阅读说明：本技术 一种无人机 (Unmanned aerial vehicle ) 是由 成诚 万志铭 许振腾 于 2020-05-25 设计创作，主要内容包括：本发明公开了一种无人机,包括机体、飞行悬臂以及螺旋桨叶,机体的内部从上至下设有上层储油腔、中部缓冲油腔以及下层电器设备腔,上层储油腔和中部缓冲油腔之间相互连通,下层电器设备腔的内部安装有飞控板,螺旋桨叶的下方均设置有甲醇发动机,机体的下方还设置有减震支撑机构；飞行悬臂的内部设置有容纳油管的油管通道以及用于容纳线缆的线缆通道,中部缓冲油腔的侧壁设有与油管一端连接的进油孔,中部缓冲油腔的内部设置有与若干进油孔贯通的环形储油槽,油管的另一端连接甲醇发动机,线缆的一端连接飞控板,线缆另一端连接甲醇发动机,本发明可以提高无人的续航能力,实现对无人机的稳定供油以及软着陆。(The invention discloses an unmanned aerial vehicle, which comprises a machine body, a flying cantilever and a propeller blade, wherein an upper oil storage cavity, a middle buffer oil cavity and a lower electrical equipment cavity are arranged in the machine body from top to bottom; the unmanned aerial vehicle flight control system comprises a flight cantilever, a middle buffer oil cavity, a plurality of oil pipes, a methanol engine, a flight control board, a plurality of oil pipes, a cable channel, an oil pipe channel and a cable channel, wherein the oil pipes are used for accommodating cables, the oil inlet holes connected with one ends of the oil pipes are formed in the side walls of the middle buffer oil cavity, the annular oil storage grooves communicated with the oil inlet holes are formed in the middle buffer oil cavity, the other end of each oil pipe is connected with the methanol engine, one end of each cable is connected with the flight control board.)

1. The utility model provides an unmanned aerial vehicle, installs including organism (1), annular array a plurality of flight cantilever (2) and the setting of organism (1) lateral wall are in propeller blade (3) of flight cantilever (2) distal end, its characterized in that: an upper oil storage cavity (4), a middle buffer oil cavity (5) and a lower electrical equipment cavity (6) are sequentially arranged in the machine body (1) from top to bottom, the upper oil storage cavity (4) and the middle buffer oil cavity (5) are communicated with each other, a flight control plate (7) is arranged in the lower electrical equipment cavity (6), an oil inlet (8) is formed in the top of the upper oil storage cavity (4), methanol engines (10) are arranged below the propeller blades (3), and a damping support mechanism (9) for supporting the machine body (1) is further arranged below the machine body (1);

the inside of flight cantilever (2) is provided with oil pipe passageway (11) that hold oil pipe (16) and is used for holding cable passageway (13) of cable (12), the lateral wall of middle part cushion oil chamber (5) be equipped with inlet port (14) that oil pipe (16) one end is connected, the inside of middle part cushion oil chamber (5) be provided with a plurality of annular oil storage tank (15) that inlet port (14) link up, the other end of oil pipe (16) is connected methanol engine (10), the one end of cable (12) is connected fly control panel (7), methanol engine (10) are connected to the cable (12) other end.

2. A drone according to claim 1, characterised in that: the damping supporting mechanism (9) comprises a plurality of hinged supports (901) which are arranged below the machine body (1) in an annular array mode, a hollow upper sleeve (902) is hinged to the lower portion of each hinged support (901), a telescopic rod (903) is slidably mounted inside the upper sleeve (902), the top of the telescopic rod (903) is connected with the upper sleeve (902) through a return spring (904), a fixed support (905) is arranged in the middle of the wall of the upper sleeve (902), the upper end of the fixed support (905) is hinged to a supporting disc (907) through the lower hinged support (906) in a swinging mode, and the lower surface of the machine body (1) is connected with the upper surface of the supporting disc (907) through a supporting pressure spring (908).

3. A drone according to claim 2, characterised in that: 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 side wall of the telescopic rod (903) positioned in the upper sleeve (902) is provided with a limiting convex column (910) clamped in the strip-shaped limiting sliding hole (909).

