A drone

Abstract

The invention discloses an unmanned aerial vehicle, comprising a body, a flight boom and propeller blades. An upper oil storage chamber, a middle buffer oil chamber and a lower electrical equipment chamber are arranged inside the body from top to bottom. The upper oil storage chamber and the middle buffer oil chamber are communicated with each other. A flight control board is installed inside the lower electrical equipment chamber. A methanol engine is arranged below the propeller blades. A shock-absorbing support mechanism is also arranged below the body. An oil pipe channel for accommodating an oil pipe and a cable channel for accommodating a cable are arranged inside the flight boom. An oil inlet hole connected to one end of the oil pipe is arranged on the side wall of the middle buffer oil chamber. An annular oil storage tank connected to a plurality of oil inlet holes is arranged inside the middle buffer oil chamber. The other end of the oil pipe is connected to the methanol engine. One end of the cable is connected to the flight control board, and the other end of the cable is connected to the methanol engine. The invention can improve the endurance of the unmanned aerial vehicle and realize stable oil supply and soft landing of the unmanned aerial vehicle.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicle devices, and in particular to a unmanned aerial vehicle. Background Art

[0002] Unmanned aircraft, or UAVs for short, are pilotless aircraft that use radio remote control equipment or their own programs to control the operating devices. UAVs not only free people from aircraft, but also release the potential of aircraft because they are no longer subject to human physiological limitations.

[0003] According to the different aerodynamic layouts, drones can be divided into unmanned fixed-wing, unmanned helicopter, unmanned multi-rotor, unmanned airship, unmanned paraglider and unmanned flapping-wing aircraft, among which the first three are the most common and widely used. Unmanned fixed-wing aircraft have the highest flight efficiency, long endurance and high cruising speed, but they need a runway, cannot hover at a fixed point and have the worst maneuverability; unmanned helicopters take off and land vertically, hover at a fixed point, have the best maneuverability, have a longer flight time and load capacity, but have the most complex structure and the highest cost; unmanned multi-rotor aircraft have the simplest structure, simple operation, strong fault tolerance, low cost, vertical take-off and landing, and hover at a fixed point, but currently have a smaller flight time and load capacity; compared with unmanned fixed-wing aircraft, unmanned rotorcraft generally have the advantages of vertical take-off and landing, hover at a fixed point and strong maneuverability; compared with unmanned helicopters, unmanned multi-rotors have the advantages of simple structure, strong fault tolerance and low cost, and constantly challenge unmanned fixed-wing and unmanned helicopters, as well as various manned aircraft.

[0004] However, most multi-rotor drones on the market use electricity or methanol as power. Existing methanol-powered drones have the following defects:

[0005] (1) For small methanol-powered drones, in order to provide stable oil pressure, the drones are generally equipped with methanol pressure regulators. However, when the drones are shaken or flipped, some drones still experience unstable oil supply;

[0006] (2) In order to avoid damage to the body of the existing drone caused by direct landing, a shock-absorbing mechanism and a shock-proof cover are usually installed at the bottom of the drone, but the effect is not ideal. Summary of the invention

[0007] To this end, the present invention provides a drone to solve the above-mentioned defects in the prior art.

[0008] An unmanned aerial vehicle comprises a body, a plurality of flight cantilevers mounted in a circular array on the side wall of the body, and propeller blades arranged at the far end of the flight cantilevers, an upper oil storage chamber, a middle buffer oil chamber and a lower electrical equipment chamber are arranged in sequence from top to bottom inside the body, the upper oil storage chamber and the middle buffer oil chamber are communicated with each other, a flight control board is installed inside the lower electrical equipment chamber, an oil inlet is arranged at the top of the upper oil storage chamber, a methanol engine is arranged below the propeller blades, and a shock-absorbing support mechanism for supporting the body is also arranged below the body;

[0009] The interior of the flight cantilever is provided with an oil pipe channel for accommodating the oil pipe and a cable channel for accommodating the cable. The side wall of the middle buffer oil chamber is provided with an oil inlet hole connected to one end of the oil pipe. The interior of the middle buffer oil chamber is provided with an annular oil storage tank that penetrates several of the oil inlet holes. The other end of the oil pipe is connected to the methanol engine, one end of the cable is connected to the flight control board, and the other end of the cable is connected to the methanol engine.

