Control method of rolling moment under large attack angle and flight control system

Abstract

The invention provides a control method of rolling torque under a large attack angle and a flight control system. According to the control method, the duty ratio of a jet flow serves as a control quantity to control the rolling moment, under the condition that a constant supply air pressure is guaranteed, the duty ratio of the jet flow is controlled through a high-frequency electromagnetic valve,the speed of the jet flow in an air outlet time period is kept constant, and the speed of the jet flow in an air closing time period is zero, therefore the control effect of a dead zone without a rudder effect is achieved. A jet flow exciter is connected to the flight control system to replace a traditional control surface, the defect that the traditional control surface loses efficacy under the condition of large attack angle flow separation is overcome, and the flight envelope of an aircraft is further widened.

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...

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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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