4. A drone according to claim 1, characterised in that: the bottom of upper oil storage chamber (4) is provided with conical funnel (17), oil leak hole (18) and middle part cushion oil chamber (5) of below of conical funnel (17) bottom communicate with each other.

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

6. A drone according to claim 1, characterised in that: a triangular rib plate (19) is arranged at the connecting part of the flying cantilever (2) and the machine body (1).

Technical Field

The invention relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle.

Background

An unmanned aircraft, called an unmanned plane for short, is a pilotless aircraft which utilizes radio remote control equipment or a self program to control a control device. Unmanned aerial vehicles not only free people from aircraft, but also release the potential of the aircraft because they are no longer subject to the physiological limitations of people.

According to the difference of the pneumatic layout mode, the unmanned aerial vehicle can be divided into an unmanned fixed wing, an unmanned helicopter, an unmanned multi-rotor wing, an unmanned airship, an unmanned umbrella wing machine and an unmanned flapping wing machine, wherein the first three types are the most common and the application is the most extensive. The unmanned fixed wing has the highest flying efficiency, long endurance time and high cruising speed, but needs a runway, cannot hover at a fixed point and has the worst maneuverability; the unmanned helicopter has the advantages of vertical take-off and landing, fixed-point hovering, best maneuverability, larger time and load, most complex structure and highest cost; the unmanned multi-rotor wing has the simplest structure, simple operation, strong fault-tolerant capability, low cost, vertical take-off and landing and fixed-point hovering, but the current time and load are smaller; compared with an unmanned fixed wing, the unmanned gyroplane generally has the advantages of vertical take-off and landing, fixed-point hovering, strong maneuverability and the like; compared with an unmanned helicopter, the unmanned multi-rotor wing has the advantages of simple structure, strong fault-tolerant capability, low cost and the like, and continuously challenges unmanned fixed wings, the unmanned helicopter and various piloted airplanes.

However, many rotor unmanned aerial vehicles on the market adopt electric power or methyl alcohol as power, and the unmanned aerial vehicle of current methyl alcohol as power has following defect:

(1) for small methanol-powered unmanned aerial vehicles, in order to provide stable oil pressure, a methanol pressure regulator is generally provided for the unmanned aerial vehicles, but when the unmanned aerial vehicles shake or turn over, the phenomenon of unstable oil supply of some unmanned aerial vehicles still occurs;

(2) and current unmanned aerial vehicle avoids directly falling to the ground the damage that causes the organism, can set up the shockproof cover of bradyseism mechanism and parcel in unmanned aerial vehicle's bottom usually, but the effect is not ideal.

Disclosure of Invention

Therefore, the invention provides an unmanned aerial vehicle to overcome the defects in the prior art.

An unmanned aerial vehicle comprises a machine body, a plurality of flying cantilevers arranged on the side wall of the machine body in an annular array mode and propeller blades arranged at the far ends of the flying cantilevers, wherein an upper oil storage cavity, a middle buffering oil cavity and a lower electrical equipment cavity are sequentially arranged in the machine body from top to bottom, the upper oil storage cavity and the middle buffering oil cavity are communicated with each other, a flight control plate is arranged in the lower electrical equipment cavity, an oil inlet is formed in the top of the upper oil storage cavity, a methanol engine is arranged below each propeller blade, and a damping and supporting mechanism used for supporting the machine body is further arranged below the machine body;

the inside of flight cantilever is provided with the oil pipe passageway that holds oil pipe and is used for holding the cable passageway of cable, the lateral wall of middle part cushion oil chamber be equipped with the inlet port that oil pipe one end is connected, the inside of middle part cushion oil chamber be provided with a plurality of the annular oil storage tank that the inlet port link up, oil pipe's the other end is connected the methyl alcohol engine, the one end of cable is connected fly the accuse board, the methyl alcohol engine is connected to the cable other end.

Preferably, shock attenuation supporting mechanism includes a plurality of hinged-support of annular array in the organism below, the articulated hollow upper casing of installing in hinged-support's below, go up sheathed tube inside slidable mounting has the telescopic link, connect through reset spring between telescopic link top and the upper casing, the pipe wall middle part of going up the sheathed tube is provided with fixing support, fixing support's upper end articulates through lower hinged-support swing has the support disc, connects through supporting the pressure spring between the lower surface of organism and the upper surface that supports the disc.

