CN220786119U

CN220786119U - Turnover wing aircraft

Info

Publication number: CN220786119U
Application number: CN202322522286.7U
Authority: CN
Inventors: 徐航
Original assignee: Anhui Kamote Robot Co ltd
Current assignee: Anhui Kamote Robot Co ltd
Priority date: 2023-09-18
Filing date: 2023-09-18
Publication date: 2024-04-16
Anticipated expiration: 2033-09-18

Abstract

The utility model discloses a turning wing aircraft, which comprises a nacelle and a gliding wing, wherein a power source and a flight control system are arranged in the nacelle, screw supports are arranged on two sides of the wing surface of the gliding wing, the number of screw supports is not less than 4, each screw support is provided with a power screw, a central shaft of the gliding wing is rotatably connected with the nacelle, the power screws are distributed on the circumference of a concentric circle by taking the central shaft as the center of a circle, the power source is connected with a screw motor, and the flight control system controls the screw and the gliding wing to form the turning wing. The utility model has simple and ingenious structural design and flexible control, greatly reduces the flight energy consumption caused by mechanical components, has smaller energy consumption and lower manufacturing cost compared with a fixed wing aircraft with a rotor wing, can take off and land in situ, can glide and can also glide to force landing when the power is insufficient.

Description

Turnover wing aircraft

Technical Field

The utility model relates to a turning wing aircraft, and belongs to the technical field of aircrafts.

Background

The application of the aircraft is very wide, as disclosed in application number 201811222322.5, a single-wing aircraft with rotor wing and fixed-wing flight modes and a mode switching method can realize the speed reduction and the speed increase of the unmanned aerial vehicle and the rotation speed increase and speed reduction of the wing through controllable combined jet flow of the wing end jet holes, autonomously switch the rotor wing-vertical lifting and fixed-wing-high-speed cruising modes, and reduce the energy consumption in the flight process; when the wing is driven to rotate, high-pressure air flow formed by the turbojet engine flows through the cavity of the main shaft and is communicated with the wing end air jet holes, and the main shaft is communicated with the air receiving pipeline through the rotary joint, so that the two wing end air jet holes which are arranged in a diagonal manner jet high-speed air flow to form reverse torque to drive the wing to rotate around the main shaft; the wing rotates to only apply the lifting force of the fuselage, so that the rotor wing vertical take-off and landing function can be realized; the main shaft is provided with an incomplete gear positioning mechanism and a braking mechanism, so that the rotor wing and fixed wing modes are rapidly switched and accurately positioned and are mutually independent; the air supply pipeline can be deformed adaptively when the attack angle of the wing is regulated.

As can be seen from the technical disclosure, in the prior art, if the fixed wing aircraft wants to take off in situ, the fixed wing aircraft needs to be additionally provided with a vertical spiral wing, and at the moment, the fixed wing becomes ascending resistance in the in situ take-off process; the rotor craft is adopted, and no fixed wing is adopted for gliding, so that the rotor craft is not limited by a runway, but the energy consumption is relatively high, the motor power required by the aircraft with larger load is also larger, and therefore the cost is higher, and the research on how to realize the low-cost and high-efficiency in-situ take-off fixed wing aircraft is important.

Disclosure of Invention

The utility model aims to solve the problems in the prior art and provides a more efficient turning wing aircraft.

In order to achieve the above purpose, the utility model adopts the technical means that: the utility model provides a upset wing aircraft, includes nacelle and glide wing, set up power supply and flight control system in the nacelle the airfoil both sides of glide wing all set up the screw support, the screw support sets up 4 or more, all set up power screw on every screw support, the axis and the nacelle swivelling joint of glide wing, and the power screw regards the axis as the centre of a circle to distribute on the circumference of a concentric circle, and the power supply is connected screw motor, and flight control system control screw and glide wing become the upset wing.

Further, 4 screw supports are arranged, wherein 2 screw supports are symmetrically arranged on two sides of the wing surface of the gliding wing, two screw supports are symmetrically arranged on the middle axis, and four screw supports are correspondingly arranged at cantilever ends of the four screw supports respectively.

Furthermore, the rotary connecting shaft of the gliding wings and the nacelle is provided with a band-type brake assembly for locking the angles of the gliding wings and the nacelle.

Furthermore, the band-type brake assembly comprises a disc brake disc and a brake, wherein the disc brake disc is arranged on the rotary connecting shaft, and the brake is connected with the disc brake disc in a braking way.

Furthermore, a group of independent attitude sensors are arranged on the gliding wings and the nacelle, the two groups of attitude sensors are connected with the flight control system, the attitude sensor in the gliding wings is used for identifying the inclination angle of the gliding wings, and the attitude sensor in the nacelle is used for identifying the azimuth.

Furthermore, a nacelle supporting leg is arranged below the nacelle, walking wheels are arranged on the nacelle supporting leg in a triangle shape, wherein two universal wheels are arranged below the front supporting leg, and a directional wheel is arranged on the rear supporting leg.

The beneficial technical effects of the utility model are as follows: the aircraft has the advantages of simple and ingenious structural design, flexible control, great reduction of flight energy consumption caused by mechanical components, smaller energy consumption compared with a fixed wing aircraft with an additional rotor, lower manufacturing cost, realization of vertical take-off and landing, and capability of landing in a gliding posture when power is insufficient.