[0010] Preferably, the shock-absorbing support mechanism includes a plurality of articulated supports in a circular array below the machine body, a hollow upper sleeve is hingedly installed below the articulated support, a telescopic rod is slidably installed inside the upper sleeve, the top of the telescopic rod and the upper sleeve are connected by a reset spring, a fixed support is provided in the middle of the tube wall of the upper sleeve, the upper end of the fixed support is swingably hinged with a support disc through a lower articulated seat, and the lower surface of the machine body and the upper surface of the support disc are connected by a support compression spring.

[0011] Preferably, a strip-shaped limiting sliding hole is provided on the side wall of the upper sleeve along the axial direction of the upper sleeve, and a limiting protrusion which is clamped inside the strip-shaped limiting sliding hole is provided on the inner side wall of the telescopic rod located on the upper sleeve.

[0012] Preferably, a conical funnel is provided at the bottom of the upper oil storage cavity, and the oil leakage hole at the bottom of the conical funnel is connected to the middle buffer oil cavity below.

[0013] Preferably, a rubber supporting foot is provided at the lower end of the telescopic rod.

[0014] Preferably, a triangular rib plate is provided at the connection portion between the flight cantilever and the fuselage.

[0015] The present invention has the following advantages:

[0016] (1) The present invention uses methanol as the raw material supply for the UAV flight, and utilizes the cooperation between the middle buffer oil chamber and the upper oil storage chamber to continuously replenish oil from the upper oil storage chamber to the middle buffer oil chamber. Even if the UAV shakes or flips during flight, part of the methanol can be tightly locked. The methanol pressure regulator is used to continuously and stably supply oil to the UAV. The annular oil storage tank can also stably lock a certain amount of oil, thereby meeting the stable oil supply requirements of the methanol engine.

[0017] (2) The present invention sets a plurality of shock-absorbing support mechanisms under the UAV body. After the telescopic rod contacts the ground, it will be continuously inserted into the upper sleeve under the elastic action of the return spring, thereby playing a certain buffering role when the UAV lands. The support compression spring is used to elastically support the inclined upper sleeve, thereby further enhancing the elastic buffering performance. The inclined upper sleeve and telescopic rod can have better anti-dumping performance during landing, and can form effective protection for the landing UAV in combination with the rubber support foot. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0019] Figure 2 It is a schematic diagram of the internal cross-sectional structure of the present invention;

[0020] Figure 3 For the present invention Figure 1 A is a schematic diagram of the enlarged structure of the middle part;

[0021] Figure 4 It is a schematic diagram of the connection structure between the middle buffer oil chamber and the flying cantilever of the present invention.

[0022] In the figure:

[0023] 1- fuselage; 2- flight cantilever; 3- propeller blade; 4- upper oil storage chamber; 5- middle buffer oil chamber; 6- lower electrical equipment chamber; 7- flight control board; 8- oil inlet; 9- shock absorption support mechanism; 10- methanol engine; 11- oil pipe channel; 12- cable; 13- cable channel; 14- oil inlet hole; 15- annular oil storage tank; 16- oil pipe; 17- cone funnel; 18- oil leakage hole; 19- triangular rib plate;

[0024] 901-hinged support; 902-upper sleeve; 903-telescopic rod; 904-reset spring; 905-fixed support; 906-lower hinged seat; 907-support disc; 908-support compression spring; 909-strip limiting sliding hole; 910-limiting boss; 911-rubber support foot. DETAILED DESCRIPTION

[0025] In order to make the technical means, creative features, objectives and effects achieved by the present invention easy to understand, the present invention is further explained below in conjunction with specific implementation methods.

