An emergency fuel unloading device for a fuel-powered unmanned aerial vehicle

Abstract

The utility model relates to unmanned plane application technical field, and disclose a kind of fuel unmanned plane emergency oil unloading device, including unmanned plane body, oil discharge subassembly and parachute subassembly, the unmanned plane body includes fuselage, the inner wall of the fuselage is equipped with oil tank, the side of the fuselage is fixed with four fixed arms, and the end of each fixed arm is equipped with engine.The fuel unmanned plane emergency oil unloading device, through the synergic effect of high-pressure pump and solenoid valve, when unmanned plane emergency failure occurs, fuel in oil tank can be quickly discharged through high-pressure spray head, effectively reduce the overall weight of unmanned plane body, so as to reduce the impact force when landing, while oil discharge process, the reaction force generated by high-pressure spray head inclined setting can assist adjusting unmanned plane attitude, cooperate the stabilizing effect of parachute subassembly, further improve the security of emergency landing, solve the security hidden danger problem caused by fuel load too large when traditional fuel unmanned plane failure.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) application technology, specifically to an emergency fuel unloading device for fuel-powered UAVs. Background Technology

[0002] A drone is an unmanned aircraft that flies by radio remote control or automatic program control. It is reusable and has a wide range of applications, which have expanded to the three major fields of military, civilian and scientific research. As demand continues to expand, the requirements for reducing drone costs are constantly increasing. The ability to safely and reliably recover drones without damage and to enable them to be reused multiple times has also become an important indicator for evaluating drone performance.

[0003] An existing patent (publication number: CN221986601U) discloses a drone parachute, which includes a drone body. The top of the drone body is equipped with a landing device. The landing device includes a shell, a receiving cavity, a top cover, a launch plate, a parachute body, magnets, and electromagnets. The top of the shell is equipped with a receiving cavity, and the top of the receiving cavity is equipped with a top cover. The receiving cavity is equipped with a launch plate, and the parachute body is fixed to the top of the launch plate. A gas generating device is provided at the bottom center of the receiving cavity. Magnets are provided on both sides of the launch plate, and electromagnets are provided on both sides of the bottom of the receiving cavity. A through hole is provided at the center of the launch plate.

[0004] The aforementioned patent uses a parachute to stabilize the drone during use. For large, long-endurance fuel-powered drones, they are usually designed with large-capacity fuel tanks to ensure long endurance. Even if a parachute is used after a malfunction, the impact of the fuel tank and fuel quality will still cause the drone to descend rapidly, which may cause the drone to be damaged due to excessive impact upon landing, or even cause safety accidents such as fuel leakage or explosion. Utility Model Content

[0005] To address the shortcomings of existing technologies, this utility model provides an emergency fuel unloading device for fuel-powered unmanned aerial vehicles (UAVs), which has the advantages of rapid fuel unloading to reduce the weight of the aircraft, assisting in adjusting the landing attitude, and improving the safety of emergency landing, thus solving the problems mentioned in the background art.

[0006] To achieve the above objectives, this utility model provides the following technical solution: an emergency fuel unloading device for a fuel-powered unmanned aerial vehicle (UAV), comprising a UAV body and a fuel discharge assembly disposed on the side of the UAV body. The UAV body includes a fuselage, with a fuel tank installed on the inner wall of the fuselage. Four fixed arms are fixed to the side of the fuselage, and an engine is installed at the end of each fixed arm. A rotor is installed at the output end of the engine. A high-pressure pump is installed on the side of each fixed arm, and the input end of the high-pressure pump is connected to the fuel tank. The UAV body has a built-in attitude sensor and a central controller. The attitude sensor monitors the flight status parameters of the UAV body in real time, including flight altitude. The system monitors the tilt angle, descent speed, etc., and transmits the data to the central controller. When the central controller determines that the UAV is in an emergency malfunction state, such as unstable flight attitude and descent speed exceeding a preset threshold, it immediately sends a start signal to the high-pressure pump and simultaneously controls the solenoid valve in the oil discharge assembly to open. The oil discharge assembly includes a bracket mounted on the fixed arm, and a high-pressure nozzle is mounted on the bottom surface of the bracket. Each high-pressure pump has two output ends, and the output ends of the high-pressure pump are respectively connected to the corresponding engine and high-pressure nozzle through pipes. Solenoid valves are installed at the output end ports of the high-pressure pump. A parachute assembly is installed on the top of the fuselage.

