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Track dip angle inversion controlling method of aircraft based on control force limitation situation

A technology of inversion control and aircraft, applied in the direction of attitude control, etc., can solve problems such as inaccurate calculation and affecting system performance

Inactive Publication Date: 2014-05-21
BEIHANG UNIV
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  • Application Information

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Problems solved by technology

It seriously affects the performance of the system and leads to inaccurate calculations

Method used

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  • Track dip angle inversion controlling method of aircraft based on control force limitation situation
  • Track dip angle inversion controlling method of aircraft based on control force limitation situation
  • Track dip angle inversion controlling method of aircraft based on control force limitation situation

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Embodiment approach （ 1

[0116] See Figure 4 , the present invention is based on a method of inversion control of aircraft track inclination under the condition of limited control force. The specific steps of the method are as follows:

[0117] Step 1: Aircraft Longitudinal Model Construction and State Transformation

[0118] The closed-loop control system adopts a negative feedback control structure, the output is the inclination angle of the aircraft track, and the input is the deflection angle of the rudder surface. The designed closed-loop control system is mainly composed of three parts: the controller link, the auxiliary analysis system link and the system model. The structure layout is shown in figure 1 shown.

[0119] Aircraft Longitudinal Model γ · = L ‾ o + ...

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Abstract

The invention relates to a track dip angle inversion controlling method of an aircraft based on a control force limitation situation. The track dip angle inversion controlling method comprises the following four steps of: step 1, constructing a longitudinal model of an aircraft and converting a state of the aircraft; step 2, carrying out an inversion control design based on saturated control input; step 3, verifying tracking performance and regulating parameters; and step 4, finishing the design. The invention aims at a longitudinal plane dynamic model of the aircraft, utilizes an input saturation error dynamic amplification method by defining an auxiliary analysis system to realize an inversion control method based on the saturated control input, and is applied to the control of a track dip angle of the aircraft. The invention has better practical value and a wide application prospect in an aerospace automatic control technical field.

Description

(1) Technical field [0001] The invention relates to an aircraft track inversion control method based on limited control force. It aims at the dynamic model of the longitudinal plane of the aircraft. By defining an auxiliary analysis system and adopting a method of dynamically amplifying input saturation errors, a method based on control is realized. The input saturation inversion control method is used for the control of aircraft track inclination, and belongs to the technical field of automatic control. (2) Background technology [0002] The track inclination angle of the aircraft is the angle between the flight speed direction and the horizontal direction, and is an important motion parameter of the aircraft. By stably and precisely controlling the inclination angle of the track, not only can the aircraft follow the predetermined trajectory, but also the flying height of the aircraft can be guaranteed. The longitudinal model of the aircraft is a nonlinear strongly coupled...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/08
Inventor 刘金琨郭一
Owner BEIHANG UNIV
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