CN110667837A

CN110667837A - Novel vector thrust dislocation double-wing tailstock type vertical take-off and landing unmanned aerial vehicle

Info

Publication number: CN110667837A
Application number: CN201910825514.3A
Authority: CN
Inventors: 朱恩桐; 陈泽峰
Original assignee: Northwest University of Technology
Current assignee: Northwestern Polytechnical University; Northwest University of Technology
Priority date: 2019-08-30
Filing date: 2019-08-30
Publication date: 2020-01-10

Abstract

The invention discloses a novel vector thrust dislocation double-wing tailstock type vertical take-off and landing unmanned aerial vehicle. The unmanned aerial vehicle is provided with two auxiliary wings which are arranged in a vertically staggered mode, wherein the wings are supported by upper and lower wing supporting plates, and a tail rudder surface is arranged at the tail part of each supporting plate. The middle machine body is connected with the upper and lower wing supporting plates on the left and right by two carbon fiber pipes. The double-engine vector power system is fixed on the front carbon fiber pipe. According to the invention, under the condition of effectively controlling the occupied area and windward area of the tailstock type unmanned aerial vehicle, the effective lift area is increased, the load-carrying performance is improved, and the control performance is improved by the design of the short-tail full-motion control surface. The unmanned aerial vehicle is particularly suitable for short-distance high-flexibility detection and use, and is applied to expressway evasion tracking like public security departments.

Description

Novel vector thrust dislocation double-wing tailstock type vertical take-off and landing unmanned aerial vehicle

Technical Field

The invention relates to the technical field of aviation, in particular to a tailstock type vertical take-off and landing unmanned aerial vehicle.

Background

Currently, mainstream vertical take-off and landing unmanned aerial vehicles in the world comprise two main types: one is a composite wing unmanned plane formed by a conventional fixed wing and an additional rotor component, such as the scheme of patent No. CN110116802A, and the other is a flying wing type tailless layout, such as the scheme of patent No. CN 207580149U. These two types of unmanned aerial vehicles respectively have the advantage and disadvantage, first kind of compound wing unmanned aerial vehicle takes off and land the in-process and uses many rotor subassemblies to provide lift and control moment, the advantage is that the organism is steady with the conversion in-process taking off and land, relative loading capacity is great, the shortcoming is that four plus rotors and driving system only play a role in the in-process taking off and land, and do not provide power at the flat in-process that flies, but as unnecessary subassembly, increase the extra heavy burden that flies flat, also cause certain air resistance, overall efficiency is lower.

And moreover, the tail sitting type unmanned aerial vehicle with the flying wings in a tailless layout has a vertical fuselage in the vertical take-off and landing process, a rotor plane is perpendicular to the gravity direction of the aircraft when taking off and hovering, and is perpendicular to the ground horizontal plane when flying horizontally, so that the unmanned aerial vehicle needs to tilt the whole fuselage by 90 degrees in the process of switching flight postures, and is more complex when being designed for control laws. In addition, because the layout of the unmanned aerial vehicle is limited, the unmanned aerial vehicle adopts a reverse camber airfoil, and has the defects of lower overall lift force, limited load capacity and higher horizontal flying speed. Its advantage does not use unnecessary power among the vertical take-off and landing process, is to incline through the fuselage and vert and realize the conversion that level flies and vertical take-off and landing, and aerodynamic efficiency is higher with structure availability factor.

Disclosure of Invention

The invention aims to solve the problems of small lift coefficient, small load capacity, high lower limit of flat flying speed and poor wind resistance of the conventional tailstock type unmanned aerial vehicle, improve the diversity of task loads, environmental adaptability and tilting flexibility, and expand the application range of tasks.