[0007] Furthermore, the parachute assembly includes a storage box, a support plate is fixed to the inner top wall of the fuselage by bolts, a T-slot is formed on the upper surface of the support plate, a T-block is fixed to the bottom surface of the storage box, the T-block is slidably connected to the T-slot, and the T-block is fixed to the support plate by bolts.

[0008] The above solution enables a detachable connection between the storage box and the support plate, facilitating the installation, maintenance, and replacement of the parachute components.

[0009] Furthermore, a catapult plate is slidably connected inside the storage box, a catapult spring is installed on the bottom surface of the catapult plate, the other end of the catapult spring is connected to the inner bottom wall of the storage box, a parachute body is installed on the upper surface of the catapult plate, an electromagnet is installed on the inner bottom wall of the storage box, and an armature that cooperates with the electromagnet is installed on the bottom surface of the catapult plate. The size of the catapult plate is larger than the port size of the storage box.

[0010] With the above scheme, when the parachute needs to be activated, the electromagnet loses its magnetism when de-energized, the ejection spring quickly resets and pushes the ejection plate upward, ejecting the parachute body from the storage box, thus achieving rapid parachute opening.

[0011] Furthermore, the top of the storage box is provided with a lid that can be automatically opened. One side of the lid is rotatably connected to the storage box via a hinge, and the other side is fixed to the storage box via a magnetic structure.

[0012] With the above solution, when the ejection plate moves upward, it will push open the magnetic structure of the box cover, causing the box cover to rotate around the hinge and open, providing a channel for the parachute body to be ejected, and avoiding the parachute being unable to deploy smoothly due to the box cover being closed.

[0013] Furthermore, the high-pressure nozzle is inclined, and the angle between the high-pressure nozzle and the fixed arm is forty-five degrees.

[0014] The above solution enables the high-pressure nozzle to spray fuel diagonally downwards during unloading. The reaction force generated by the spray can help adjust the attitude of the drone to a certain extent, reducing the problem of center of gravity imbalance caused by rapid fuel unloading. At the same time, the tilted high-pressure nozzle can also expand the diffusion range of the fuel, accelerate the evaporation rate of the fuel, and reduce the possibility of fuel accumulating in specific areas and causing safety hazards.

[0015] Furthermore, the storage box is located directly above the center of the device.

[0016] The above solution ensures that the parachute assembly can generate a uniform pulling force on the drone body when it deploys, preventing the drone body from tipping over or rotating during descent due to eccentric pulling force, and further improving the stability and safety of the drone body during emergency landing.

[0017] Compared with the prior art, the technical solution of this utility model has the following beneficial effects:

[0018] This emergency fuel unloading device for fuel-powered drones can quickly discharge fuel from the tank through high-pressure nozzles by working in conjunction with a high-pressure pump and a solenoid valve when the drone experiences an emergency malfunction. This effectively reduces the overall weight of the drone and thus reduces the impact force during landing. At the same time, the reaction force generated by the tilted high-pressure nozzles during the fuel discharge process can help adjust the drone's attitude. Combined with the stabilizing effect of the parachute assembly, this further improves the safety of emergency landing and solves the safety hazard caused by excessive fuel load when traditional fuel-powered drones malfunction. Attached Figure Description

[0019] Figure 1 This is a three-dimensional structural diagram of the present application;

[0020] Figure 2 This is a rendering of the overall deployment of the parachute body in this application;

[0021] Figure 3 This is a side view of the overall fixed arm of this application;

[0022] Figure 4 This is a sectional view of the side view of the overall bearing plate of this application;

[0023] Figure 5 This is a side view of the overall storage box of this application;

[0024] Figure 6 This is a diagram showing the internal structure of the storage box as described in this application.

[0025] In the picture:

[0026] 1. Unmanned Aerial Vehicle (UAV) fuselage; 101. Body; 102. Fuel tank; 103. Fixed arm; 104. Engine; 105. Rotor; 106. High-pressure pump;

[0027] 2. Oil drain assembly; 201. Bracket; 202. High-pressure nozzle;

[0028] 3. Parachute assembly; 301. Storage box; 302. Support plate; 303. T-block; 304. Ejection plate; 305. Ejection spring; 306. Parachute body; 307. Electromagnet; 308. Armature; 309. Box lid. Detailed Implementation

