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

A technology of parameter uncertainty, control system, applied in general control system, control/regulation system, attitude control and other directions, can solve the problem of affecting the accuracy of the pilot's operation, affecting the flight quality and flight mission of the aircraft, the amplitude of the same, etc. question

Inactive Publication Date: 2013-02-06
BEIHANG UNIV
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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...

Method used

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

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Experimental program
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Embodiment approach （ 1

[0126] Step 1: Analysis and construction of aircraft tilt angle model

[0127] The closed-loop control system adopts a negative feedback control structure, and the output is the tilt angle of the aircraft. Due to the phenomenon of input saturation in the aircraft tilt angle control system, there is a nonlinear part of the input saturation in the aircraft tilt angle control system. The involved aircraft tilt angle control system just comprises linear controller, saturation and aircraft model three parts, and the schematic diagram of aircraft tilt angle control system of the present invention is as Figure 1.2 shown.

[0128] The transfer function of the simplified model of aircraft tilt angle is as follows:

[0129] G ( s ) = k s ( s + e 0 ...

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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...

Claims

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Application Information

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IPC IPC(8): G05D1/08G05B13/04
Inventor 刘金琨祝国强王明钊
Owner BEIHANG UNIV
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