CN212861843U

CN212861843U - Aircraft with adjustable wing angle

Info

Publication number: CN212861843U
Application number: CN202021779854.1U
Authority: CN
Inventors: 姚英雷
Original assignee: Individual
Current assignee: Individual
Priority date: 2020-08-24
Filing date: 2020-08-24
Publication date: 2021-04-02
Anticipated expiration: 2030-08-24

Abstract

The utility model discloses an aircraft with adjustable wing angle, which relates to the technical field of aircraft and comprises a fuselage, wherein a master control integrated circuit board is arranged in the fuselage, wings are symmetrically arranged on two sides of the fuselage, a first turntable is connected between the wings and the fuselage, first engines are arranged at the bottom ends of the two wings, the front ends of the first engines are rotatably connected with first propellers, and two tail parts of the fuselage are symmetrically provided with two tail wings; and the power consumption of the aircraft is greatly reduced, the flight mileage of the aircraft can be increased, and the practicability of the aircraft is improved.

Description

Aircraft with adjustable wing angle

Technical Field

The utility model belongs to the technical field of the aircraft, concretely relates to wing angle adjustable aircraft.

Background

An aircraft is an instrumental flying object made by humans, capable of flying off the ground, flying in space and controlled by humans, flying in the atmosphere or in the extraterrestrial space (space). Most of the existing aircrafts are fixed wings, and the control flight attitude is mainly adjusted by a gyroscope.

However, the existing aircraft has the problems of large wind resistance and slow flying speed in the takeoff stage and horizontal flight in the use process, so that the energy consumption of the aircraft is increased, and the flying mileage is shortened.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a wing angle adjustable aircraft to solve the problem that proposes in the above-mentioned background art, can effectually reduce the windage, reach the effect that improves aircraft take-off speed and airspeed.

In order to achieve the above object, the utility model provides a following technical scheme: an aircraft with adjustable wing angle comprises a fuselage, wherein a master control integrated circuit board is arranged inside the fuselage, wings are symmetrically arranged on two sides of the fuselage, a first rotary table is connected between each wing and the fuselage, a first engine is arranged at the bottom ends of the two wings, the front ends of the first engines are respectively and rotatably connected with a first propeller, two tail portions of the fuselage are symmetrically provided with two tail wings, a second rotary table is connected between the two tail wings and the fuselage, a second engine is arranged at the bottom ends of the two tail wings, the front ends of the two second engines are respectively and rotatably connected with a second propeller, a third electro-hydraulic push rod and a fourth electro-hydraulic push rod are symmetrically hinged on two sides of the fuselage below the two wings through hinge seats, and the top ends of the two third electro-hydraulic push rods and the fourth electro-hydraulic push rods are respectively hinged with the two sides of the bottoms of the two wings, the two sides of the machine body are located below the two tail wings, and are symmetrically hinged with first electro-hydraulic push rods and second electro-hydraulic push rods through hinged seats, and the top ends of the first electro-hydraulic push rods and the second electro-hydraulic push rods are hinged with the two sides of the bottoms of the two tail wings respectively.

Preferably, reinforcing rods are installed at the top and the bottom of each of the two wings, and one ends, far away from the wings, of the four reinforcing rods are connected with the first rotating disc.

Preferably, the rotation angle of the two wings is 0-90 degrees.

Preferably, the rotation angle of both of said tail wings ranges from 0 to 90 °.

Preferably, the tail ends of the first engine and the second engine are both provided with heat dissipation holes, and the heat dissipation holes are rectangular in different sizes.

Compared with the prior art, the beneficial effects of the utility model are that:

(1) the utility model makes the angle of the propeller adapt to the taking-off or flying posture of the aircraft by adjusting the angle of the wing, thereby effectively reducing the resistance of the aircraft during flying and greatly improving the taking-off speed and flying speed of the aircraft; and the power consumption of the aircraft is greatly reduced, the flight mileage of the aircraft can be increased, and the practicability of the aircraft is improved.

(2) And simultaneously, the utility model discloses utilize the wing to rotate to vertical state, can make the screw up, when the engine drive screw rotates, can provide lift for the aircraft can take off perpendicularly, thereby realizes that the aircraft not only can flat fly, still can take off perpendicularly, makes taking off of aircraft can adjust according to the flight demand, the effectual practicality that has increased the aircraft.

