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A control system and control method for controlling the speed of an aircraft

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

Active Publication Date: 2020-05-15
BEIJING INSTITUTE OF TECHNOLOGYGY +1
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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 speed of an aircraft
  • A control system and control method for controlling the speed of an aircraft
  • A control system and control method for controlling the speed of an aircraft

Examples

Experimental program
Comparison scheme
Effect test

Embodiment approach

[0112] 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 .

[0113] 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.

[0114] 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 .

[0115] Wherein, the absolute value obtaining sub-module 31 is used to perform absolute value processin...

Embodiment

[0177] 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.

[0178] In the simulink simulation example, adopt the system of the present invention, set k e =0.5,k ec = 1,k uP =0.8,k uI =0.3,k uD =0.1, wherein, let the input speed be 20m / s, and the simulation time be 30 seconds, add a wind gust with a wind speed of 10m / s and a duration of 2s at t=15s as a disturbance, and use two positive and negative simulations to represent Tailwind and headwind, where the test results with tailwind and headwind as disturbance are as follows Figure 9 and Figure 10 shown.

Embodiment 1

[0190] The response time of embodiment 1 and comparative example 2 is 6s, and the response time of comparative example 1 is 10s;

[0191] (4) compare the perturbed situation of embodiment 1 and comparative examples 1 to 2:

[0192] The maximum overshoot of the embodiment relative to the disturbance signal is 22%, and the time to return to the steady state is 7s; the maximum overshoot of the comparative example 1 relative to the disturbance signal is 37%, and the time to return to the steady state is 10s; Comparative example 2 The maximum overshoot relative to the disturbance signal is 24%, and the time to return to the steady state is 8s.

[0193] 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 parameter...

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Abstract

The invention discloses a control system used for controlling the aircraft rate and a control method thereof. The system comprises a conventional PID controller (1), a fuzzy PID controller (2) and a weight allocation module (3). The weight allocation module (3) performs weight allocation on the conventional PID controller (1) and the fuzzy PID controller (2) according to the actual flight environment and performs weight allocation by using a fuzzy control method. The method is performed by using the system. The conventional PID controller (1) and the fuzzy PID controller (2) are effectively combined so that the flight stability can be guaranteed in normal flight and the adaptability can also be enhanced in case of 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 speed 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-adaptation is po...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/08G05D1/10
CPCG05D1/0825G05D1/101
Inventor 林德福侯淼阎康王伟王江王辉林时尧
Owner BEIJING INSTITUTE OF TECHNOLOGYGY