CN214729651U

CN214729651U - Full-electric single-wing self-rotating unmanned aerial vehicle aircraft

Info

Publication number: CN214729651U
Application number: CN202121015370.4U
Authority: CN
Inventors: 孙洪飞; 叶晓浩
Original assignee: Xiamen University
Current assignee: Xiamen University
Priority date: 2021-05-12
Filing date: 2021-05-12
Publication date: 2021-11-16
Anticipated expiration: 2031-05-12

Abstract

An all-electric single-wing self-rotating unmanned aerial vehicle comprises a vehicle body and wings, wherein the wings are arranged on one side of the vehicle body; the wing comprises a fixed wing, a rotatable flap and a torsion wing, the fixed wing is connected with the fuselage, the rotatable flap is arranged on one side of the fixed wing, and the torsion wing is arranged at the tail ends of the fixed wing and the rotatable flap; the airplane body is provided with a flight control board, a battery, an electric controller, a motor, a propeller and a carbon board; two ends of the carbon plate are respectively connected with the machine body and the motor, and the other end of the motor is connected with the propeller and used for controlling the rotation of the propeller; the flight control panel is connected with an electric regulator, a motor and a battery, the battery is used for supplying power to the aircraft, and the electric regulator is used for regulating the rotating speed of the motor; the fixed wing is provided with a steering engine, and the steering engine is connected with the flight control plate and used for controlling the rotation of the rotatable flap. By adopting the wing self-rotation technology, the wing self-rotation aircraft has the advantages of vertical take-off and landing functions, good aerodynamic performance, light weight, low power consumption, stability, long endurance time and the like.

Description

Full-electric single-wing self-rotating unmanned aerial vehicle aircraft

Technical Field

The utility model relates to an aircraft technical field especially relates to a full electric single wing spin unmanned aerial vehicle aircraft.

Background

Along with the wide application of unmanned aerial vehicle technique in the aspect of agricultural plant protection, require more and more high to unmanned aerial vehicle, unmanned aerial vehicle includes oily power unmanned aerial vehicle and electric unmanned aerial vehicle, electric unmanned aerial vehicle is small and exquisite convenient, accept by most people, unmanned aerial vehicle is at the in-process that descends, if do not do the shock attenuation work, the condition of support frame rupture easily appears, current unmanned aerial vehicle is four rotor unmanned aerial vehicle for the majority simultaneously, four rotor unmanned aerial vehicle part multiple weight is great, simultaneously the price is expensive, unit interval power consumption is great, lead to the voyage shorter.

The existing aircraft has good application in the field of bionic biology, such as bird shape, clover shape and vertical dandelion shape, the traditional fixed wing moment micro unmanned aerial vehicle generally adopts the traditional shapes of common rectangular wings, zimmerman-shaped wings and the like, is easily influenced by the phenomenon of self-induced transverse instability during flying, self-induced rolling oscillation occurs, the aircraft can be out of control or even crash seriously, and the maple seeds existing in nature are an aerial landing deceleration solution. On the side of the oval seed, there is a light and thin paddle. When the maple seeds fall from the tree, the air pushes the blades to enable the whole maple seeds to rotate, so that lift force is generated, the falling speed of the maple seeds is slowed down, and the maple seeds can float to a farther place. The utility model discloses design overall structure on the basis of emulation maple seed flight principle, have simple structure, control effectively reliable characteristics easily.

Disclosure of Invention

An object of the utility model is to solve the above-mentioned problem among the prior art, refer to the maple seed spin flight mode in nature, combine aircraft global design method, research single-oar rotor aircraft aerodynamic configuration, overall structure provide a full electric single wing spin unmanned aerial vehicle aircraft, adopt wing autogyration technique, make it have the function of VTOL, good aerodynamic performance, lightweight, low-power consumption, steady, advantage such as time of endurance length.

In order to achieve the above purpose, the utility model adopts the following technical scheme:

an all-electric single-wing self-rotating unmanned aerial vehicle comprises a vehicle body and wings, wherein the wings are arranged on one side of the vehicle body; the wing comprises a fixed wing, a rotatable flap and a torsion wing, the fixed wing is connected with the fuselage, the rotatable flap is arranged on one side of the fixed wing, and the torsion wing is arranged at the tail ends of the fixed wing and the rotatable flap; the airplane body is provided with a flight control board, a battery, an electric controller, a motor, a propeller and a carbon board; two ends of the carbon plate are respectively connected with the machine body and the motor, and the other end of the motor is connected with the propeller and used for controlling the rotation of the propeller; the flight control panel is connected with an electric regulator, a motor and a battery, the battery is used for supplying power to the aircraft, and the electric regulator is used for regulating the rotating speed of the motor; the fixed wing is provided with a steering engine, and the steering engine is connected with the flight control plate and used for controlling the rotation of the rotatable flap.

