Spring releasing and inserting device for quickly separating electrically connected piston from unmanned aerial vehicle

Abstract

The utility model belongs to the technical field of unmanned aerial vehicle launch canisters, and particularly relates to a spring disengaging and inserting device used for rapidly separating an electrical connection piston from an unmanned aerial vehicle, an installation base is arranged at the bottom of a launch canister, a base guide column is arranged on the installation base, a piston guide hole is formed in a boosting piston, and the base guide column and the piston guide hole are matched. Unmanned aerial vehicle guide columns matched with the guide holes are arranged on the unmanned aerial vehicle seat; the mounting base is connected with the boosting piston through a first electric connector, and the boosting piston is connected with the unmanned aerial vehicle seat through a second electric connector; a spring plunger matched with an unmanned aerial vehicle seat is arranged on the boosting piston; a pneumatic stopping plug matched with an unmanned aerial vehicle body is arranged on the launching cylinder, and the unmanned aerial vehicle body and an unmanned aerial vehicle base are integrally arranged.

Description

Technical Field

[0001] The utility model belongs to the technical field of unmanned aerial vehicle launch tubes, and in particular is a spring disconnecting device for quickly separating an electrically connected piston from a unmanned aerial vehicle. Background Art

[0002] At present, there is no relevant electrical connection interface between the general drone launcher and the drone. For example, when charging the drone, it is necessary to manually remove the drone from the launcher and charge it under the mains; the power-on is generally provided with a corresponding switch or button on the head of the drone, and the drone is powered on by manual operation of the switch or button, which is very complicated. Most communications rely on wireless methods, which have a great impact on the electromagnetic interference and signal distribution strength of the region, and have poor reliability. Especially for large-scale cluster launchers that integrate storage, transportation and launch, they cannot respond quickly in wartime, and the cumbersome operation is even more criticized. Therefore, it is very necessary to electrically connect the launcher to the drone and perform high-reliability charging, power-on, communication and other functions on the drone through the launcher.

[0003] At present, there are generally two separation methods: Kevlar rope or wire rope dragging the piston, and adding a parachute to the tail of the piston;

[0004] Kevlar rope or steel wire rope drags the piston: One end of the Kevlar rope is tied to the tail of the piston, and the other end is tied to the base of the launch device. When the piston is accelerated to the muzzle of the launch tube during launch, the piston is forced to separate from the drone under the pulling action of the Kevlar rope. This method is generally used on gunpowder launch devices, which can effectively prevent fire, smoke, etc. from escaping the launch tube and exposing the launch position. However, due to the large instantaneous impact, it is generally used once and needs to be replaced each time.

[0005] Add a parachute to the piston tail: A free parachute is attached to the piston tail. After the drone and the drone are out of the tube, the parachute at the piston tail is unfolded. As the windward area increases, the air resistance increases proportionally, and the piston separates from the drone under the air resistance. However, the parachute must be folded and loaded into the tube every time it is used, otherwise the parachute rope or parachute bag is likely to be involved in the drone propeller, causing a crash.

[0006] Therefore, the utility model designs a spring disconnecting device for quickly separating an electrically connected piston from a drone to solve the technical problems existing in the prior art. Utility Model Content

[0007] In view of the deficiencies in the prior art, the purpose of the utility model is to provide a spring disconnecting device for quickly separating an electrically connected piston from a drone, thereby solving the above-mentioned technical problems.

[0008] The solution adopted by the utility model is: a spring plug-out device for quickly separating an electrically connected piston from a drone, comprising a launching tube and a booster piston, a drone seat and a drone body, characterized in that:

[0009] The bottom of the launch tube is provided with a mounting base, the mounting base is provided with a base guide column, the booster piston is provided with a piston guide hole, and the UAV seat is provided with a UAV guide column matched with the guide hole;

[0010] The mounting base is connected to the booster piston via a first electrical connector, and the booster piston is connected to the drone seat via a second electrical connector;

[0011] The booster piston is provided with a spring plunger that cooperates with the drone seat;

[0012] The launching tube is provided with a pneumatic stopper matched with the drone body, and the body is integrated with the drone seat.

