CN116424551A

CN116424551A - Unmanned aerial vehicle with tilting, folding and wing-folding variants

Info

Publication number: CN116424551A
Application number: CN202310449991.0A
Authority: CN
Inventors: 朱云涛; 汪军宏; 王苑硕; 张命辉; 陈迪; 熊峻江
Original assignee: Beihang University
Current assignee: Beihang University
Priority date: 2023-04-25
Filing date: 2023-04-25
Publication date: 2023-07-14

Abstract

A tilting wing-folding variant unmanned aerial vehicle comprises a fuselage, a tilting wing-folding wing, a landing gear, a tail wing, a main rotor wing and a tail rotor wing. The vertical take-off and landing and fixed wing state cruising can be realized through tilting the folded wings, and the wings can be folded to reduce the space occupied by ground parking. The tilting folded wing moves backwards when tilting from a vertical take-off and landing state to a fixed wing state, so that the focus of the wing is positioned behind the gravity center when the fixed wing state flies, and the whole aircraft has static stability. The tilting wing folding variant unmanned aerial vehicle solves the problems that the fixed wing state of the existing tilting wing unmanned aerial vehicle does not have static stability and the occupied space is large when the wing is unfolded and caused by ground parking through reasonable matching and connection of all the components.

Description

Unmanned aerial vehicle with tilting, folding and wing-folding variants

Technical Field

The invention relates to the field of unmanned aerial vehicles, in particular to a tilting and folding wing variant unmanned aerial vehicle.

Background

The tilting wing unmanned aerial vehicle changes the thrust vector direction through the tilting wing, thereby having the capability of vertical take-off and landing and fixed-point hovering of the multi-rotor aircraft and having the characteristics of high-speed and low-power consumption cruising of the fixed-wing aircraft. Compared with a tilting rotor wing and rotor wing/fixed wing composite unmanned aerial vehicle, the tilting rotor wing unmanned aerial vehicle has better hovering efficiency and better cruising efficiency, and has important engineering application value. In order to meet the stability of the vertical state, the gravity center of the tilting wing unmanned aerial vehicle is generally located behind the wing, but when the tilting wing unmanned aerial vehicle is switched to the fixed wing state to fly flatly, the focus of the wing is located in front of the gravity center, so that the flying stability of the tilting wing unmanned aerial vehicle is poor. Meanwhile, in order to ensure a high-speed and high-efficiency flat flight state, the tilting wing unmanned aerial vehicle usually adopts a large aspect ratio configuration, and because wings cannot be folded, the wings occupy a large space when parked on the ground, which severely limits the application of the tilting wing unmanned aerial vehicle in the military/civil field (such as carrier-borne aircraft, future urban three-dimensional traffic and the like).

In order to overcome the defects, the invention provides the tilting wing folding variant unmanned aerial vehicle, which is translated to the rear of the fuselage while the wings tilt, so that the focus of the wings is positioned at the rear of the center of gravity in a fixed wing flight state, and the whole unmanned aerial vehicle has good static stability. Meanwhile, the foldable high aspect ratio wing obviously reduces the occupied space when the ground is parked, and reconciles the contradiction between the cruising efficiency and the occupied space when the ground is parked.

Disclosure of Invention

1. The purpose is as follows: the invention aims to provide a tilting folding wing variant unmanned aerial vehicle which has good static flight stability of a fixed wing and reduces occupied space when parking on the ground.

2. The technical scheme is as follows: a tilt-turn wing-fold variant unmanned aerial vehicle, comprising: fuselage, tilting fold wing, landing gear, tail wing, main rotor wing, tail rotor wing; the tilting folding wing is positioned in the middle of the fuselage, the tail wing is positioned at the rear part of the fuselage, and the tail rotor wing is positioned at the tail part of the fuselage. When the inclined folding wing chord line is perpendicular to the axis of the fuselage, the tension vectors of the main rotor wing and the tail rotor wing are all vertical upwards, and at the moment, the inclined folding wing variant unmanned aerial vehicle can perform vertical lifting actions, and rolling, pitching, yawing, ascending, descending, advancing and retreating actions are controlled by utilizing the tension vector changes of the main rotor wing and the tail rotor wing. When the chord line of the tilting and folding wing is parallel to the axis of the fuselage, the tilting and folding wing variant unmanned aerial vehicle can fly in a traditional fixed wing aircraft state, and rolling, pitching and yawing actions are controlled by utilizing ailerons, elevators and rudders.

