CN105270625A

CN105270625A - Multi-purpose vertical take-off and landing unmanned aerial vehicle

Info

Publication number: CN105270625A
Application number: CN201510698485.0A
Authority: CN
Inventors: 翟剑豪
Original assignee: QING'AN GROUP CO Ltd
Current assignee: QING'AN GROUP CO Ltd; Qingan Group Co Ltd
Priority date: 2015-10-23
Filing date: 2015-10-23
Publication date: 2016-01-27

Abstract

The invention relates to a multi-purpose vertical take-off and landing unmanned aerial vehicle, which belongs to aviation system technology. A flip-wing V-22 Osprey, in which pitching and heading in a vertical take-off and landing state are controlled through periodical variable pitch, is available for tiltrotor aircrafts internationally. The scheme is not available for the tiltrotor aircrafts in domestic at the present stage. The biggest difficulty for the multi-purpose vertical take-off and landing unmanned aerial vehicle is excessive flight condition of the unmanned aerial vehicle from the vertical take-off and landing state to a level-flight state. The multi-purpose vertical take-off and landing unmanned aerial vehicle can take off and land like a helicopter and can also fly like a fixed-wing aircraft; and through the adoption of a coaxial dual-rotor design, the load capacity of the multi-purpose vertical take-off and landing unmanned aerial vehicle can be improved within a limited rotor diameter space. At present, an unmanned aerial vehicle, which can take off and land vertically and can also fly for a long time, is expected for both military use and civil use.

Description

A kind of high-mobility, multipurpose, wheeled vehicle VUAV

Technical field

The present invention relates to a kind of high-mobility, multipurpose, wheeled vehicle VUAV, belong to aviation system technology.

Background technology

Tilt rotor aircraft has V22 " osprey " to adopt pitching and the course of periodically variable pitch contro l vertical takeoff and landing state in the world.Domestic present stage there is no the program.Maximum difficult point high-mobility, multipurpose, wheeled vehicle VUAV is that aircraft is from vertical lift state to the flat excessive state of flight flying State Transferring.

Summary of the invention

Technical matters to be solved by this invention is: by VUAV of the present invention, has both overcome the speed restriction of helicopter, can overcome again the place restriction of fixed wing aircraft landing.

A kind of high-mobility, multipurpose, wheeled vehicle VUAV, this unmanned plane comprises aileron, large-scale rudder face, wing, tailplane, rotor protective case, fuselage, rotor and vertical tail, described fuselage is flats, the wing that can vert is installed in its two sides, be provided with the rotor synchronously verted at inboard, outside comprises aileron, and described rotor is made up of upper rotor and lower rotor, and there is rotor protective case, at the afterbody of described rotor, large-scale rudder face is installed; At the afterbody of described fuselage, tailplane and vertical tail are installed.

Vertical takeoff and landing state start principle

Control of sideward roll: rely on the different lift control aircraft roll that both sides rotor produces;

Pitch control subsystem: rely on both sides wing to vert and rudder face Hybrid mode aircraft pitch below rotor;

Beneficial effect: high-mobility, multipurpose, wheeled vehicle VUAV can landing as helicopter, also can fly as fixed-wing, adopts coaxial double-rotary wing design can promote load-carrying capacity in limited rotor diameter space.At present military or civilianly all expect a energy and vertical takeoff and landing, unmanned plane during long boat can be had again.This project just in time fills up domestic this respect technological gap, has huge potential market, and the economic profit of great number.

Accompanying drawing explanation

Fig. 1 is the state front view that takes off vertically;

Fig. 2 is the state birds-eye view that takes off vertically;

Fig. 3 is main rotor section-drawing;

Fig. 4 is the state left view that takes off vertically;

Fig. 5 is the state axonometric drawing that takes off vertically;

Fig. 6 puts down to fly state axonometric drawing.

1. aileron 2. large-scale rudder face 3. wing 4. tailplane 5. rotor protective case 6. fuselage

7. rotor 72. times rotor 8. vertical tails on rotor 71.

Detailed description of the invention

Principle prototype design parameter:

Span 1.5M

Fuselage length 1M

Power adopts electro-motor;

Take-off weight is about 1.5Kg;

Maximum take-off weight≤2.5Kg;

Checking aircraft vertical takeoff condition, the controllability of various flight attitude under fixed-wing state and transformation condition three kinds of different modes.

Vertical takeoff and landing flight controls (see Fig. 5):

Control of sideward roll: rely on the different lift control aircraft roll that both sides rotor 7 produces;

Pitch control subsystem: rely on both sides wing 3 to vert and large-scale rudder face 2 Hybrid mode aircraft pitch below rotor 7;

Heading control: rely on the differential start of the large-scale rudder face 2 below two rotors 7 to control vector;

Transition flight state:

Unmanned plane flies state from vertical takeoff and landing condition conversion to flat, first both sides wing 3 verts to heading, (large-scale rudder face 2 mixes start and mainly plays the static and dynamic equilibrium of offsetting and producing when aircraft verts in two auxiliary mixing starts of large-scale rudder face 2, allow fuselage 6 maintenance level), before the zero boundary speed of unmanned plane during flying speed lower than aircraft stall, wing 3 tilt angle is not more than 45 °, and aspect controls according to vertical takeoff and landing state model.After aircraft flight speed exceedes stall zero boundary speed, wing 3 verts 90 ° and lock (large-scale rudder face 2 locks equally), and wing 3 outer rim aileron 1 is started working, and enters flatly to fly state master mode.

The flat state that flies is flown and is controlled (see Fig. 6):

Control of sideward roll: rely on aileron 1 rudder face of both sides wing 3 end to control aircraft roll;

Pitch control subsystem: rely on tailplane 4 to control aircraft pitch;

Heading control: rely on vertical tail 8 rudder face to control vector.

Claims

1. a high-mobility, multipurpose, wheeled vehicle VUAV, it is characterized in that: this unmanned plane comprises aileron (1), large-scale rudder face (2), wing (3), tailplane (4), rotor protective case (5), fuselage (6), rotor (7) and vertical tail (8), described fuselage (6) is flats, the wing (3) that can vert is installed in its two sides, in wing (3) inner side, the rotor (7) synchronously verted is installed, outside comprises aileron (1), described rotor (7) is made up of upper rotor (71) and lower rotor (72), and there is rotor protective case (5), at the afterbody of described rotor (7), large-scale rudder face (2) is installed, at the afterbody of described fuselage (6), tailplane (4) and vertical tail (8) are installed.

2. high-mobility, multipurpose, wheeled vehicle VUAV according to claim 1, is characterized in that: this unmanned plane, when vertical takeoff and landing, relies on the different lift control aircraft roll that both sides rotor (7) produce; Both sides wing (3) are relied on to vert and rotor (7) below large-scale rudder face (2) Hybrid mode aircraft pitch; The differential start of large-scale rudder face (2) of two rotor (7) belows is relied on to control vector.

3. high-mobility, multipurpose, wheeled vehicle VUAV according to claim 1, is characterized in that: this unmanned plane flat fly state time, rely on aileron (1) rudder face of both sides wing (3) end to control aircraft roll; Tailplane (4) is relied on to control aircraft pitch; Vertical tail (8) rudder face is relied on to control vector.