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A control system and control method for controlling the attitude angle of an aircraft

A control system and controller technology, applied in the field of aircraft, can solve problems such as poor self-adaptation and poor flight stability of aircraft

Active Publication Date: 2020-04-07
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The control method currently applied is through conventional PID control or fuzzy PID control. Among them, conventional PID control has certain limitations. When encountering external disturbances such as airflow, conventional PID control is difficult to automatically adjust to adapt to changes in the external environment, namely The self-adaptation is poor, and the fuzzy PID control can perform self-regulation when there is an external emergency, and the adaptive ability is strong. However, when there is no emergency (during normal flight), the fuzzy PID control is used to control the flight stability of the aircraft. Poor sex

Method used

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  • A control system and control method for controlling the attitude angle of an aircraft
  • A control system and control method for controlling the attitude angle of an aircraft
  • A control system and control method for controlling the attitude angle of an aircraft

Examples

Experimental program
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Embodiment approach

[0109] According to a preferred embodiment of the present invention, the PID parameter incremental actual value conversion sub-module 224 performs the following processing: Δk P ’=ΔK P '*k uP ; Δk I ’=ΔK I '*k uI ; Δk D ’=ΔK D '*k uD .

[0110] Among them, k uP Expressed in relation to ΔK P ’ Carry out language value to actual value Δk P ’ The deblurring factor used in conversion, k uI Expressed in relation to ΔK I ’ Carry out language value to actual value Δk I ’ The deblurring factor used in conversion, k uD Expressed in relation to ΔK D ’ Carry out language value to actual value Δk D ’ The deblurring factor to use when converting.

[0111] According to a preferred embodiment of the present invention, such as Figure 5 As shown, the weight distribution module 3 includes an absolute value calculation sub-module 31 and a weight distribution sub-module 32 .

[0112] Wherein, the absolute value obtaining sub-module 31 is used to perform absolute value processin...

Embodiment

[0174] The present invention is further described by simulink simulation experiments below. However, these examples are only exemplary and do not constitute any limitation to the protection scope of the present invention.

[0175] In the simulink simulation example, adopt the system of the present invention, set k e = 2,k ec = 1,k uP =0.55,k uI =0.2,k uD =0.1, wherein, make the pitch angle of input be 10 °, simulation time is 30 seconds, add the impulse signal that size is 10 ° as disturbance at t=15s place, the system of the present invention is tested, the result is as follows Figure 9 shown.

Embodiment 1

[0187] The response time of embodiment 1 and comparative example 2 is 6s, and the response time of comparative example 1 is 10s;

[0188] (4) compare the perturbed situation of embodiment 1 and comparative examples 1 to 2:

[0189] The maximum overshoot of the embodiment relative to the disturbance signal is 18%, and the time to return to the steady state is 3s; the maximum overshoot of the comparative example 1 relative to the disturbance signal is 27.5%, and the time to return to the steady state is 5s; Comparative example 2 The maximum overshoot relative to the disturbance signal is 16.5%, and the time to return to the steady state is 3s.

[0190] As can be seen from the above, (a) relative to the conventional PID control of the system of the present invention, the overshoot is reduced to 17% by 27.5%, and the time to reach stability is reduced by 40%; (b) relative to the fuzzy PID control, the steady state can reach no static Poor, the adjustment range of fuzzy PID parame...

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Abstract

The present invention discloses a control system of aircraft attitude angle control and a control method of aircraft attitude angle control. The system comprises: a traditional PID controller (1), a fuzzy PID controller (2) and a weight distribution module (3). The weight distribution module (3) performs weight distribution for the traditional PID controller (1) and the fuzzy PID controller (2) according to actual flight environment, and a fuzzy control method is employed to perform weight distribution. The control method is performed by employing the system to perform effective combination of the traditional PID controller (1) and the fuzzy PID controller (2) so as to ensure the flight stability when flight in normal state and improve the adaptability when emergency.

Description

technical field [0001] The present invention relates to the field of aircraft, in particular to the control of the aircraft, in particular to a control system for controlling the attitude angle of the aircraft and a control method thereof. Background technique [0002] With the rapid development of science and technology, the control technology of aircraft is also constantly improving, and people's requirements for flight effects are also constantly improving. The problem to be solved in aircraft control is how to improve its flight effect, such as static and dynamic characteristics, adaptive ability, robustness and so on. [0003] The control method currently applied is through conventional PID control or fuzzy PID control. Among them, conventional PID control has certain limitations. When encountering external disturbances such as airflow, conventional PID control is difficult to automatically adjust to adapt to changes in the external environment, namely The self-adaptat...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/08
CPCG05D1/0816
Inventor 阎康林德福宋韬王伟胡宽荣王辉王江李晨迪
Owner BEIJING INSTITUTE OF TECHNOLOGYGY