[0013] Preferably, the first electrical connector includes a first male pin on the mounting seat and a first female pin at the bottom of the booster piston, and the second electrical connector includes a second male pin on the mounting seat and a second female pin at the bottom of the drone seat, and the first female pin is electrically connected to the second male pin.

[0014] Preferably, the spring plunger comprises a fixed column arranged on the booster piston, a movable column is slidably connected inside the fixed column, and a booster spring is arranged between the movable column and the fixed column.

[0015] Preferably, the pneumatic stop bolt includes a cylinder body provided on the launching tube, a stop bolt body is slidably connected to the cylinder body, a return spring is provided between the stop bolt body and the inner wall of the cylinder body, two groups of proximity switches are provided on the cylinder body, an air pipeline is provided on the cylinder body, an electromagnetic valve is provided on the air pipeline, and a card slot corresponding to the stop bolt body is provided on the drone body.

[0016] Preferably, an O-shaped rubber sealing ring corresponding to the launching tube is provided on the mounting base.

[0017] Preferably, the spring plungers are provided in an array and are evenly distributed at both ends of the second male pin, and the second male pin is eccentrically arranged on the booster piston.

[0018] Additional aspects and advantages of the present application will be given in part in the description below, and in part will become apparent from the description below, or will be learned through the practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1It is one of the cross-sectional viewing angles of the present utility model.

[0020] Figure 2 This is the second cross-sectional view of the present invention.

[0021] Figure 3 It is a schematic diagram of the interior of the spring plunger of the utility model.

[0022] Figure numerals: 1. Launch tube; 2. Booster piston; 3. UAV seat; 4. UAV body; 5. Mounting base; 6. Base guide column; 7. Piston guide hole; 8. UAV guide column; 11. Spring plunger; 12. Pneumatic stop bolt; 13. First pin male connector; 14. First pin female connector; 15. Second pin male connector; 16. Second pin female connector; 17. Fixed column; 18. Movable column; 19. Booster spring; 20. Cylinder body; 21. Stop bolt body; 22. Reset spring; 23. Proximity switch; 24. Air pipeline; 25. Solenoid valve; 26. Slot. DETAILED DESCRIPTION

[0023] The above and other technical contents, features and functions of the present invention are described in detail below with reference to the attached Figure 1-3 The detailed description of the embodiments will clearly show that the structural contents mentioned in the following embodiments are all based on the drawings in the specification.

[0024] Various exemplary embodiments of the present utility model will be described below with reference to the accompanying drawings.

[0025] Embodiment 1, a spring disconnecting device for quickly disconnecting an electrically connected piston from a drone, comprises a launching tube 1, a booster piston 2, a drone seat 3, and a drone body 4, and is characterized in that:

[0026] The bottom of the launch tube 1 is provided with a mounting base 5, the mounting base 5 is provided with a base guide column 6, the booster piston 2 is provided with a piston guide hole 7, and the drone seat 3 is provided with a drone guide column 8 matched with the guide hole;

[0027] The mounting base 5 is connected to the booster piston 2 via a first electrical connector, and the booster piston 2 is connected to the drone seat 3 via a second electrical connector;

[0028] The booster piston 2 is provided with a spring plunger 11 that cooperates with the drone seat 3;

[0029] The launch tube 1 is provided with a pneumatic stopper 12 that cooperates with the drone body 4, and the drone body is integrated with the drone seat 3;

[0030] The first electrical connector includes a first male pin 13 provided on the mounting seat and a first female pin 14 provided at the bottom of the booster piston 2, and the second electrical connector includes a second male pin 15 provided on the mounting seat and a second female pin 16 provided at the bottom of the drone seat 3, and the first female pin 14 is electrically connected to the second male pin 15;

