Differential geometry nonlinear control method for aircraft anti-interference attitude tracking

A nonlinear control and differential geometry technology, applied in the direction of adaptive control, general control system, control/regulation system, etc., can solve problems such as difficult engineering implementation, complex structure, large amount of calculation, etc.

Inactive Publication Date: 2015-05-27
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

[0005] In order to overcome the deficiencies of the existing technology and avoid the problems that the structure of the traditional nonlinear control method is too complicated, it is not easy to implement in engineering, and the amount of calculation is large. Considering the existence of uncertain factors and various disturbances, the present invention proposes an aerospace A differential geometric nonlinear control method for anti-jamming attitude tracking of the controller, and a simple and anti-jamming nonlinear control law

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  • Differential geometry nonlinear control method for aircraft anti-interference attitude tracking
  • Differential geometry nonlinear control method for aircraft anti-interference attitude tracking
  • Differential geometry nonlinear control method for aircraft anti-interference attitude tracking

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Embodiment Construction

[0091] The implementation of the method of the present invention will be described in detail below in conjunction with the accompanying drawings.

[0092] A nonlinear control method for spacecraft anti-jamming attitude tracking, the specific steps comprising:

[0093] Step 1. Establish the close-range relative attitude dynamic model of two spacecraft

[0094] Select the center of mass of the target spacecraft as the orbital coordinate system Oxyz(s o ) origin O, the z-axis points to the center of the earth, the x-axis is perpendicular to the z-axis along the velocity direction in the orbital plane, and the y-axis satisfies the right-hand rule, then the schematic diagram of the relative motion of the two spacecraft is as follows figure 1 shown. Define the spacecraft body system OX B Y B Z B The origin of is the spacecraft center of mass O, OX B ,OY B ,OZ B The three axes are fixedly connected to the spacecraft body, and are respectively consistent with the main axes of ...

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Abstract

The invention discloses a differential geometry nonlinear control method for aircraft anti-interference attitude tracking. The method comprises the following steps: performing linear transformation on a nonlinear attitude dynamic model to obtain the form of a linear space; successively performing controller design on a linearized attitude tracking system by utilizing an LQR (Linear Quadratic Regulator) to obtain a nonlinear control law. The aircraft attitude tracking controller based on a differential geometry theory and an LQR control method can comprehensively consider the control error and the fuel consumption, adopts a simpler linear control theory, has a simple and convenient control structure, reduces the calculated amount and saves satellite resources; therefore, the differential geometry nonlinear control method is particularly suitable for space attitude tracking tasks needing real-time solution and having limited computing power.

Description

technical field [0001] The invention relates to a differential geometric nonlinear control method for spacecraft anti-jamming attitude tracking, which belongs to the field of spacecraft control. Background technique [0002] The structure and function of spacecraft are becoming more and more complex, and the development of aerospace technology makes new space tasks such as on-orbit operation possible, which puts forward higher requirements for the control technology of spacecraft. On the one hand, the control system should ensure the robust stability and dynamic performance of the entire system under various uncertain factors and external disturbances, and maintain high-precision control effects; on the other hand, due to the limitations of the on-board computer, it should also It is possible to simplify the complexity of the controller structure and use a relatively simple control algorithm. However, due to the strong nonlinearity and coupling of the spacecraft attitude dy...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B13/04
Inventor 罗建军孙浩朱战霞袁建平殷泽阳
Owner NORTHWESTERN POLYTECHNICAL UNIV
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