Method for suppressing limit cycle of inclination angle control system of aircraft with parameter uncertainty

Abstract

The invention discloses a method for suppressing the limit cycle of an inclination angle control system of an aircraft with parameter uncertainty. The method comprises the following main steps of: step 1, analyzing and establishing a model of the inclination angle system of the aircraft; step 2, analyzing scanning functions of a non-linear section and an oscillation phenomenon of the limit cycle; step 3, designing a controller of the inclination angle system of the aircraft with the parameter uncertainty; step 4, inspecting the performance of the controller; and step 5, ending the design. With the adoption of the method, not only is the oscillation of the limit cycle of the aircraft suppressed, but also the parameter uncertainty is overcome, and furthermore, the rapid and precise tracking to the inclination angle of the aircraft is realized. The method has better practical value and good application prospect in the technical field of automatic control.

Description

(1) Technical field [0001] The invention relates to a method for suppressing limit cycles of an aircraft inclination angle control system with parameter uncertainty, which is aimed at a non-linear aircraft inclination angle control system, and is used to suppress the inclination angle limit cycle oscillation caused by the nonlinear part of the aircraft inclination angle control system The phenomenon overcomes parameter uncertainty and belongs to the field of automatic control technology. (2) Background technology [0002] The aircraft is a complex nonlinear model, and it is also necessary to control saturation, hysteresis, friction and other phenomena in the flight control, so it is difficult to directly apply the classical linear control theory to the aircraft. Moreover, due to the existence of nonlinear links, a continuous oscillation with constant amplitude may occur—limit cycle oscillation. The occurrence of limit cycle oscillation on the aircraft not only affects the a...

AI Technical Summary

Problems solved by technology

[0002] The aircraft is a complex nonlinear model, and it is also necessary to control saturation, hysteresis, friction and other phenomena in the flight control, so it is difficult to directly apply the classical linear control theory to the aircraft

Moreover, due to the existence of nonlinear links, there may be a continuous oscillation with constant amplitude - limit cycle oscillation

The occurrence of limit cycle oscillation on the aircraft not only affects the accuracy of the pilot's operation, but also affects the flight quality and mission of the aircraft.

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