The utility model discloses still include first buffering foam ball, the bottom of fuselage is located to first buffering foam ball, is located the below that fuselage and stationary vane are connected.

The utility model discloses still include second buffering foam ball, the bottom of fuselage is located to second buffering foam ball, is located the below that carbon plate and fuselage are connected.

The fuselage and the stationary vane are connected through first connecting piece, first connecting piece includes first connecting seat and carbon-point, first connecting seat and fuselage fixed connection, the one end of carbon-point is passed first connecting seat and is passed through the round pin fixedly, and the other end and the stationary vane of carbon-point are connected.

The carbon plate is connected with the machine body through a second connecting piece, the second connecting piece comprises a second connecting seat and a fixing seat, the second connecting seat comprises a bottom plate parallel to the machine body and an inclined plate connected with the bottom plate, the bottom plate is connected with the machine body, the inclined plate is connected with the fixing seat, and the fixing seat is connected with the carbon plate.

The inclined plate and the bottom plate form an included angle of 135 degrees.

And reinforcing ribs are arranged on two sides of the joint of the bottom plate and the inclined plate.

The fixing seat is provided with a groove, and the carbon plate is inserted into the groove and is positioned and connected through the positioning hole.

Compared with the prior art, the utility model discloses technical scheme obtains beneficial effect is:

the utility model discloses based on the flight principle of maple seed, provide one kind and can carry out the full-electric single wing spin unmanned aerial vehicle aircraft that stably controls through motor and steering wheel, have good aerodynamic appearance and the function of rotary wing machine VTOL, for general rotorcraft that verts, alleviate the requirement to the engine when VTOL, have lightweight, low-power consumption, steady, advantage such as time of endurance is long, also a new thinking that future aircraft development provided simultaneously.

The utility model adopts the second connecting piece to realize the parallel of the motor thrust direction and the ground, and realizes the stable control of the unmanned aerial vehicle; the motor and the machine body can be well connected, the height of the motor is increased due to the main effect of the carbon plate, the propeller is prevented from colliding with the ground, the propeller can take off smoothly, and the motor and the propeller are protected to a certain extent in the process of falling to the ground.

Drawings

Fig. 1 is a schematic diagram of the overall structure of an all-electric single-wing self-spinning unmanned aerial vehicle.

Fig. 2 is a schematic bottom view of an all-electric single-wing self-spinning unmanned aerial vehicle.

Fig. 3 is a schematic front view of the full electric single-wing spinning unmanned aerial vehicle during takeoff or landing.

Fig. 4 is a left-side view schematic diagram of the full electric single-wing spinning unmanned aerial vehicle during takeoff or landing.

Fig. 5 is a schematic top view of the all-electric single-wing spinning unmanned aerial vehicle during takeoff or landing.

Fig. 6 is a schematic view of the overall structure of the second connector.

Fig. 7 is a side view of the second connector.

Fig. 8 is a top view of the second connector.

Fig. 9 is a schematic structural view of a carbon plate.

Reference numerals: fuselage 1, fly the accuse board 2, first buffering foam ball 3, first connecting piece 4, round pin 5, electricity is transferred 6, second connecting piece 7, carbon plate 8, screw 9, motor 10, carbon-point 11, rotatable wing flap 12, stationary vane 13, turn round wing 14, battery 15, nut 16, second buffering foam ball 17, steering wheel 18, bottom plate 19, swash plate 20, fixing base 21, recess 22.

Detailed Description

In order to make the technical problem, technical solution and beneficial effects to be solved by the present invention clearer and more obvious, the following description is made in detail with reference to the accompanying drawings and embodiments.

As shown in fig. 1 to 9, the present embodiment includes a fuselage 1 and wings, and the wings are disposed on one side of the fuselage 1;

the wing comprises a fixed wing 13, a rotatable flap 12 and a torsion wing 14, wherein the fixed wing 13 is connected with the fuselage 1, the rotatable flap 12 is arranged on one side of the fixed wing 13, and the torsion wing 14 is arranged at the tail ends of the fixed wing 13 and the rotatable flap 12; the aircraft body 1 is provided with a flight control board 2, a battery 15, an electric regulator 6, a motor 10, a propeller 9 and a carbon plate 8; two ends of the carbon plate 8 are respectively connected with the machine body 1 and the motor 10, and the other end of the motor 10 is connected with the propeller 9 through a nut 16 and used for controlling the rotation of the propeller 9; the flight control panel 2 is connected with an electric regulator 6, a motor 10 and a battery 15, the battery 15 is used for supplying power to the aircraft, and the electric regulator 6 is used for adjusting the rotating speed of the motor 10; the fixed wing 13 is provided with a steering engine 18, and the steering engine 18 is connected with the flight control plate 2 and used for controlling the rotation of the rotatable flap 12.