[0031] The spring plunger 11 includes a fixed column 17 provided on the booster piston 2, a movable column 18 is slidably connected inside the fixed column 17, and a booster spring 19 is provided between the movable column 18 and the fixed column 17;

[0032] The pneumatic stopper 12 comprises a cylinder 20 provided on the launch tube 1, a stopper body 21 is slidably connected to the cylinder 20, a return spring 22 is provided between the stopper body 21 and the inner side wall of the cylinder 20, two groups of proximity switches 23 are provided on the cylinder 20, an air pipeline 24 is provided on the cylinder 20, an electromagnetic valve 25 is provided on the air pipeline 24, and a card slot 26 corresponding to the stopper body 21 is provided on the drone body 4;

[0033] The mounting base 5 is provided with an O-shaped rubber sealing ring corresponding to the launching tube 1;

[0034] The spring plungers 11 are arranged in an array and are evenly distributed at both ends of the second male pin connector 15 , and the second male pin connector 15 is eccentrically arranged on the booster piston 2 .

[0035] When in use, the booster piston 2 is electrically connected to the drone seat 3 through an electrical connector. Electrical connectors are provided at the bottom and top of the booster piston 2 (the top electrical connector is the second male pin 15, and the bottom electrical connector is the first female pin 14). The bottom electrical connector is docked with the launching device (the first male pin 13 and the first female pin 14 cooperate), and the top electrical connector is docked with the drone seat 3 (the second male pin 15 and the second female pin 16 cooperate). During loading, under the action of the base guide column 6 and the piston guide hole 7 and the drone guide column 8 and the piston guide hole 7, efficient blind plug docking can be achieved.

[0036] After loading into place, each electrical connector can be reliably docked under the guidance of the guide column. At this time, the UAV can be charged, powered on, communicated and other tasks through the electrical connector set on the launch device.

[0037] The electrical connector has a multi-core mixed current structure with different cores. Each core has the same function and can be used to charge the drone battery, power on the drone, communicate between the ground station and the drone, detect the position of the drone, etc.

[0038] Principle of drone arrival detection: Short-circuit the two cores of the designated electrical connector inside the drone, and use the PLC detection circuit installed inside the launcher control cabinet to determine whether the loading is in place and whether there is a drone in the tube. When the drone is not loaded in place, the circuit is broken, and after the drone is loaded in place, the circuit is connected.

[0039] Four spring plungers 11 are arranged on the top of the booster piston 2. The spring force in the compressed state matches the separation force of the electrical connector. When loaded in the barrel, the gravity of the drone body 4 and the friction between the wing and the barrel wall ensure the reliable connection of the electrical connector. After loading, the pneumatic stopper 12 is used to axially position the drone to further ensure the reliable docking of the electrical connector. (The pneumatic stopper 12 can also ensure the stability of the drone body 4 during transportation, preventing the drone body 4 from shaking in the launch barrel 1, thereby causing damage to the drone)

[0040] During launch, high-pressure gas enters the launch tube 1, and under the strong thrust of the gas pressure, the booster piston 2 pushes the drone seat 3 and the drone body 4 to accelerate in the tube; after exiting the tube and before the drone body 4 is started, the booster piston 2 and the drone seat 3 are no longer affected by the gas pressure, but only by the inertial motion of the air resistance; at this time, the spring plunger 11 works, and the booster spring 19 inside the fixed column 17 starts to reset from the compressed state, firstly, to provide a separation force for separating the electrical connector, and secondly, to provide a certain reaction force to the booster piston 2, so that it decelerates and further separates from the drone quickly;

[0041] The spring plunger 11 is evenly arranged around the electrical connector and eccentrically placed on the circular cross section. When providing separation force, it is only necessary to push out the upper end of the booster piston 2 and quickly open the airflow channel with the drone seat 3 to achieve rapid separation of the booster piston 2 under the action of wind resistance. After hundreds of tests, the separation time is generally maintained within 0.3 seconds.

