CN102673780A

CN102673780A - Double-configuration aircraft

Info

Publication number: CN102673780A
Application number: CN201210186003XA
Authority: CN
Inventors: 李建波; 赵洪
Original assignee: Individual
Current assignee: Individual
Priority date: 2012-06-07
Filing date: 2012-06-07
Publication date: 2012-09-19

Abstract

The invention discloses a double-configuration aircraft. When high-speed configuration is used, a plane head is connected with the front end of the plane body, wings are installed on the plane body and vertical to the plane body, an auxiliary wing is correspondingly installed on two sides of the wings respectively, a power fuel system and a control system are loaded inside the plane body, culverts are in shapes of annular cylinders, the culverts and the tail end of the plane body are fixed through a support, and the centers of the culverts correspond to an axis of the plane body, the cross section of flow deflectors are wing-shaped, the flow deflectors are radially fixed on the back sides of propellers inside the culverts, the propellers are installed in a center formed by the flow deflectors, operation rudder faces are symmetrically distributed on the tail portions of the culverts, and a lifting support is located at the periphery of the lateral faces of the culverts. When low-speed configuration is used, the culverts are directly connected with the plane head through the support, and no plane body, wing and auxiliary wing is installed. The double-configuration aircraft adopts the double-configuration design, components can be selectively assembled to be a high-speed configuration aircraft or a low-speed configuration aircraft according to task requirements, the aerodynamic design coupling problem of the aircraft on giving consideration to different flight states is solved, and comprehensive task adaptation capability of the aircraft is obviously improved.

Description

Two configuration aircraft

Technical field

The present invention relates to a kind of aircraft, design a kind of pair of configuration aircraft especially.

Background technology

In order to design a kind of unmanned vehicle; Make it can have the high-speed flight performance of fixed-wing and VTOL, the hover performance of helicopter concurrently; The mankind have proposed a lot of aircraft schemes, comprising: the jet plane of tiltrotor, compound helicopter, lift change type aircraft, equipment vectored thrust driving engine etc.Physical resource can be referring to the paper of American scholar Rob Ransone: vertical short field aircraft outline and their contribution (An overview of VSTOL Aircraft and their Contributions, paper number: AIAA-2002-5976).

Tiltrotor can be carried out VTOL with rotor power, flies state flat at a high speed, the power that flies before rotor verts and provides, and rely on wing to produce lift.The rotary wing changing spacing mechanism of tiltrotor and driving device are very complicated, cost is big, very high to the requirement of material; And the mechanical characteristic that verts during transition flight of aircraft is complicated; Brought big difficulty for the flight and the control of aircraft, the development of tiltrotor is under some influence.

Lift change type unmanned plane relies on the pulling force or the thrust of screw propeller to carry out VTOL, handles whole machine body then and verts to get into and flatly at a high speed fly state, utilizes wing that lift is provided.This kind aircraft generally adopts normal arrangement, and Flight Vehicle Structure is simpler relatively, and the flat high speed characteristics that flies of this kind aircraft is better; Be easy to control; But the hover performance of this type aircraft is not very desirable usually, is difficult to hover for a long time, and recovery is brought certain difficulty.

But the above several kinds of vertical take-off and landing unmanned aerial vehicle is lower to the landing conditional request, can carry out flying before the high speed, but the low-speed performance of aircraft is relatively poor, is unfavorable for complicated battlefield surroundings and the requirement of task variety of aircraft reply.

Summary of the invention

Goal of the invention: the present invention is directed to the deficiency of prior art, propose a kind of two configuration aircraft of taking into account high speed, low speed different flight state.

Technical scheme: a kind of pair of configuration aircraft of the present invention comprises head, fuselage, aileron, wing, duct, flow deflector, support, screw propeller, operation rudder face, alighting gear, power fuel oil system and control system; Can aircraft component be carried out selectivity be assembled into high speed configuration and low speed configuration according to mission requirements:

During the high speed configuration, said head links to each other with front fuselage, and wing is installed on the fuselage and is vertical with fuselage; Aileron of each corresponding installation of wing both sides; Power fuel oil system and control system are loaded in fuselage interior, and said duct is the ring-type cylinder, can strengthen the pneumatic efficiency of screw propeller; Fix through support and tail cone, and its center is relative with the fuselage axis; The flow deflector cross section is a wing, is fixed on the rear side of duct internal helicoid oar radially, is used for offsetting the reactive torque of screw propeller; Screw propeller be installed in that flow deflector forms in the heart; Be made up of 2～5 blades, in flight course, screw propeller rotating tee overregulate rotating speed changes propeller thrust; Several operation rudder faces are symmetrically arranged in the duct afterbody, in the duct wake flow, through the required operating torque of deflection generation aircraft of operation rudder face; Alighting gear is positioned at around the duct side.When high-speed flight, produce lift by wing, before providing, duct and screw propeller fly thrust, and primary control surface in the duct and the aileron on the wing are realized the attitude manipulation, can realize VTOL, hovering and flat at a high speed flying.

During the low speed configuration; Duct directly links to each other with fuselage through support; Head, wing and aileron need be installed, directly rely on duct and screw propeller to produce lift and thrust, the primary control surface of duct afterbody provides attitude and nonchannel flow operations such as operating torque is realized hovering, pitching, lift-over, driftage.