Preferably, the side wall of the upper sleeve is provided with a strip-shaped limiting sliding hole along the axial direction of the upper sleeve, and the side wall of the telescopic rod, which is positioned inside the upper sleeve, is provided with a limiting convex column clamped inside the strip-shaped limiting sliding hole.

Preferably, the bottom of the upper oil storage cavity is provided with a conical funnel, and an oil leakage hole at the bottom of the conical funnel is communicated with the middle buffer oil cavity below the conical funnel.

Preferably, the lower end of the telescopic rod is provided with a rubber supporting foot.

Preferably, a triangular rib plate is arranged at the connecting part of the flying cantilever and the aircraft body.

The invention has the following advantages:

(1) the invention adopts methanol as the raw material supply for the unmanned aerial vehicle flight, utilizes the matching of the middle buffer oil cavity and the upper oil storage cavity, and continuously supplies oil to the middle buffer oil cavity from the upper oil storage cavity, so that part of methanol can be tightly locked even if the unmanned aerial vehicle shakes or turns over in the flight process, and the annular oil storage tank can also be used for stably locking a certain amount of oil for the unmanned aerial vehicle to supply oil continuously and stably, thereby meeting the requirement of stable oil supply of a methanol engine;

(2) according to the invention, the plurality of damping support mechanisms are arranged below the unmanned aerial vehicle body, and the telescopic rods of the damping support mechanisms can be continuously inserted into the upper sleeve under the elastic action of the return spring after contacting the ground, so that a certain buffering effect is achieved when the unmanned aerial vehicle lands; utilize to support the pressure spring to carry out elastic support to the last sleeve pipe of slope installation to further reinforcing elasticity shock-absorbing capacity, and the last sleeve pipe that the slope set up and telescopic link can have better when descending prevent empting the performance, cooperation rubber support footing can form the effective protection to descending unmanned aerial vehicle.

Drawings

FIG. 1 is a schematic view of the overall structure of the present invention;

FIG. 2 is a schematic diagram of the internal cross-sectional structure of the present invention;

FIG. 3 is an enlarged view of A of FIG. 1 according to the present invention;

FIG. 4 is a schematic view of the connecting structure of the middle buffer oil chamber and the flying cantilever.

In the figure:

1-body; 2-a flying cantilever; 3-a propeller blade; 4-upper oil storage chamber; 5-a middle buffer oil cavity; 6-lower electrical equipment cavity; 7-flight control panel; 8-an oil inlet; 9-a shock-absorbing support mechanism; 10-methanol engine; 11-oil pipe passage; 12-a cable; 13-a cable channel; 14-oil inlet hole; 15-annular oil storage tank; 16-tubing; 17-a conical funnel; 18-oil leakage holes; 19-triangular rib plate;

901-hinged support; 902-installing a sleeve; 903-a telescopic rod; 904-a return spring; 905-a fixed support; 906-lower hinge mount; 907-support disc; 908-supporting a compression spring; 909-bar-shaped limit slide holes; 910-a limiting convex column; 911-rubber support foot.

Detailed Description

In order to make the technical means, the creation characteristics, the achievement purposes and the effects of the invention easy to understand, the invention is further described with the specific embodiments.

As shown in fig. 1 to 4, the present invention provides an unmanned aerial vehicle, which can improve the cruising ability of the unmanned aerial vehicle, and realize stable oil supply and soft landing for the unmanned aerial vehicle. Specifically, the method comprises the following steps:

this unmanned aerial vehicle includes that organism 1, annular array install a plurality of flight cantilever 2 and the setting of 1 lateral wall of organism are in the propeller blade 3 of the 2 distal ends of flight cantilever. The number of flying booms 2 in this embodiment is four.

The buoyancy generated by the rotation of the propeller blades 3 enables the unmanned aerial vehicle to take off. The connection part of the flying cantilever 2 and the machine body 1 is provided with a triangular rib plate 19, so that the connection firmness of the connection part of the flying cantilever 2 and the machine body 1 is improved.

The invention utilizes methanol to provide power for the unmanned aerial vehicle. Wherein, the inside of organism 1 is from last to being provided with upper oil storage chamber 4, middle part cushion oil chamber 5 and lower floor's electrical equipment chamber 6 down in order, communicate each other between upper oil storage chamber 4 and the middle part cushion oil chamber 5.