[0026] like Figures 1 to 4 As shown, the present invention provides a UAV, which can improve the endurance of the UAV and achieve stable fuel supply and soft landing of the UAV. Specifically:

[0027] The drone comprises a body 1, a plurality of flight cantilevers 2 mounted in a circular array on the side wall of the body 1, and propeller blades 3 arranged at the far end of the flight cantilevers 2. In this embodiment, the number of the flight cantilevers 2 is four.

[0028] The buoyancy generated by the rotation of the propeller blades 3 enables the drone to take off. A triangular rib plate 19 is provided at the connection between the flight boom 2 and the body 1 to improve the firmness of the connection between the flight boom 2 and the body 1.

[0029] The present invention uses methanol to provide power for the UAV. The interior of the body 1 is provided with an upper oil storage chamber 4, a middle buffer oil chamber 5 and a lower electrical equipment chamber 6 in sequence from top to bottom, and the upper oil storage chamber 4 and the middle buffer oil chamber 5 are interconnected.

[0030] A conical funnel 17 is provided at the bottom of the upper oil storage chamber 4, and the oil leakage hole 18 at the bottom of the conical funnel 17 is connected to the middle buffer oil chamber 5 below. The conical structure of the conical funnel 17 is conducive to the upper oil storage chamber 4 continuously replenishing oil to the middle buffer oil chamber 5, and there is still a relatively stable oil supply even if the drone shakes or flips during flight. The upper oil storage chamber 4 continuously replenishes oil to the middle buffer oil chamber 5, and there is still a relatively stable oil supply even if the drone shakes or flips during flight.

[0031] An oil inlet 8 is provided at the top of the upper oil storage chamber 4, and methanol can be added into the upper oil storage chamber 4 from the oil inlet 8. The oil inlet 8 is closed by a sealing plug.

[0032] A flight control board 7 is installed inside the lower electrical equipment cavity 6, and a methanol engine 10 is arranged below the propeller blades 3. When the methanol engine 10 is working, it can drive the propeller blades 3 to rotate.

[0033] The flight control board 7 can satisfy the ground remote controller to control the four methanol engines 10 respectively.

[0034] By using methanol as fuel, the UAV can adjust the rotation speed to a very low level and accelerate rapidly. The methanol engine 10 of the present invention can be a three-blade airplane model methanol engine of model AP15A.

[0035] Among them, the interior of the flight boom 2 is provided with an oil pipe channel 11 for accommodating an oil pipe 16 and a cable channel 13 for accommodating a cable 12. One end of the cable 12 is connected to the flight control board 7, and the other end of the cable 12 is connected to the methanol engine 10, so that the flight control board 7 can control the rotation of the three-blade methanol engine.

[0036] The side wall of the middle buffer oil chamber 5 is provided with an oil inlet hole 14 connected to one end of the oil pipe 16, and the inside of the middle buffer oil chamber 5 is provided with an annular oil storage tank 15 which is connected to several of the oil inlet holes 14. When the drone rotates, under the action of centrifugal force, some methanol will enter the annular oil storage tank 15, that is, the annular oil storage tank 15 is used to stably lock a certain amount of oil to meet the stable oil supply requirements of several methanol engines. The other end of the oil pipe 16 is connected to the methanol engine 10.

[0037] A shock-absorbing support mechanism 9 for supporting the machine body 1 is also provided below the machine body 1. Specifically:

[0038] The shock-absorbing support mechanism 9 includes a plurality of hinged supports 901 arranged in a circular array below the body 1, a hollow upper sleeve 902 is hingedly installed below the hinged support 901, a telescopic rod 903 is slidably installed inside the upper sleeve 902, and a rubber support foot 911 is provided at the lower end of the telescopic rod 903. The rubber support foot 911 can increase the friction between it and the ground to prevent the UAV from sliding sideways after landing.

[0039] The top of the telescopic rod 903 and the upper sleeve 902 are connected via a return spring 904. A fixed support 905 is provided in the middle of the tube wall of the upper sleeve 902. The upper end of the fixed support 905 is swingably hinged with a support disc 907 via a lower hinge seat 906. The lower surface of the body 1 and the upper surface of the support disc 907 are connected via a support compression spring 908.