Drawings

Fig. 1 is a schematic structural view of the present invention;

fig. 2 is a bottom view of the present invention;

FIG. 3 is a schematic view of the structure of the wing and the tail of the present invention after rotation;

fig. 4 is a schematic view of the internal structure of the fuselage of the present invention;

in the figure: 1-a fuselage; 2-an airfoil; 3-a first propeller; 4-a first engine; 5-a reinforcing rod; 6-a first turntable; 7-a second propeller; 8-tail fin; 9-a second engine; 10-a second turntable; 11-a first electro-hydraulic push rod; 12-a second electro-hydraulic push rod; 13-a third electro-hydraulic push rod; 14-a fourth electro-hydraulic push rod; 15-master control integrated circuit board.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

Referring to fig. 1-4, the present invention provides the following technical solutions: an aircraft with an adjustable wing angle comprises an aircraft body 1, a main control integrated circuit board 15 is installed inside the aircraft body 1, a power supply module, a control module and a communication module are integrated on the main control integrated circuit board 15, wherein the power supply module is used for supplying power to the aircraft so as to facilitate the flight of the aircraft, the control module is used for controlling the operation of electrical components of the aircraft so as to facilitate the adjustment of wings 2 of the aircraft, the communication module is used for realizing the wireless connection of the aircraft and a remote terminal so as to facilitate the remote control and data transmission of the aircraft, wings 2 are symmetrically arranged on two sides of the aircraft body 1, a first rotating disc 6 is connected between the two wings 2 and the aircraft body 1, first engines 4 are installed at the bottom ends of the two wings 2, first propellers 3 are rotatably connected at the front ends of the two first engines 4, and two tail wings 8 are symmetrically arranged at the, a second rotary table 10 is connected between the two empennages 8 and the fuselage 1, second engines 9 are mounted at the bottom ends of the two empennages 8, the first engine 4 and the second engine 9 are electrically connected with a master control integrated circuit board 15, the front ends of the two second engines 9 are rotatably connected with second propellers 7, third electro-hydraulic push rods 13 and fourth electro-hydraulic push rods 14 are symmetrically hinged at the two sides of the fuselage 1 below the two wings 2 through hinge seats, the third electro-hydraulic push rods 13 and the fourth electro-hydraulic push rods 14 are electrically connected with the master control integrated circuit board 15, the top ends of the two third electro-hydraulic push rods 13 and the fourth electro-hydraulic push rods 14 are hinged with the two sides of the bottoms of the two wings 2, first electro-hydraulic push rods 11 and second electro-hydraulic push rods 12 are symmetrically hinged at the two sides of the fuselage 1 below the two empennages 8 through hinge seats, the first electro-hydraulic push rods 11 and the second electro-hydraulic push rods 12 are electrically connected with the master control integrated circuit, the top ends of the two first electro-hydraulic push rods 11 and the second electro-hydraulic push rods 12 are respectively hinged with the two sides of the bottom of the two tail wings 8.

Specifically, when the flying vehicle is used, a user can wirelessly connect the flying vehicle with a remote terminal through a communication module on a main control integrated circuit board 15 and send a flying command through the remote terminal, at the moment, a control module on the main control integrated circuit board 15 controls a first engine 4 and a second engine 9 to work, so that the first engine 4 drives a first propeller 3 to rotate, the second engine 9 drives a second propeller 7 to rotate so as to propel the flying vehicle to take off until the flying vehicle flies up, the user can control the angles of the wings 2 and the empennage 8 to be adjusted through the remote terminal in the flying process of the flying vehicle, namely, the remote terminal sends a command, the communication module on the main control integrated circuit board 15 receives the command and feeds the command back to the control module, then the control module controls a third electro-hydraulic push rod 13 to contract, a fourth electro-hydraulic push rod 14 to extend, so that the wings 2 and the body 1 rotate relatively, therefore, the angle adjustment of the wing 2 is realized, meanwhile, the control module controls the first electro-hydraulic push rod 11 to contract and the second electro-hydraulic push rod 12 to extend, so that the empennage 8 rotates relative to the fuselage 1 under the action of the second rotary disc 10, the angle of the empennage 8 is changed, the wing 2 and the empennage 8 can be adjusted according to the flight requirement, the resistance of the aircraft during flight can be effectively reduced, and the takeoff speed and the flight speed of the aircraft can be improved; the power consumption of the aircraft is greatly reduced, and the flight mileage of the aircraft can be increased;

