CN105366033A

CN105366033A - Wing dissymmetric backswept rolling control method for gliding aircrafts

Info

Publication number: CN105366033A
Application number: CN201510758951.XA
Authority: CN
Inventors: 黄勇; 李永红; 钟世东; 马晓永; 李巍; 刘大伟; 苏继川
Original assignee: High Speed Aerodynamics Research Institute of China Aerodynamics Research and Development Center
Current assignee: High Speed Aerodynamics Research Institute of China Aerodynamics Research and Development Center
Priority date: 2015-11-10
Filing date: 2015-11-10
Publication date: 2016-03-02

Abstract

The invention provides a wing dissymmetric backswept rolling control method for gliding aircrafts. According to the rolling control method, by utilizing the wings with relatively large aspect ratio of a gliding aircraft, rolling control is realized through the normal force difference generated during dissymmetric backswept of wings with relatively large aspect ratio. The wing dissymmetric backswept rolling control method for gliding aircrafts possesses substantially-increased rolling control efficiency compared with a conventional tail vane control method, and can be popularized and applied to rolling control on aircrafts with a similar layout.

Description

A kind of wing asymmetrical-swept roll unloads method of the class aircraft that glides

Technical field

The invention belongs to aerodynamic scope, be specifically related to a kind of wing asymmetrical-swept roll unloads method of the class aircraft that glides.

Background technology

The roll unloads of glide class aircraft generally adopts installs at aircraft afterbody the method realization controlling rudder face, but be subject to the restriction of rudder face size, the available arm of force of rolling moment is shorter, control for realizing larger rolling moment, the rudder face degree of bias or rudder face area can only be increased, and the increase of the rudder face degree of bias or rudder face area is subject to the restriction of Flight Vehicle Structure, the aerodynamic characteristic of rudder face own, and the increase of the rudder face degree of bias or rudder face area often makes control surface hinge moment increase, and then improve the requirement of strength of acting device.

Summary of the invention

The technical problem to be solved in the present invention is to provide a kind of wing asymmetrical-swept roll unloads method of the class aircraft that glides.

The wing asymmetrical-swept roll unloads method of glide class aircraft of the present invention, comprises the following steps:

A. the left and right wing of glide class aircraft has change sweepback angle control setup respectively;

B., during average flight state, the sweepback angle α A of port wing is identical with the sweepback angle α B of starboard wing;

When c. carrying out roll unloads, the sweepback angle α A of the sweepback angle α B > port wing of starboard wing, to obtain negative rolling moment, the sweepback angle α A of the sweepback angle α B < port wing of starboard wing, to obtain positive rolling moment.

The wing aspect ratio of glide class aircraft is more than or equal to 5, | α A|≤10 °, sweepback angle of the sweepback angle α B-port wing of starboard wing.

The wing asymmetrical-swept roll unloads method of glide class aircraft of the present invention utilizes glide class aircraft, as guided missile, unmanned plane etc. have comparatively high aspect ratio wing, the longer roll unloads arm of force can be obtained and influential feature is not had substantially to fore-and-aft stability, by the port wing of glide class aircraft, starboard wing are carried out low-angle asymmetrical-swept and obtain port wing, starboard wing normal force residual quantity, and then produce larger roll unloads moment.

The wing asymmetrical-swept roll unloads method of glide class aircraft of the present invention can produce larger roll unloads moment and higher control efficiency relative to traditional tail vane control method, solve a difficult problem for traditional tail vane control ability deficiency, to the aeroperformance improving aircraft, there is higher engineering practical value, the roll unloads of the aircraft of similar layout can be applied to.

Accompanying drawing explanation

Fig. 1 is glide class aircraft port wing, starboard wing symmetrical sweepback state appearance schematic diagram;

Fig. 2 is glide class aircraft port wing, starboard wing asymmetrical-swept state appearance schematic diagram;

Fig. 3 is glide class aircraft port wing, starboard wing asymmetrical-swept state appearance schematic diagram;

Fig. 4 is glide class aircraft port wing, starboard wing asymmetrical-swept state appearance schematic diagram;

In figure, 1. port wing 2. starboard wing 3. tail vane.

