Control surface fault adaptive fault-tolerant control method for flying-wing layout aircraft

Abstract

The invention discloses a control surface fault adaptive fault-tolerant control method for a flying-wing layout aircraft, and the method comprises the steps: designing a control surface fault parameter adaptive adjustment law so as to compensate for impact on the control performance from a fault; approaching to unknown items for system uncertainty caused by the pneumatic parameter changes caused by the fault through a neural network, thereby compensating for the impact on the control performance from the pneumatic parameter changes; combining the characteristics of the flying-wing layout aircraft with the fault condition to design a dynamic control distribution strategy; carrying out the processing of an expected control signal through a command filer, and obtaining a corresponding control command with the limited amplitude, rate and bandwidth. According to the invention, the method gives consideration to the combined faults of partial failure and dead clamping of a plurality of control surfaces and the changes, caused by the fault of the pneumatic parameters of the aircraft. When the control surface of the flying-wing layout aircraft with the limited input has a fault, the method can enable the aircraft to remain stable, and to achieve the progressive tracking of a given reference signal. Moreover, the aircraft has the predetermined dynamic performances.

Description

technical field [0001] The invention belongs to the technical field of fault-tolerant control of aircraft, and in particular relates to a fault-adaptive fault-tolerant control method of a control surface of an aircraft with flying wing layout. Background technique [0002] Due to its light weight, good stealth effect, and flexible maneuverability, the tailless flying wing aircraft has been widely used in unmanned fighter jets, and is even regarded by the industry as the most promising to meet the growing noise, emission and other environmental problems. New Civil Aircraft Concepts for Regulatory Requirements and Air Traffic Flow Demands. But it is the tailless layout that brings new challenges to the control of this type of aircraft: there is no horizontal tail, which reduces the longitudinal stability, the longitudinal control arm is short, the control efficiency is low, and the rudder deflection is easy to reach saturation; without the vertical tail, Reduced lateral and l...

AI Technical Summary

Problems solved by technology

However, the article does not consider the saturation characteristics of the actuator, and there are many affected aerodynamic parameters that need to be considered, and the design is more complicated

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