An Aircraft Attitude Control Method Based on Nonlinear Feedback and Differential Tracking

A non-linear feedback, attitude control technology, applied in attitude control, non-electric variable control, vehicle position/route/height control, etc., can solve the problems of difficult engineering implementation, difficult controller parameter tuning, etc., to facilitate engineering implementation , The effect of solving the difficulty of parameter tuning and reducing the number of parameters

Active Publication Date: 2020-04-03
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

[0005] In order to avoid the deficiencies of the prior art, the present invention proposes an aircraft attitude control method based on nonlinear feedback and differential tracking to solve the attitude control of aircraft similar to launch vehicles under the influence of gusts, parameter perturbations, and unknown disturbances Problems, to avoid the difficulty in the implementation of important parts of the controller, and the difficulty in setting too many controller parameters

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  • An Aircraft Attitude Control Method Based on Nonlinear Feedback and Differential Tracking
  • An Aircraft Attitude Control Method Based on Nonlinear Feedback and Differential Tracking
  • An Aircraft Attitude Control Method Based on Nonlinear Feedback and Differential Tracking

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specific Embodiment

[0058] refer to Figure 1-2 , using the method of the present invention to design an attitude controller for an anti-jamming launch vehicle to eliminate the deviation of the attitude angle, so that the rocket flies according to the program angle designed for realizing the predetermined orbit. In view of the characteristics of the axisymmetric launch vehicle, the present invention is specifically described by taking rocket pitch attitude control as an example, and the specific implementation steps are as follows:

[0059] Step 1. Establish the attitude motion model of the launch vehicle and obtain the nominal data:

[0060] In view of the symmetric characteristics of the launch vehicle, a motion model of the pitch channel of the controlled object rocket is established, which consists of three parts: rigid body motion, elastic motion and attitude measurement.

[0061] The equation of motion for a rigid body is:

[0062]

[0063] The elastic vibration equation is:

[0064] ...

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Abstract

The invention relates to an aircraft attitude control method based on nonlinear feedback and differential tracking. The nonlinear feedback based on a time-optimal control integrated function is used as an attitude controller, while a rapidity control index is raised by more than 3 times and a control precision index is raised by more than 50%, compared with the background technology, the difficulty of project implementation is greatly reduced, and 4 control parameters are still maintained. An integral chain differentiator is used to design an uncertainty compensator, while the anti-interference ability of the controller is maintained, only one control parameter is needed, but a compensator used by the background technology needs 7 parameters. The whole control scheme needs 5 parameters, the control parameters are reduced by more than 50% compared with the background technology, and the difficulty of parameter setting is greatly reduced. A firefly algorithm is used to carry out the optimization tuning of the controller parameters, the number of setting iterations is reduced by more than 10 times compared with background technology, which has high engineering applicability.

Description

technical field [0001] The invention belongs to an anti-jamming control method for aircraft attitude control, and relates to an aircraft attitude control method based on nonlinear feedback and differential tracking, in particular to the aircraft attitude control problem in the presence of internal and external disturbances and parameter perturbations. Background technique [0002] When the structure of an axisymmetric aircraft such as a launch vehicle becomes more and more complicated to complete the scheduled mission, it will be greatly affected by uncertain factors such as gusts, parameter perturbations, and unknown disturbances during the flight, which leads to the adoption of traditional proportions. The stability margin of the differential (Proportion-Differential, PD) launch vehicle attitude control system is reduced, and there is even a risk of instability. Therefore, it is necessary to design an aircraft attitude control method with strong anti-interference ability. ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/08
CPCG05D1/0808
Inventor 王佩张科吕梅柏徐有新王靖宇姜海旭邢超李伟
Owner NORTHWESTERN POLYTECHNICAL UNIV
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