In order to achieve the purpose, the tail seat type unmanned aerial vehicle is in a staggered upper and lower double-wing short-tail layout, the double-wing type adopts a large-bending high-lift wing type, and the short tail is provided with a full-motion elevon to replace a conventional wing trailing edge control surface. Furthermore, the unmanned aerial vehicle uses the left and right double propellers to provide static thrust and position height in the vertical take-off and landing and hovering processes. And a vector power mechanism and the deflection of the tail control surface are utilized to provide moment to carry out attitude control and wind resistance operation. The vector power mechanism is composed of a vector motor base, a motor, a propeller, a vector tilting steering engine and an electric regulator. The vector motor base is arranged on the supporting carbon fiber pipe

The aircraft body assembly is made of aviation laminates and is fixed with the aircraft through a front carbon fiber tube and a rear carbon fiber tube which penetrate through the aircraft body. Because this unmanned aerial vehicle adopts the modularized design, the fuselage can carry out simple and convenient replacement through taking out two carbon fiber tubes according to the task load of difference.

Through foretell design organization mode, this unmanned aerial vehicle aircraft nose is vertical upwards when taking off and landing, and the foot rest that extends by upper and lower wing fagging provides the support. During take-off, unmanned aerial vehicle provides power through two vector driving system, and vector motor mechanism deflects when flying to the tie, and the tail is gone up full-motion elevator simultaneously and is deflected, provides sufficient moment and drives unmanned aerial vehicle and vert, gets into the tie and flies. The flat flight in-process, upper and lower wing provides most lift, wherein, compares in the design of conventional flying wing tailless overall arrangement, and this unmanned aerial vehicle's upper and lower straight wing dislocation design can also make wing moment part balanced each other, relies on the moment reduction on the tail, has improved the mobility when reducing trim lift loss. The design improves the lift coefficient of the whole machine, effectively reduces the lower limit of the horizontal flying speed, increases the effective load and improves the maneuvering performance.

Furthermore, due to the staggered double-wing design, the wing projection area of the unmanned aerial vehicle is about 1.3 times of that of a single wing while the effective wing area is increased by about two times, the wing projection area is not obviously increased, and the wind resistance is effectively improved in a vertical take-off and landing state. The vector thrust system can change the direction of a tension line, and effectively improves maneuverability and wind resistance stability in a vertical take-off and landing state.

Furthermore, the unmanned aerial vehicle has compact design, the fuselage and the wings are easy to replace due to modularized design, wherein the upper wing supporting plate and the lower wing supporting plate play a structure multiplexing design, can support the upper wing and the lower wing, and are used as lifting support frames to be connected with full-motion lifting ailerons.

Drawings

The invention is explained below with reference to the drawings

FIG. 1 is a schematic view of an overall novel vector thrust staggered double-wing tailstock type vertical take-off and landing unmanned aerial vehicle

FIG. 2 is a schematic diagram of a novel vector thrust dislocation double-wing tailstock type vertical take-off and landing unmanned aerial vehicle upper and lower wing supporting plates and control surface assembly

FIG. 3 is a schematic view of a novel vector thrust dislocation two-wing tailstock type vertical take-off and landing unmanned aerial vehicle body assembly

FIG. 4 is a schematic view of a novel vector thrust dislocation double-wing tailstock type dual-generator vector power assembly of a vertical take-off and landing unmanned aerial vehicle

FIG. 5 is a schematic view of a hovering attitude of a novel vector thrust dislocation double-wing tailstock type VTOL UAV

Detailed Description

The present invention will be described in detail with reference to the accompanying drawings.

As shown in fig. 1, the novel vectored thrust dislocation double-wing tailstock type vertical take-off and landing drone comprises an upper wing surface 102, a lower wing surface 101, a right aileron lifting control surface 103, a left aileron lifting surface 104, an upper wing supporting plate 105, a right vector power system 107, a left vector power system 108 and a fuselage assembly 109. The upper wing and the lower wing are arranged in a staggered mode from top to bottom and from front to back, and the front edge of the upper wing is closer to the front side than the front edge of the lower wing. When the upper and lower fuselage is connected to upper and lower wing fagging, also fixed the fuselage through two carbon fiber tubes, structural efficiency is high. The left and right double-engine vector power system is arranged at the forefront and is vertically arranged between the upper wing and the lower wing, so that the power and control capability of vertical take-off and landing is provided.