The bottom of the upper oil storage cavity 4 is provided with a conical funnel 17, and an oil leakage hole 18 at the bottom of the conical funnel 17 is communicated with the middle buffer oil cavity 5 below the conical funnel 17. The toper structure of conical hopper 17 is favorable to upper oil storage chamber 4 to constantly mend oil to middle part cushion oil chamber 5 in, and it also has comparatively stable fuel feeding to take place to rock or overturn even unmanned aerial vehicle flight in-process. The upper oil storage cavity 4 continuously supplies oil to the middle buffer oil cavity 5, and stable oil supply can be still realized even if the unmanned aerial vehicle shakes or overturns in the flying process.

An oil inlet 8 is arranged 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.

The interior of lower floor's electrical equipment chamber 6 is installed and is flown control board 7, and propeller blade 3's below all is provided with methyl alcohol engine 10, and methyl alcohol engine 10 during operation can drive propeller blade 3 rotatory.

The flight control board 7 can meet the requirement that a ground remote controller respectively controls four methanol engines 10.

Methanol is used as fuel, so that the unmanned aerial vehicle can adjust the rotating speed to be very low and can accelerate quickly, and the methanol engine 10 can be a three-blade model airplane methanol engine with the model number of AP 15A.

The flight cantilever 2 is internally 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 with the flight control panel 7, and the other end of the cable 12 is connected with the methanol engine 10, so that the flight control panel 7 can control the rotation of the three-blade methanol engine.

The lateral wall of middle part cushion oil chamber 5 be equipped with the inlet port 14 that 16 one ends of oil pipe are connected, the inside of middle part cushion oil chamber 5 be provided with a plurality of annular oil storage tank 15 that the inlet port 14 link up, unmanned aerial vehicle have partial methyl alcohol to get into inside annular oil storage tank 15 at rotatory in-process, under the effect of centrifugal force, utilize annular oil storage tank 15 to pin certain oil mass promptly steadily, satisfy the demand of the stable fuel feeding of several methyl alcohol engines. The other end of the oil pipe 16 is connected with the methanol engine 10.

Wherein, a damping support mechanism 9 for supporting the machine body 1 is further arranged below the machine body 1. Specifically, the method comprises the following steps:

the shock absorption supporting mechanism 9 comprises a plurality of hinged supports 901 which are arranged below the machine body 1 in an annular array mode, a hollow upper sleeve 902 is hinged to the lower portion of each hinged support 901, a telescopic rod 903 is slidably mounted inside each upper sleeve 902, and a rubber supporting foot 911 is arranged at the lower end of each telescopic rod 903. Rubber support footing 911 can increase the friction between itself and the ground, avoiding unmanned aerial vehicle to sideslip after descending.

The top of the telescopic rod 903 is connected with the upper sleeve 902 through a return spring 904, a fixed support 905 is arranged in the middle of the wall of the upper sleeve 902, the upper end of the fixed support 905 is hinged with a support disc 907 through a lower hinge seat 906 in a swinging manner, and the lower surface of the machine body 1 is connected with the upper surface of the support disc 907 through 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 side wall of the telescopic rod 903 in the upper sleeve 902 is provided with a limiting convex column 910 clamped in the strip-shaped limiting sliding hole 909. The limiting convex column 910 is clamped inside the strip-shaped limiting sliding hole 909, so that the telescopic rod 903 is prevented from being disconnected when sliding in the upper sleeve 902, and meanwhile, the limiting telescopic rod 903 is prevented from rotating radially.

After contacting the ground, the telescopic rod 903 is continuously inserted into the upper sleeve 902 under the elastic action of the return spring 904, so that the unmanned aerial vehicle can play a certain buffering role during landing; the obliquely installed upper sleeve 902 is elastically supported by the supporting compression springs 908, so that the elastic buffer performance is further enhanced, and the obliquely arranged upper sleeve 901 and the telescopic rod 903 can have better anti-toppling performance when falling.

Although the invention has been described in detail above with reference to a general description and specific examples, it will be apparent to one skilled in the art that modifications or improvements may be made thereto based on the invention. Accordingly, such modifications and improvements are intended to be within the scope of the invention as claimed.