Interplane air grid system based large angle-of-attack flying airflow separation control method

Abstract

The invention discloses an interplane air grid system based large angle-of-attack flying airflow separation control method, and belongs to the technical field of aircraft design. The method is suitable for the large angle-of-attack flight of an aircraft and the airflow-separated aircraft control, a skin is started by a skin driving device of the flying control system, and air grid separators in air grid systems deflect to generate lateral control force; and the air grid systems in different positions of the aircraft can be individually controlled to reinforce the spatial attitude change capability of the large angle-of-attack flight. The method can improve the air streaming characteristic according to an assigned rule under an aircraft large angle-of-attack flying condition, and is suitable for a plurality of angle-of-attack states; and the method can provide new direct lateral control force under large angle-of-attack flying and reduced even failed rudder and vertical tail conditions, and can be used for changing the attitude and state in the large angle-of-attack flight to improve the mobility and agility of the aircraft.

Description

technical field [0001] The invention belongs to the technical field of aircraft design, and relates to a method for controlling the separation of airflow at high angles of attack. A deflectable air grid partition is arranged inside the wing to affect the surface of the wing and the flow of the internal airflow, so as to delay stall and provide lateral power purpose. Background technique [0002] High angle of attack flight maneuverability is one of the basic requirements for the design of a new generation of aircraft. The primary problem facing maneuvering at high angles of attack is the sudden drop in lift-to-drag ratio caused by airflow separation, that is, the "stall" problem. How to delay or control airflow separation has always been a research hotspot in the field of aerodynamics. The methods and technologies adopted at present mainly include "leading edge flap", "front canard", "wing side strip", setting "pelvic fin", "asymmetrical vortex single hole micro blowing", ...

AI Technical Summary

Problems solved by technology

[0006] The present invention aims at the problem that the airflow diversion affects the aerodynamic characteristics of the traditional wing when flying at a high angle of attack, and proposes a method for controlling the air flow at a high angle of attack based on the air grid system between the wings, so as to improve the air flow characteristics of the aircraft flying at a high angle of attack. And provide direct control of lateral force for aircraft maneuvering at high angles of attack

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