As shown in fig. 2, the upper and lower wing stay plate assemblies have mounting

holes

202 and 201 for connecting the upper wing surface and the lower wing surface, and mounting

holes

203 and 204 for fixing the carbon fiber tubes of the fuselage, the lifting aileron 206 of the unmanned aerial vehicle is fixed at the tail of the upper and lower wing stay plates, the steering gear 207 for controlling the aileron is arranged in the mounting holes of the upper and lower stay plate assemblies, and the rotating arm of the steering gear is connected with the control surface of the lifting aileron through a guide rod, so that the deflection of the control surface is controlled by controlling the rotation of the steering gear. The upper and lower gussets extend rearwardly to form an upright landing gear 205.

As shown in fig. 3, the body of the fuselage assembly is composed of a front cover plate 303, side plates 301, a central plate 302, and an upper cover plate 307, with front and rear carbon

fiber fixing tubes

305, 306. The fuselage is fitted with a full-motion rudder 304. All avionics equipment such as flight control, batteries, cameras, image transmission systems and the like are carried on the aircraft body.

As shown in fig. 4, the vector power system includes a propeller 401, a motor 402, a vector motor base 403, a support rod 404 and an adapter 405. The propeller is directly connected with the motor through double blades, and the motor is arranged on the vector motor base through a screw hole at the bottom of the motor. The vector motor base is fixedly connected with the support rod and the switching installation piece. The vector motor base can deflect the direction of the motor tension, and the flexibility and the wind resistance of the unmanned aerial vehicle are improved.

Finally, it should be noted that the above embodiments of the invention are only used for illustrating the technical solutions of the invention, and are not limited thereto. Any modification, equivalent replacement, and improvement made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A novel vector thrust dislocation double-wing tailstock type vertical take-off and landing unmanned aerial vehicle is characterized by comprising a middle body assembly, an upper wing supporting plate, a lower wing supporting plate, an upper wing assembly, a lower wing assembly, a full-motion lifting aileron and a vector power assembly; the unmanned aerial vehicle is directly driven to tilt through tilting vector power and elevator deflection to realize the horizontal flight state after being converted from the hovering state, the attitude is kept stable by means of static thrust output by the power propeller in the hovering and vertical takeoff and landing stages, and maneuvering actions such as rolling and yawing are realized by means of the elevon in the horizontal flight stage.

2. The novel vector thrust dislocation double-wing tailstock type VTOL UAV of claim 1, wherein the upper and lower wing assemblies are fixed on the upper and lower wing supporting plates, there is a tail wing mechanism fixed on the rear part of the upper and lower wing supporting plates, the middle fuselage is connected with the upper and lower wing supporting plates by a circular pipe beam, and the power device is fixed on the circular pipe beam.

3. The novel vector thrust dislocation double-wing tailstock type vertical take-off and landing unmanned aerial vehicle as claimed in claim 2, wherein the wings are large-camber high-lift wing type, flat wing type, no control surface is arranged on the wings, the upper wing and the lower wing are installed in a front-back dislocation mode, and the front edge of the lower wing is 60 percent of the chord length behind the upper wing.

4. The novel vector thrust dislocation double-wing tailstock type vertical take-off and landing unmanned aerial vehicle as claimed in claim 1, wherein the airframe is provided with aeronautical and electrical equipment such as airspeed head, camera, battery, flight controller, etc.

5. The novel vectored thrust offset twin wing tailstock VTOL UAV of claim 1 wherein the upper wing is located above and in front of the relative position of the lower wing, and the leading edge of the upper wing is located at 60 percent of the chord length of the leading edge of the lower wing to maximize aerodynamic efficiency of the twin wings.