Improved iterative algorithm-based adaptive sliding mode variable structure spacecraft attitude control method

An adaptive sliding mode and iterative algorithm technology, applied in attitude control, aerospace vehicles, aircraft, etc., can solve problems affecting system control performance, system buffeting, etc.

Active Publication Date: 2018-08-21
HARBIN ENG UNIV
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Problems solved by technology

However, the sliding mode method also has its own defects. Due to the need to shuttle the sliding mode surface back and fo

Method used

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  • Improved iterative algorithm-based adaptive sliding mode variable structure spacecraft attitude control method
  • Improved iterative algorithm-based adaptive sliding mode variable structure spacecraft attitude control method
  • Improved iterative algorithm-based adaptive sliding mode variable structure spacecraft attitude control method

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Embodiment Construction

[0101] The present invention will be further elaborated below with examples in conjunction with the accompanying drawings.

[0102] Step 1. According to the spacecraft attitude control requirements, the linear model of the spacecraft system in any direction is expressed as:

[0103]

[0104] In formula (1), x 1 is the attitude angle in this direction. is the angular velocity of the attitude angle in this direction. x 2 is the angular velocity of the attitude angle in this direction. A and B are the system parameters in the state space equation. is the moment of inertia of the spacecraft with parameter perturbation. d is the external disturbance of the system. u is the input of the controller to be designed.

[0105] Step 2. Design an adaptive sliding mode control law based on the hyperbolic tangent function according to the linear model of the spacecraft

[0106] The sliding mode function is designed as

[0107]

[0108] In formula (2), s(t) is the sliding mod...

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Abstract

The invention relates to an improved iterative algorithm-based adaptive sliding mode variable structure spacecraft attitude control method. The method comprises the steps that 1, by means of Euler angle coordinate transformation, dynamics modeling is conducted on a general rigid spacecraft; 2, in consideration of outside disturbance and parameter perturbation, the spacecraft is designed on the basis of the hyperbolic tangent adaptive sliding mode control law (ADSVC); 3, an iterative algorithm is improved, and the improved iterative algorithm has better processing capacity on training a data set. On the basis of the ADSVC method finished designing, parameters of a control law are adjusted by means of the improved iterative algorithm, the system can perform parameter adjustment according tothe actual state, and the requirements of rapidness and control precision are met.

Description

technical field [0001] The invention relates to a spacecraft attitude control method, in particular to a spacecraft attitude control method which combines an improved iterative algorithm with an adaptive sliding mode variable structure method. Background technique [0002] With the continuous development of aerospace technology, human beings have become more eager to explore the space world, and the structure of spacecraft has become more and more complicated. The good dynamic quality of spacecraft attitude control system is the key to the success of space mission. The spacecraft will be subject to some complex disturbances in the space environment, including the solar light pressure and gravitational gradient caused by the space environment and radiation, as well as buffeting and parameter perturbations caused by the complex structure of the body and load connections. However, no matter the control scheme is designed using the classical control method or the modern control...

Claims

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Application Information

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IPC IPC(8): G05D1/08
CPCB64G1/244
Inventor 黄平曹雨佳孙婷婷王伟孙延伟贾通王旭刚赵云志王佳安吴闻起黄俊杰杨光
Owner HARBIN ENG UNIV
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