Detailed description of the invention

The inventive method is described in detail below in conjunction with drawings and Examples.

Embodiment 1

A kind of glide class aircraft, its port wing, starboard wing have change sweepback angle control setup respectively, and wing aspect ratio is 5.When average flight state, as shown in Figure 1, the sweepback angle α A of port wing is identical with the sweepback angle α B of starboard wing, is 26 °.When carrying out roll unloads, the sweepback angle α A of port wing is different from the sweepback angle α B of starboard wing, when needing to realize negative rolling moment, is slightly increased by starboard wing sweepback angle α B, as shown in Figure 2, starboard wing sweepback angle is increased to 27 ° from 26 °, and port wing sweepback angle α A keeps 26 °, | α B-α A|=1 °, now, under identical inlet flow conditions, the normal force of port wing will be greater than starboard wing, can realize the roll unloads of full bullet; When needing to realize positive rolling moment, port wing sweepback angle is increased slightly.

Research proves, the wing asymmetrical-swept roll unloads method of glide class aircraft of the present invention deflects control method relative to the tail vane of tradition glide class aircraft, roll unloads efficiency significantly increases, within the scope of low incidence (angle of attack is less than 12 °), during Mach number 0.6, the control efficiency of asymmetrical-swept is 4 ~ 8 times of tail vane control efficiency substantially, and namely the asymmetrical-swept angle of 1 ° can realize the rolling moment that 4 tail vanes 4 ° ~ 8 ° of rudder face degrees of bias produce.

Embodiment 2

A kind of glide class aircraft, its left and right wing has change sweepback angle control setup respectively, and wing aspect ratio is 6.When average flight state, as shown in Figure 1, the sweepback angle α A of port wing is identical with the sweepback angle α B of starboard wing, is 26 °.When carrying out roll unloads, the sweepback angle α A of port wing is different from the sweepback angle α B of starboard wing, when needing to realize negative rolling moment, is increased by starboard wing sweepback angle α B, as shown in Figure 3, starboard wing sweepback angle is increased to 31 ° from 26 °, and port wing sweepback angle α A keeps 26 °, | α B-α A|=5 °, now, under identical inlet flow conditions, the normal force of port wing will be greater than starboard wing, can realize the roll unloads of full bullet; When needing to realize positive rolling moment, increased at port wing sweepback angle, starboard wing sweepback angle remains unchanged.

Embodiment 3

A kind of glide class aircraft, its left and right wing has change sweepback angle control setup respectively, and wing aspect ratio is 7.When average flight state, as shown in Figure 1, the sweepback angle α A of port wing is identical with the sweepback angle α B of starboard wing, is 26 °.When carrying out roll unloads, the sweepback angle α A of port wing is different from the sweepback angle α B of starboard wing, when needing to realize negative rolling moment, is increased by starboard wing sweepback angle α B, as shown in Figure 4, starboard wing sweepback angle is increased to 36 ° from 26 °, and port wing sweepback angle α A keeps 26 °, | α B-α A|=10 °, now, under identical inlet flow conditions, the normal force of port wing will be greater than starboard wing, can realize the roll unloads of full bullet; When needing to realize positive rolling moment, increased at port wing sweepback angle, starboard wing sweepback angle remains unchanged.

Claims

1. a wing asymmetrical-swept roll unloads method for class of gliding aircraft, is characterized in that, comprise the following steps:

A. be respectively arranged with become sweepback angle control setup at the port wing of glide class aircraft, starboard wing;

When c. carrying out roll unloads, the sweepback angle α A of the sweepback angle α B > port wing of starboard wing, to obtain negative rolling moment; The sweepback angle α A of the sweepback angle α B < port wing of starboard wing, to obtain positive rolling moment.

2. the wing asymmetrical-swept roll unloads method of glide class aircraft according to claim 1, is characterized in that: the wing aspect ratio of glide class aircraft is more than or equal to 5.

3. the wing asymmetrical-swept roll unloads method of glide class aircraft according to claim 1, is characterized in that: | α A|≤10 °, sweepback angle of the sweepback angle α B α B-port wing of starboard wing.