The automobile body structure further comprises a first buffering foam ball 3 and a second buffering foam ball 17, wherein the first buffering foam ball 3 is arranged at the bottom of the automobile body 1 and is positioned below the connection part of the automobile body 1 and the fixed wing 13; and the second buffer foam ball 17 is arranged at the bottom of the machine body 1 and is positioned below the connection of the carbon plate 8 and the machine body 1.

Specifically, fuselage 1 and stationary vane 13 are connected through first connecting piece 4, first connecting piece 4 includes first connecting seat and carbon-point 11, first connecting seat and fuselage 1 fixed connection, the one end of carbon-point 11 is passed first connecting seat and is passed through round pin 5 fixedly, and the other end and the stationary vane 13 of carbon-point 11 are connected, so, can realize through first connecting piece 4 that wing and fuselage can dismantle.

Specifically, carbon plate 8 is connected through second connecting piece 7 with fuselage 1, second connecting piece 7 includes second connecting seat and fixing base 21, the second connecting seat includes bottom plate 19 parallel with fuselage 1 and the swash plate 20 of being connected with bottom plate 19, bottom plate 19 is connected with fuselage 1, swash plate 20 is connected with fixing base 21, fixing base 21 is connected with carbon plate 8. The inclined plate 20 and the bottom plate 19 form an included angle of 135 degrees. Reinforcing ribs are arranged on two sides of the joint of the bottom plate 19 and the inclined plate 20. The fixing seat 21 is provided with a groove 22, and the carbon plate 8 is inserted into the groove 22 and is positioned and connected through a positioning hole.

The principle of the utility model is as follows:

1. motor 10 drives screw 9 rotatory, it is rotatory around the rotation center to promote whole unmanned aerial vehicle, the rotation center falls on first buffering foam ball 3 place axis through the counter weight, fuselage 1 is rotatory, it is rotatory to drive whole wing, the cutting air produces the lift, unmanned aerial vehicle realizes taking off perpendicularly, through remote controller or fly control procedure remote input order to flying control board 2 output instruction, through the size that instruction electricity is transferred 6 can the adjusting motor 10 rotational speed, the speed that whole wing cutting air can be controlled to the rotational speed size adjustment of motor 10, can adjust the size of lift, control unmanned aerial vehicle is ascending in the vertical direction, descend and hover.

2. The deflection angle of the steering engine 18 can be controlled through the instruction output by the flight control board 2, the steering engine 18 drives the rotatable flap 12 to deflect, lift force adjustment of the whole aircraft can be supplemented to a certain extent, meanwhile, the instruction can realize periodic rotation of the rotatable flap 12 controlled by the steering engine 18, transverse offset force is generated, transverse offset of the unmanned aerial vehicle is realized, the motor 10 and the steering engine 18 are controlled through the GPS function attached to the flight control board 2, the offset direction of the whole unmanned aerial vehicle can be controlled, and the unmanned aerial vehicle can move in all directions in space.

3. The torsion wing 14 imitating the maple seeds can reduce partial airflow loss at the tail of the whole wing, after the motor 10 stops working, under the action of inertia and the influence of wind force appearing in space, the wing continues to rotate in the descending process, the self-rotating motion generates partial lift force to resist gravity, slow descending is achieved, the descending process imitating the maple seeds is achieved, energy consumed in the descending process is greatly reduced, only the periodic motion of the steering engine 18 needs to be controlled, and the flight direction of the whole unmanned aerial vehicle can be controlled.