[0042] There are no safety risks such as rope breakage or parachute rope being entangled in propellers. It has high reliability, relies on spring reset, can be reused many times, and has been tested more than a hundred times without any problems. It is simple and convenient to operate, without the need for complicated and troublesome operations such as coiling ropes and folding parachutes, saving time and enabling quick response.

[0043] The pneumatic stopper 12 principle: It is composed of a two-position three-way solenoid valve 25, an air passage, a reset spring 22, a stopper body 21, a cylinder 20, a proximity switch 23, etc. When stopping: the two-position three-way solenoid valve 25 is powered off, and under the action of the reset spring 22, the stopper body 21 extends and pushes into the corresponding slot 26 of the drone to stop the drone; when unlocking: the two-position three-way solenoid valve 25 is powered on, and high-pressure gas enters from the bottom to compress the spring, and the stopper body 21 pushes up, and the drone is unlocked. A proximity switch 23 is fixed on the outer wall of the cylinder 20, which can be used to detect the extension and retraction position of the stopper, and further clearly judge the stopping state.

[0044] The above description is only for illustrating the present invention, and it should be understood that the present invention is not limited to the above embodiments, and various variations that conform to the concept of the present invention are within the protection scope of the present invention.

Claims

1. A spring disconnecting device for quickly disconnecting an electrically connected piston from an unmanned aerial vehicle, comprising a launching tube (1), a booster piston (2), an unmanned aerial vehicle seat (3), and an unmanned aerial vehicle body (4), characterized in that: The bottom of the launch tube (1) is provided with a mounting base (5), the mounting base (5) is provided with a base guide column (6), the booster piston (2) is provided with a piston guide hole (7), and the drone seat (3) is provided with a drone guide column (8) matched with the guide hole; The mounting base (5) and the booster piston (2) are connected via a first electrical connector, and the booster piston (2) and the drone seat (3) are connected via a second electrical connector; The booster piston (2) is provided with a spring plunger (11) that cooperates with the drone seat (3); The launch tube (1) is provided with a pneumatic stopper (12) that cooperates with the drone body (4), and the body is integrated with the drone seat (3).

2. A spring disconnecting device for quickly disconnecting an electrically connected piston from a drone according to claim 1, characterized in that: The first electrical connector comprises a first male pin (13) provided on the mounting seat and a first female pin (14) provided at the bottom of the booster piston (2); The second electrical connector comprises a second male pin connector (15) provided on the mounting seat and a second female pin connector (16) provided at the bottom of the drone seat (3), and the first female pin connector (14) and the second male pin connector (15) are electrically connected.

3. A spring disconnecting device for quickly disconnecting an electrically connected piston from a drone according to claim 2, characterized in that: The spring plunger (11) comprises a fixed column (17) provided on the booster piston (2), a movable column (18) being slidably connected inside the fixed column (17), and a booster spring (19) being provided between the movable column (18) and the fixed column (17).

4. A spring disconnecting device for quickly disconnecting an electrically connected piston from a drone according to claim 3, characterized in that: The pneumatic stopper (12) comprises a cylinder (20) provided on a launch tube (1), a stopper body (21) being slidably connected to the cylinder (20), a return spring (22) being provided between the stopper body (21) and the inner wall of the cylinder (20), two groups of proximity switches (23) being provided on the cylinder (20), an air pipeline (24) being provided on the cylinder (20), an electromagnetic valve (25) being provided on the air pipeline (24), and a slot (26) corresponding to the stopper body (21) being provided on the drone body (4).

5. A spring disconnecting device for quickly disconnecting an electrically connected piston from an unmanned aerial vehicle according to claim 4, characterized in that: The mounting base (5) is provided with an O-shaped rubber sealing ring corresponding to the launching tube (1).

6. A spring disconnecting device for quickly disconnecting an electrically connected piston from a drone according to claim 5, characterized in that: The spring plunger (11) is provided in an array and is evenly distributed at both ends of the second male pin (15), and the second male pin (15) is eccentrically arranged on the booster piston (2).

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