[0040] The side wall of the upper sleeve 902 is provided with a strip-shaped limiting sliding hole 909 along the axial direction of the upper sleeve 902, and the inner side wall of the telescopic rod 903 located in the upper sleeve 902 is provided with a limiting convex column 910 clamped inside the strip-shaped limiting sliding hole 909. The limiting convex column 910 is clamped inside the strip-shaped limiting sliding hole 909 to prevent the telescopic rod 903 from being disjointed when sliding in the upper sleeve 902, and at the same time, the telescopic rod 903 is limited to prevent it from radially rotating.

[0041] After contacting the ground, the telescopic rod 903 will be continuously inserted into the upper sleeve 902 under the elastic action of the return spring 904, thereby playing a certain buffering role when the drone lands; the support compression spring 908 is used to elastically support the inclined upper sleeve 902, thereby further enhancing the elastic buffering performance, and the inclined upper sleeve 901 and telescopic rod 903 can have better anti-dumping performance during landing.

[0042] Although the present invention has been described in detail above by general description and specific embodiments, it is obvious to those skilled in the art that some modifications or improvements can be made to the present invention. Therefore, these modifications or improvements made without departing from the spirit of the present invention all belong to the scope of protection claimed by the present invention.

Claims

1. An unmanned aerial vehicle, comprising a body (1), a plurality of flight cantilevers (2) mounted in a circular array on the side wall of the body (1), and propeller blades (3) arranged at the far end of the flight cantilevers (2), characterized in that: The interior of the machine body (1) is provided with an upper oil storage chamber (4), a middle buffer oil chamber (5) and a lower electrical equipment chamber (6) in sequence from top to bottom; the upper oil storage chamber (4) and the middle buffer oil chamber (5) are interconnected; a flight control board (7) is installed inside the lower electrical equipment chamber (6); an oil inlet (8) is provided at the top of the upper oil storage chamber (4); a methanol engine (10) is provided below the propeller blades (3); and a shock-absorbing support mechanism (9) for supporting the machine body (1) is also provided below the machine body (1); The flight boom (2) is provided with an oil pipe channel (11) for accommodating an oil pipe (16) and a cable channel (13) for accommodating a cable (12); the side wall of the middle buffer oil chamber (5) is provided with an oil inlet hole (14) connected to one end of the oil pipe (16); the middle buffer oil chamber (5) is provided with an annular oil storage tank (15) that is connected to a plurality of the oil inlet holes (14); the other end of the oil pipe (16) is connected to the methanol engine (10); one end of the cable (12) is connected to the flight control board (7); and the other end of the cable (12) is connected to the methanol engine (10); The shock-absorbing support mechanism (9) comprises a plurality of hinged supports (901) arranged in an annular array below the machine body (1); a hollow upper sleeve (902) is hingedly mounted below the hinged support (901); a telescopic rod (903) is slidably mounted inside the upper sleeve (902); the top of the telescopic rod (903) and the upper sleeve (902) are connected via a return spring (904); a fixed support (905) is arranged in the middle of the tube wall of the upper sleeve (902); the upper end of the fixed support (905) is swingably hingedly connected to a support disc (907) via a lower hinged seat (906); and the lower surface of the machine body (1) and the upper surface of the support disc (907) are connected via a support compression spring (908); The side wall of the upper sleeve (902) is provided with a strip-shaped limiting sliding hole (909) along the axial direction of the upper sleeve (902), and the inner side wall of the telescopic rod (903) located at the upper sleeve (902) is provided with a limiting protrusion (910) clamped inside the strip-shaped limiting sliding hole (909); A conical funnel (17) is provided at the bottom of the upper oil storage chamber (4), and an oil leakage hole (18) at the bottom of the conical funnel (17) and a middle buffer oil chamber (5) below are connected to each other.

2. A drone according to claim 1, characterized in that: The lower end of the telescopic rod (903) is provided with a rubber supporting foot (911).

3. The drone according to claim 1, characterized in that: A triangular rib plate (19) is provided at the connection position between the flight boom (2) and the body (1).

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