Further, wing is trapezoidal, and the high mounted wing structure can be disassembled into two parts with wing from wing root, convenient transportation.

Alighting gear comprises the bumper and the ring that lands, and the spring in the bumper can effectively reduce the land overload, and protection body and internal unit, bumper are connected on the ring that lands, and can prevent that aircraft from turning on one's side when landing.

Beneficial effect: 1, the present invention adopts two configured; Can the parts selectivity be assembled at a high speed or low speed configuration aircraft according to mission requirements; Solve aircraft and taken into account the pneumatic design coupling difficult problem of different flight state; Give full play to the not performance advantage of isomorphism type of aircraft, significantly improved the comprehensive task adaptive capacity of this kind aircraft; 2, adopt duct single screw engine installation, utilize flow deflector binding operation rudder face to realize screw propeller reactive torque balance and flight control integrated design, simplified steering unit, make structure compact more reliable; 3, this aircraft is that a kind of high-mobility, multipurpose, wheeled vehicle carries machine platform, carries various tasks equipment and can carry out multiple-tasks such as scouting, detection.

Description of drawings

The structural representation of Fig. 1 during for high speed configuration of the present invention;

The structural representation of Fig. 2 during for low speed configuration of the present invention.

The specific embodiment:

A kind of pair of configuration aircraft that present embodiment provides like Fig. 1, shown in 2, comprises head 1, fuselage 2, aileron 3, wing 4, duct 5, flow deflector 6, support 7, screw propeller 8, operation rudder face 9, alighting gear 10, power fuel oil system and control system; Can aircraft component be carried out selectivity be assembled into high speed configuration and low speed configuration according to mission requirements:

During the high speed configuration, said head 1 links to each other with fuselage 2 front ends, and wing 4 is installed on the fuselage 2 and is vertical with fuselage 2; Aileron 3 of each corresponding installation of wing 4 both sides; The power fuel oil system loading is in fuselage 2 inside, and said duct 5 is the ring-type cylinder, can strengthen the pneumatic efficiency of screw propeller 8; Terminal fixing through support 7 with fuselage 2, and its center is relative with fuselage 2 axis; Flow deflector 6 cross sections are wing; Be fixed on the rear side of duct 5 internal helicoid oars 8 radially; Be used for offsetting the reactive torque of screw propeller 8, screw propeller 8 be installed in that flow deflector 6 forms in the heart, constitute by 3 blades; In flight course, screw propeller 8 rotating tee overregulate rotating speeds change screw propeller 8 thrusts; 4 groups of boxlike operation rudder faces 9 are symmetrically arranged in duct 5 afterbodys, in duct 5 wake flows, through the required operating torque of deflection generation aircraft of operation rudder face 9; Alighting gear 10 is positioned at around duct 5 sides.When high-speed flight, produce lift by wing 4, duct 5 flies thrust before providing with screw propeller 8, and the primary control surface 9 in the duct 5 is handled with the aileron 3 realization attitudes on the wing 4, can realize VTOL, hovering and flat at a high speed flying.

During the low speed configuration; Duct 5 directly links to each other with fuselage 2 through support 7; Head 1, wing 4 and aileron 3 need be installed, directly rely on duct 5 and screw propeller 8 to produce lift and thrust, realize nonchannel flow operation; The primary control surface 9 of duct 5 afterbodys provides attitudes such as operating torque is realized hovering, pitching, lift-over, driftage, and mainly 9 fine settings come balance to the reactive torque that screw propeller 8 produces with primary control surface by flow deflector 6.

Wherein, wing 4 is trapezoidal, and the high mounted wing structure can be disassembled into two parts with wing 4 from wing root, convenient transportation.

Alighting gear 10 comprises the bumper and the ring that lands, and the spring in the bumper can effectively reduce the land overload, and protection body and internal unit, bumper are connected on the ring that lands, and can prevent that aircraft from turning on one's side when landing.

As stated, although represented and explained the present invention that with reference to specific preferred embodiment it shall not be construed as the restriction to the present invention self.Under the spirit and scope of the present invention prerequisite that does not break away from the accompanying claims definition, can make various variations in form with on the details to it.

Claims

1. a two configuration aircraft during low speed configuration, comprises fuselage, duct, flow deflector, support, screw propeller, operation rudder face, alighting gear, power fuel oil system and control system; Said duct links to each other with fuselage through support, and power fuel oil system and control system are loaded in fuselage interior, and said duct is the ring-type cylinder; Fix through support and tail cone, and its center is relative with the fuselage axis, said flow deflector cross section is a wing; Be fixed on the rear side of duct internal helicoid oar radially; Screw propeller be installed in that flow deflector forms in the heart, the operation rudder face is symmetrically arranged in the duct afterbody, alighting gear is positioned at around the duct side;

During the high speed configuration; On the basis of low speed configuration, increase head, aileron, wing, said head links to each other with front fuselage, and wing is installed on the fuselage and is vertical with fuselage; Aileron of each corresponding installation of wing both sides, said duct is fixed through support and tail cone.

2. according to claim 1 pair of configuration aircraft is characterized in that: said wing is trapezoidal, and the high mounted wing structure is disassembled into two parts from wing root.

3. according to claim 1 pair of configuration aircraft is characterized in that: said alighting gear comprises the bumper and the ring that lands, and bumper is connected on the ring that lands.