[0029] The technical solutions of the embodiments of this application 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. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0030] Please see Figure 1 - Figure 6This embodiment discloses an emergency fuel unloading device for a fuel-powered drone, comprising a drone body 1 and a fuel discharge assembly 2 disposed on the side of the drone body 1. The drone body 1 includes a fuselage 101, with a fuel tank 102 installed on the inner wall of the fuselage 101. Four fixed arms 103 are fixed to the side of the fuselage 101, with an engine 104 installed at the end of each fixed arm 103. A rotor 105 is installed at the output end of the engine 104. A high-pressure pump 106 is installed on the side of each fixed arm 103, with the input end of the high-pressure pump 106 connected to the fuel tank 102. The drone body 1 has a built-in attitude sensor and a central controller. The attitude sensor monitors the flight status parameters of the drone body 1 in real time, including flight altitude and tilt. The system transmits data such as angle and descent speed to the central controller. When the central controller determines that the UAV body 1 is in an emergency fault state, such as unstable flight attitude and descent speed exceeding a preset threshold, it immediately sends a start signal to the high-pressure pump 106 and simultaneously controls the solenoid valve in the oil discharge assembly 2 to open. The oil discharge assembly 2 includes a bracket 201 installed on the fixed arm 103. A high-pressure nozzle 202 is installed on the bottom surface of the bracket 201. Each high-pressure pump 106 has two output ends. The output ends of the high-pressure pump 106 are connected to the corresponding engine 104 and high-pressure nozzle 202 through pipes. Solenoid valves are installed at the output end ports of the high-pressure pump 106. A parachute assembly 3 is installed on the top of the body 101.

[0031] Please see Figure 2 , Figure 5 and Figure 6 The parachute assembly 3 includes a storage box 301. A support plate 302 is fixed to the inner top wall of the fuselage 101 by bolts. A T-slot is formed on the upper surface of the support plate 302. A T-block 303 is fixed to the bottom surface of the storage box 301. The T-block 303 is slidably connected to the T-slot. The T-block 303 is fixed to the support plate 302 by bolts, realizing a detachable connection between the storage box 301 and the support plate 302, which facilitates the installation, maintenance and replacement of the parachute assembly 3.

[0032] Please see Figure 2 , Figure 5 and Figure 6An ejection plate 304 is slidably connected inside the storage box 301. An ejection spring 305 is mounted on the bottom surface of the ejection plate 304, and the other end of the ejection spring 305 is connected to the inner bottom wall of the storage box 301. A parachute body 306 is mounted on the upper surface of the ejection plate 304. An electromagnet 307 is mounted on the inner bottom wall of the storage box 301. An armature 308 cooperating with the electromagnet 307 is mounted on the bottom surface of the ejection plate 304. The size of the ejection plate 304 is larger than the port size of the storage box 301. When the parachute needs to be activated, the electromagnet 307 is de-energized and loses its magnetism, and the ejection spring 305... 5. Quickly reset and push the ejection plate 304 upward to eject the parachute body 306 from the storage box 301, achieving rapid parachute deployment. The top of the storage box 301 is provided with an automatically opening lid 309. One side of the lid 309 is rotatably connected to the storage box 301 via a hinge, and the other side is fixed to the storage box 301 via a magnetic structure. When the ejection plate 304 moves upward, it will push open the magnetic structure of the lid 309, causing the lid 309 to rotate around the hinge and open, providing a channel for the parachute body 306 to be ejected, and preventing the parachute from failing to deploy smoothly due to the lid 309 being closed.

[0033] Please see Figure 1 , Figure 2 and Figure 3 The high-pressure nozzle 202 is tilted, with an angle of 45 degrees between it and the fixed arm 103. This allows the high-pressure nozzle 202 to spray fuel diagonally downwards during fuel unloading. The reaction force generated by the spray can help adjust the attitude of the drone body 1 to a certain extent, reducing the center of gravity imbalance caused by rapid fuel unloading. At the same time, the tilted high-pressure nozzle 202 can also expand the fuel diffusion range, accelerate the fuel evaporation rate, and reduce the possibility of fuel accumulation in specific areas causing safety hazards. The storage box 301 is located directly above the center of the body 101, ensuring that the parachute assembly 3 can generate a uniform pulling force on the drone body 1 when it is deployed. This prevents the drone body 1 from tipping over or rotating during descent due to eccentric pulling force, further improving the stability and safety of the drone body 1 during emergency landing.

[0034] It should be noted that after the parachute body 306 pops out and unfolds, the parachute body 306 pulls the drone body 1, causing it to descend at a relatively stable speed. The central controller will continuously receive data from the attitude sensor and dynamically adjust the spray intensity of each high-pressure nozzle 202 and the on / off state of the solenoid valve to ensure that the drone body 1 always maintains a relatively stable descent attitude.