The machine body is characterized by comprising a battery, a flight control device, a steering engine and a tilting mechanism. Further, the fuselage is connected with the tilting folding wing, the tail wing, the landing gear and the tail rotor wing to form a whole.

The machine body is characterized by comprising side plates, a top plate and a reinforcing frame. Further, the side plates and the top plate are provided with hollowed-out parts for reducing weight.

The machine body is characterized in that a protection device for preventing the tail rotor wing from colliding with the ground is arranged at the tail part.

The tilting folded wing is characterized in that the wing can tilt 0-90 degrees relative to the fuselage around an axis vertical to the fuselage, and the main rotor wing is driven to tilt synchronously. Further, the tilt fold wing can translate relative to the fuselage during tilting.

The tilting wing is characterized in that when the chord line of the tilting wing is vertical to the ground, the tilting wing can rotate around an axis parallel to the chord line of the tilting wing, so that the purpose of reducing the parking occupied space of the tilting wing variant unmanned aerial vehicle is achieved.

The tilting folding wing is characterized in that a bracket is arranged at the wing tip, and the supporting function is achieved when the chord line of the tilting folding wing is perpendicular to the ground.

The landing gear is characterized by comprising a front wheel and a main wheel. Further, the front wheel is positioned in front of the machine body and can rotate left and right to control the tilting wing-folding variant unmanned aerial vehicle to turn on the ground; the main wheel is positioned behind the gravity center of the tilting wing-folding variant unmanned aerial vehicle and in the middle of the fuselage so as to reduce the bending moment born by the fuselage when the tilting wing-folding variant unmanned aerial vehicle is parked on the ground.

The tail fin is characterized by comprising a vertical fin and a horizontal fin. The horizontal tail is positioned above the vertical tail and is integrally arranged in a T shape, so that the inclined folding wing is prevented from interfering with the horizontal tail when being folded.

The main rotor wing is characterized in that the main rotor wing is fixed on the foldable part of the tilting folding wing.

The tail rotor wing is characterized in that the tail rotor wing can tilt around the axis of the machine body, and the tilting range is +/-45 degrees, so that the yaw movement of the tilting wing folding variant unmanned aerial vehicle is controlled.

3. The advantages and the effects are as follows: the tilting wing-folding variant unmanned aerial vehicle has good static stability when flying in a fixed wing state through the coupling of wing tilting and translational motion. Meanwhile, the foldable wing obviously reduces the occupied space of the unmanned aerial vehicle when the unmanned aerial vehicle is parked on the ground.

Drawings

The invention is further illustrated by the following figures and examples:

FIG. 1 is a schematic view of a wing fold condition;

FIG. 2 is a schematic view of a vertical take-off and landing state;

FIG. 3 is a fixed wing state diagram;

fig. 4 is a schematic diagram of a tilt-fold wing variant unmanned aerial vehicle;

in fig. 4: the component 1 is a tilting folding wing, the component 2 is a main rotor wing, the component 3 is a fuselage, the component 4 is a tail wing, the component 5 is a tail rotor wing, and the component 6 is a landing gear.

Detailed Description

Specific embodiments of the present invention will be described with reference to fig. 1 to 4:

the invention relates to a tilting folding wing variant unmanned aerial vehicle, which is characterized by comprising the following components: fuselage, tilting fold wing, landing gear, tail wing, main rotor wing, tail rotor wing; the tilting folding wing is positioned in the middle of the fuselage, the tail wing is positioned at the rear part of the fuselage, and the tail rotor wing is positioned at the tail part of the fuselage.

When the tilting folding wing variant unmanned aerial vehicle is parked on the ground, the tilting folding wing can be folded towards the rear side of the machine body, so that the occupied space is reduced during parking.