4. The second connecting piece 7 has a vital function, the power installation part of the unmanned aerial vehicle of the utility model, namely the installation part of the motor 10 is very different from the traditional unmanned aerial vehicle, the thrust direction generated by the motor 10 has a 90-degree included angle with the air cutting direction of the wings of the unmanned aerial vehicle, therefore, the second connecting piece 7 is designed to meet the installation requirement of the motor 10, as shown in figure 6, the bottom surface of the second connecting piece 7 is provided with two positioning holes, the right end of the machine body 1 is provided with two positioning holes with the same size, the second connecting piece 7 is fixed on the machine body 1 by bolt connection and gluing, in the process that the motor 10 drives the propeller 9 to rotate, in order to prevent the propeller 9 from touching the ground, the installation plane of the motor 10 needs to have a certain height difference with the plane of the machine body 1 in the vertical direction, therefore, the second connecting piece 7 is designed with an inclined plane which forms an included angle ANS of 135 degrees with the bottom surface as shown in figure 7, simulation calculation is carried out through CFD software YS, under the prerequisite of sparingly using material and satisfying the intensity requirement, design this angle and be favorable to descending the in-process at unmanned aerial vehicle, certain buffering occasionally contacts to earth, prevents the damage of second connecting piece 7, can satisfy the difference in height requirement of motor 10 and fuselage 1 on the vertical height simultaneously. Through the calculation result of ANSYS and the result of carrying out the entity experiment, arrange the strengthening rib of a row on the position that receives stress concentration and destruction easily on second connecting piece 7, reduce the probability of damage of second connecting piece 7. The inclined plane of the second connecting piece 7 is designed with 4 positioning holes to be connected with the carbon plate 8, the carbon plate 8 is obtained by laser cutting of a carbon plate with the thickness of 2mm, as shown in fig. 9, the tail part of the carbon plate 8 is provided with 4 positioning holes, the second connecting piece 7 is connected with the carbon plate 8 by bolts, 4 holes at the top part of the carbon plate 8 are positioning holes of the motor 10, the carbon plate 8 is connected with the motor 10 by screws, the second connecting piece 7 is provided with a fixing seat 21 in a cuboid shape, as shown in fig. 8, a groove 22 is formed in the fixing seat 21 and is used for fixing the carbon plate 8, the freedom degree of the carbon plate 8 in each direction is limited, the length of the fixing seat 21 is prolonged, the vibration generated by the carbon plate 8 in the rotating process of the motor 10 can be effectively reduced, the consideration of economy and reduction of the weight of the unmanned aerial vehicle is realized, experiments and simulations show that when the length of the fixing seat 21 is 40mm, the micro vibration generated by the carbon plate 8 and the increased weight of the second connecting piece 7 do not influence the normal takeoff of the unmanned aerial vehicle, the whole second connecting piece 7 is obtained by 3D printing of a nylon material and has certain strength and toughness.

The utility model discloses not only keep good aerodynamic performance, reduce energy consumption, also reduce the aircraft simultaneously and rise and fall the requirement to the place to for general rotorcraft that verts, reduce its requirement to the engine.

Claims

1. The utility model provides a full electric single wing spin unmanned aerial vehicle aircraft which characterized in that: the airplane wing aircraft comprises an airplane body and wings, wherein the wings are arranged on one side of the airplane body; the wing comprises a fixed wing, a rotatable flap and a torsion wing, the fixed wing is connected with the fuselage, the rotatable flap is arranged on one side of the fixed wing, and the torsion wing is arranged at the tail ends of the fixed wing and the rotatable flap; the airplane body is provided with a flight control board, a battery, an electric controller, a motor, a propeller and a carbon board; two ends of the carbon plate are respectively connected with the machine body and the motor, and the other end of the motor is connected with the propeller and used for controlling the rotation of the propeller; the flight control panel is connected with an electric regulator, a motor and a battery, the battery is used for supplying power to the aircraft, and the electric regulator is used for regulating the rotating speed of the motor; the fixed wing is provided with a steering engine, and the steering engine is connected with the flight control plate and used for controlling the rotation of the rotatable flap.

2. An all-electric single-wing spinning unmanned aerial vehicle as claimed in claim 1, wherein: still include first buffering foam ball, the bottom of fuselage is located to first buffering foam ball, is located the below that fuselage and stationary vane are connected.

3. An all-electric single-wing spinning unmanned aerial vehicle as claimed in claim 1, wherein: still include second buffering foam ball, the bottom of fuselage is located to second buffering foam ball, is located the below that carbon plate and fuselage are connected.

4. An all-electric single-wing spinning unmanned aerial vehicle as claimed in claim 1, wherein: the fuselage and the stationary vane are connected through first connecting piece, first connecting piece includes first connecting seat and carbon-point, first connecting seat and fuselage fixed connection, the one end of carbon-point is passed first connecting seat and is passed through the round pin fixedly, and the other end and the stationary vane of carbon-point are connected.

5. An all-electric single-wing spinning unmanned aerial vehicle as claimed in claim 1, wherein: the carbon plate is connected with the machine body through a second connecting piece, the second connecting piece comprises a second connecting seat and a fixing seat, the second connecting seat comprises a bottom plate parallel to the machine body and an inclined plate connected with the bottom plate, the bottom plate is connected with the machine body, the inclined plate is connected with the fixing seat, and the fixing seat is connected with the carbon plate.

6. An all-electric single-wing spinning unmanned aerial vehicle as claimed in claim 5, wherein: the inclined plate and the bottom plate form an included angle of 135 degrees.

7. An all-electric single-wing spinning unmanned aerial vehicle as claimed in claim 5, wherein: and reinforcing ribs are arranged on two sides of the joint of the bottom plate and the inclined plate.

8. An all-electric single-wing spinning unmanned aerial vehicle as claimed in claim 5, wherein: the fixing seat is provided with a groove, and the carbon plate is inserted into the groove and is positioned and connected through the positioning hole.