Drawings

The utility model is further illustrated in the following figures and examples.

FIG. 1 is a schematic diagram of the glide gesture structure of the present utility model;

fig. 2 is a schematic view of the vertical take-off and landing attitude structure of the present utility model.

In the figure: 1. nacelle, 2, screw bracket, 3, glider, 4, screw motor, 5, screw, 6, axis, 7, disk brake dish, 8, stopper, 9, nacelle landing leg, 10, universal wheel.

Detailed Description

Example 1

The turning wing aircraft shown in fig. 1 and 2 comprises a nacelle 1 and a gliding wing 3, wherein a power source and a flight control system are arranged in the nacelle 1, propeller supports 2 are arranged on two sides of an airfoil of the gliding wing 3, 4 propeller supports 2 are arranged, 2 groups of propeller supports are symmetrically arranged on two sides of the airfoil of the gliding wing 3, two groups of propeller supports 2 are symmetrically arranged on a central axis, and four propellers 5 are respectively and correspondingly arranged at cantilever ends of the four propeller supports 2. The center shaft 6 of the gliding wings 3 is rotatably connected with the nacelle 1, the power propellers 5 are distributed on the circumference of a concentric circle by taking the center shaft 6 as the center of a circle, the power source is connected with the propeller motor 4, and the flight control system controls the propellers 5 and the gliding wings 3 to form the overturning wings.

Here, as a modification of the structure, the propeller 5 can be distributed on the circumference of one concentric circle with the center axis 6 as the center, even if the propeller mount 2 is not symmetrically provided.

As a control method, in a take-off stage, a flight control system adjusts the angle of the glide wing to a state that the glide wing is vertical to the ground by detecting the inclination angle of the glide wing and the horizontal plane, and realizes in-situ take-off by a propeller. The reverse operation is needed during landing, when the aircraft is in a gliding state, the steering control during the gliding can be realized by adjusting the rotating speed difference of the rotor wings at two sides, and the control during the hovering is the same as that of the existing rotorcraft; when the system detects that the power is insufficient, the system automatically controls the band-type brake to lock the angle between the overturning wings and the nacelle, so that the gliding wings are parallel to the horizontal plane, and the aircraft glides and falls.

A pod leg 9 is arranged under the pod 1, and the triangular travelling wheels are arranged on the pod leg 9, wherein two universal wheels 10 are arranged under the front leg, and the directional wheels are arranged on the rear leg. With this structure, a gliding drop is ensured.

As a structural design for controlling the angle, a band-type brake assembly is arranged on a rotary connecting shaft of the glider 3 and the nacelle 1 and used for locking the angle of the glider 3 and the nacelle 1.

As a control structural design, a group of independent attitude sensors are arranged on the gliding wings 3 and the nacelle 1, the two groups of attitude sensors are connected with a flight control system, the attitude sensors in the gliding wings are used for inclination angle recognition of the gliding wings, and the attitude sensors in the nacelle are used for azimuth recognition.

As band-type brake structural design, band-type brake subassembly includes dish brake dish 7, stopper 8, and dish brake dish 7 is installed on the swivelling joint axle, and stopper 8 is connected with the braking of dish brake dish 7, and flight control system connects and controls stopper 8.

The above embodiments are for illustrating the technical solution of the present utility model, but not for limiting the technical solution of the present utility model, and all simple modifications based on the technical solution of the present utility model should be considered as the protection scope of the present utility model.

Claims

1. A roll-over wing aircraft, characterized in that: the aircraft comprises a nacelle and a gliding wing, wherein a power source and a flight control system are arranged in the nacelle, screw supports are arranged on two sides of an airfoil of the gliding wing, the number of screw supports is not less than 4, power screw supports are arranged on each screw support, a central shaft of the gliding wing is rotatably connected with the nacelle, the power screw is distributed on the circumference of a concentric circle by taking the central shaft as the center of a circle, the power source is connected with a screw motor, and the flight control system controls the screw and the gliding wing to form a turnover wing.

2. The roll-over wing aircraft of claim 1, wherein: the number of the propeller supports is 4, 2 of the propeller supports are symmetrically arranged on two sides of the wing surface of the gliding wing, two groups of the propeller supports are symmetrically arranged on the middle axis, and four propellers are correspondingly arranged at the cantilever ends of the four propeller supports respectively.

3. The roll-over wing aircraft of claim 1, wherein: and the rotary connecting shaft of the gliding wings and the nacelle is provided with a band-type brake assembly for locking the angles of the gliding wings and the nacelle.

4. A roll-over wing aircraft according to claim 3, wherein: the band-type brake assembly comprises a disc brake disc and a brake, wherein the disc brake disc is arranged on the rotary connecting shaft, and the brake is connected with the disc brake disc in a braking way.

5. A roll-over wing aircraft according to claim 3, wherein: and a group of independent attitude sensors are arranged on the gliding wings and the nacelle, the two groups of attitude sensors are connected with a flight control system, the attitude sensor in the gliding wings is used for identifying the inclination angle of the gliding wings, and the attitude sensor in the nacelle is used for identifying the azimuth.

6. The roll-over wing aircraft of claim 1, wherein: the nacelle is provided with nacelle supporting legs below, the nacelle supporting legs are provided with walking wheels in a triangle shape, wherein two universal wheels are arranged below the front supporting legs, and the rear supporting legs are provided with directional wheels.