The tilting folded wing can translate along the axis of the machine body when tilting, and the focus of the wing is positioned behind the gravity center of the whole machine when flying in a fixed wing state, so that the whole machine has static stability.

When the inclined folding wing chord line is perpendicular to the axis of the fuselage, the tension vectors of the main rotor wing and the tail rotor wing are all vertical upwards, and at the moment, the inclined folding wing variant unmanned aerial vehicle can perform vertical lifting actions, and rolling, pitching, yawing, ascending, descending, advancing and retreating actions are controlled by utilizing the tension vector changes of the main rotor wing and the tail rotor wing.

When the chord line of the tilting and folding wing is parallel to the axis of the fuselage, the tilting and folding wing variant unmanned aerial vehicle can fly in a traditional fixed wing aircraft state, and rolling, pitching and yawing actions are controlled by utilizing ailerons, elevators and rudders.

Claims

1. A tilt-turn wing-fold variant unmanned aerial vehicle, comprising: fuselage, tilting fold wing, landing gear, tail wing, main rotor wing, tail rotor wing; the wing is folded to the tilting and is located the fuselage middle part, the fin be located the fuselage rear portion, the tail rotor be located the fuselage afterbody, when the wing chord line is folded to the tilting and is perpendicular to the axis of fuselage, main rotor and tail rotor pulling force vector all vertically upwards, the wing variant unmanned aerial vehicle of tilting and folding this moment can take off and land the action perpendicularly, utilize main rotor and tail rotor pulling force vector change control roll, every single move, driftage, rise, decline, advance, retreat action, when the wing chord line is folded to the tilting and folding the wing chord line parallel to the axis of fuselage, the wing variant unmanned aerial vehicle of tilting and folding can fly with traditional fixed wing aircraft state level, utilize aileron, elevator, rudder control roll, every single move, yaw action.

The fuselage of claim 1, comprising a battery, flight controls, steering engines, tilting mechanisms, further wherein the fuselage is integrally connected to the tilting fold wing, tail wing, landing gear, tail rotor.

The airframe as recited in claim 1, further comprising side panels, top panel and reinforcing frame, wherein the side panels and top panel have hollowed-out portions for weight reduction purposes.

The fuselage of claim 1, wherein the tail section has a protective means to prevent the tail rotor from rubbing against the ground.

The tilt-turn wing according to claim 1, wherein the tilt-turn wing is tiltable about an axis perpendicular to the fuselage by 0-90 degrees relative to the fuselage to effect synchronous tilting of the main rotor, and further wherein the tilt-turn wing is translatable relative to the fuselage during tilting, and wherein the tilt-turn wing focal point is located behind the center of gravity of the tilt-turn wing variant drone when the chord line is parallel to the fuselage axis.

The tilt-turn wing according to claim 1, wherein the tilt-turn wing variant unmanned aerial vehicle is rotatable about an axis parallel to its chord line when perpendicular to the ground, for the purpose of reducing the parking footprint of said tilt-turn wing variant unmanned aerial vehicle.

The tilt-turn wing according to claim 1, wherein a bracket is provided at the wing tip for supporting the tilt-turn wing chord line when it is perpendicular to the ground.

The landing gear of claim 1, comprising a front wheel and a main wheel, further wherein the front wheel is positioned in front of the fuselage and is rotatable left and right to control steering of the tilt-turn wing variant unmanned aerial vehicle on the ground; the main wheel is positioned behind the gravity center of the tilting wing-folding variant unmanned aerial vehicle and in the middle of the fuselage so as to reduce the bending moment born by the fuselage when the tilting wing-folding variant unmanned aerial vehicle is parked on the ground.

The tail wing according to claim 1, comprising a tail and a tail, wherein the tail is positioned above the tail and is integrally arranged in a T-shape to prevent the inclined folding wing from interfering with the tail when folded.

The main rotor of claim 1, wherein said tilt-turn wing is secured to said foldable wing sections.

The tail rotor of claim 1, wherein the tail rotor is tiltable about an axis of the fuselage to a range of ± 45 degrees to control yaw movement of the tilt-turn wing-fold variant drone.