A control method and flight control system for rolling torque under a large angle of attack

Abstract

The invention proposes a control method and a flight control system for the rolling moment at a large attack angle. The control method uses the duty ratio of the jet as the control amount to control the rolling moment. Under the condition that the supply air pressure is kept constant, the duty ratio of the jet is controlled by a high-frequency solenoid valve, which makes the speed of the jet flow Keep constant, and the speed is zero during the air-holding time period, thereby realizing the control effect of no rudder effect dead zone. The invention connects the jet exciter with the flight control system, replaces the traditional rudder surface, overcomes the failure of the traditional rudder surface in the case of flow separation at a large attack angle, and further widens the flight envelope of the aircraft.

Description

technical field [0001] The invention discloses a rolling moment control method and a flight control system at a large attack angle, belonging to the field of aircraft control. Background technique [0002] At high angles of attack, traditional roll control surfaces (ailerons) fail due to severe boundary layer separation, and using them to control post-stall maneuvers at high angles of attack will become very inefficient and Danger. It is necessary to design an effective and linear control method to control the rolling moment of the aircraft at high angles of attack. [0003] The surface of a swept-wing aircraft will wind two or more vortex systems from the leading edge. Since these vortex systems become an important part of the lift force at high angles of attack, if these vortex systems can be controlled, the aircraft's flight can be effectively controlled. Stress situation. [0004] Jet flow along the leading edge is a way to control the vortex system at a high angle of...

AI Technical Summary

Problems solved by technology

[0004] Jet flow along the leading edge is a way to control the vortex system at a high angle of attack. Its main principle is to inject momentum into the vortex core, thereby delaying the breakup of the vortex at a high angle of attack. However, if this control method is used to control The rolling moment of the aircraft has a disadvantage, that is, when the velocity of the jet along the leading edge does not reach a certain threshold, the control is ineffective, that is to say, there is a "dead zone" in the control

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