in addition, in this embodiment, if the aircraft needs to take off vertically, the user can control the angle adjustment of the wing 2 and the tail wing 8 of the aircraft through the remote terminal, so that the wing 2 and the tail wing 8 of the aircraft rotate to the vertical state, at this time, the first screw propeller 3 and the second screw propeller 7 are driven by the wing 2 and the tail wing 8 to be in the upward state, and then the first screw propeller 3 and the second screw propeller 7 are respectively driven by the first engine 4 and the second engine 9 to rotate, so as to provide lift force for the aircraft, so that the aircraft takes off vertically, so that the taking off of the aircraft can be changed according to the flight requirement, and the improvement of the practicability of the aircraft is facilitated.

Furthermore, reinforcing rods 5 are installed at the tops and the bottoms of the two wings 2, one ends, far away from the wings 2, of the four reinforcing rods 5 are connected with the first rotating disc 6, and the stability of the wings 2 and the first rotating disc 6 during connection can be improved through the reinforcing rods 5, so that the wings 2 and the first rotating disc 6 are stable, and the rotation adjustment of the wings 2 is facilitated.

Specifically, the rotation angle ranges of the two wings 2 are both 0 to 90 °, when the rotation angle is 0 °, the wings 2 are in a horizontal state, when the rotation angle is between 0 to 90 °, the wings 2 are in an inclined state, and when the rotation angle is 90 °, the wings 2 are in a vertical state, so that the angle adjustment of the wings 2 is realized.

It should be noted that the rotating angle ranges of the two tail wings 8 are both 0 to 90 degrees, when the rotating angle is 0 degree, the tail wings 8 are in a horizontal state, when the rotating angle is 0 to 90 degrees, the tail wings 8 are in an inclined state, and when the rotating angle is 90 degrees, the tail wings 8 are in a vertical state, thereby realizing the angle adjustment of the tail wings 8.

Furthermore, heat dissipation holes are formed in the tail ends of the first engine 4 and the second engine 9, and the heat dissipation holes are rectangular and have different sizes, so that efficient heat dissipation of the first engine 4 and the second engine 9 is facilitated, and normal work of the first engine 4 and the second engine 9 is guaranteed.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.

Claims

1. An aircraft with adjustable wing angle, which is characterized in that: including fuselage (1), the internally mounted of fuselage (1) has master control integrated circuit board (15), and the bilateral symmetry of fuselage (1) is provided with wing (2), two all be connected with first carousel (6) between wing (2) and fuselage (1), and all install first engine (4) between the bottom of two wing (2), two the front end of first engine (4) all rotates and is connected with first screw (3), the afterbody symmetry of fuselage (1) is provided with two fin (8), and all is connected with second carousel (10), two between two fin (8) and fuselage (1) second engine (9) are all installed to the bottom of fin (8), and the front end of two second engine (9) all rotates and is connected with second screw (7), the both sides of fuselage (1) and the below that is located two wing (2) all articulate through articulated seat symmetry have third electrohydraulic push rod (13) and fourth electrohydraulic push away The top of third electricity liquid push rod (13) and fourth electricity liquid push rod (14) is articulated mutually with the bottom both sides of two wings (2) respectively, the below that the both sides of fuselage (1) just are located two fin (8) all articulates through articulated seat symmetry has first electricity liquid push rod (11) and second electricity liquid push rod (12), two the top of first electricity liquid push rod (11) and second electricity liquid push rod (12) is articulated mutually with the bottom both sides of two fin (8) respectively.

2. The aircraft of claim 1, wherein: two stiffener (5) are all installed to the top and the bottom of wing (2), and four stiffener (5) keep away from the one end of wing (2) and all are connected with first carousel (6).

3. The aircraft of claim 1, wherein: the rotation angle ranges of the two wings (2) are both 0-90 degrees.

4. The aircraft of claim 1, wherein: the rotating angle ranges of the two tail wings (8) are both 0-90 degrees.

5. The aircraft of claim 1, wherein: the tail ends of the first engine (4) and the second engine (9) are provided with heat dissipation holes, and the heat dissipation holes are rectangular in different sizes.