[0035] The working principle of the above embodiment is as follows: When the UAV body 1 encounters an emergency malfunction, the attitude sensor quickly captures abnormal flight data and transmits it to the central controller. The central controller completes the fault determination and then sends commands to the high-pressure pump 106 and the solenoid valve. After the high-pressure pump 106 starts, its input end draws fuel from the fuel tank 102 through a pipeline. At this time, the solenoid valve connected to the engine 104 remains closed, and the fuel flows to the high-pressure nozzle 202 through the output end. Under high pressure, it is sprayed out from the nozzle. During the fuel injection process, the central controller performs differentiated control on the injection duration and intensity of different nozzles, which can realize real-time correction of the UAV's yaw angle. Simultaneously, the electromagnet 307 in the parachute assembly 3 is de-energized, and the ejection spring 305 pushes the ejection plate 304 upward, opening the magnetic box cover 309 and ejecting the parachute body 306 from the storage box 301. The parachute fully unfolds under the action of airflow, providing an upward pull for the drone body 1 and reducing the descent speed of the drone body 1. During this process, the central controller continuously receives feedback data from the attitude sensor and adjusts the working state of the high-pressure nozzle 202 in real time to ensure that the drone maintains a stable attitude under the dual effects of fuel unloading and parachute deceleration until a safe landing, effectively avoiding the risk of fuel tank 102 rupture and fuel leakage.

[0036] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0037] Although embodiments of this application have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of this application, the scope of which is defined by the appended claims and their equivalents.

Claims

1. An emergency fuel unloading device for a fuel-powered unmanned aerial vehicle (UAV), comprising a UAV body (1) and a fuel discharge assembly (2) disposed on the side of the UAV body (1), characterized in that: The UAV body (1) includes a fuselage (101), an oil tank (102) installed on the inner wall of the fuselage (101), four fixed arms (103) fixed on the side of the fuselage (101), an engine (104) installed at the end of each fixed arm (103), a rotor (105) installed at the output end of the engine (104), and a high-pressure pump (106) installed on the side of each fixed arm (103). The input end of the high-pressure pump (106) is connected to the oil tank (102). The oil discharge assembly (2) includes a bracket (201) installed on the fixed arm (103). A high-pressure nozzle (202) is installed on the bottom surface of the bracket (201). Each high-pressure pump (106) is provided with two output ends. The output ends of the high-pressure pump (106) are respectively connected to the corresponding engine (104) and the high-pressure nozzle (202) through pipes. Solenoid valves are installed at the output end ports of the high-pressure pump (106). A parachute assembly (3) is provided above the fuselage (101).

2. The emergency fuel unloading device for a fuel-powered unmanned aerial vehicle according to claim 1, characterized in that: The parachute assembly (3) includes a storage box (301). The inner top wall of the fuselage (101) is fixed with a support plate (302) by bolts. A T-shaped groove is provided on the upper surface of the support plate (302). A T-shaped block (303) is fixed on the bottom surface of the storage box (301). The T-shaped block (303) is slidably connected to the T-shaped groove. The T-shaped block (303) is fixed to the support plate (302) by bolts.

3. The emergency fuel unloading device for a fuel-powered unmanned aerial vehicle according to claim 2, characterized in that: The storage box (301) is internally slidably connected to a catapult plate (304). A catapult spring (305) is installed on the bottom surface of the catapult plate (304). The other end of the catapult spring (305) is connected to the inner bottom wall of the storage box (301). A parachute body (306) is installed on the upper surface of the catapult plate (304). An electromagnet (307) is installed on the inner bottom wall of the storage box (301). An armature (308) that cooperates with the electromagnet (307) is installed on the bottom surface of the catapult plate (304). The size of the catapult plate (304) is larger than the port size of the storage box (301).

4. The emergency fuel unloading device for a fuel-powered unmanned aerial vehicle according to claim 3, characterized in that: The top of the storage box (301) is provided with a lid (309) that can be automatically opened. One side of the lid (309) is rotatably connected to the storage box (301) via a hinge, and the other side is fixed to the storage box (301) via a magnetic structure.

5. The emergency fuel unloading device for a fuel-powered unmanned aerial vehicle according to claim 1, characterized in that: The high-pressure nozzle (202) is inclined, and the angle between the high-pressure nozzle (202) and the fixed arm (103) is forty-five degrees.

6. The emergency fuel unloading device for a fuel-powered unmanned aerial vehicle according to claim 3, characterized in that: The storage box (301) is located directly above the center of the body (101).

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