and a first female joint connected by a cable, the first female joint is used to connect with a second male joint arranged on the aircraft, and the first male joint is used to connect with a second female joint arranged at the bottom of the cylinder.

10. The pneumatic ejection launcher according to claim 1, characterized in that: A limit support column is arranged on the piston, and a limit piece capable of rotationally limiting the aircraft is arranged at the end of the limit support column.

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