Flexible satellite attitude maneuver control method based on binomial approximation model

A technology of approximate model and satellite attitude, applied in the direction of motor vehicles, space navigation equipment, space navigation aircraft, etc., to achieve the effect of strong function, improved simplicity and effectiveness, and broad engineering application prospects

Active Publication Date: 2020-12-22
BEIHANG UNIV
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Problems solved by technology

Due to the limitations of traditional control methods in the face of complex flexible bodies, there are potential risks in modern satellite applications

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  • Flexible satellite attitude maneuver control method based on binomial approximation model
  • Flexible satellite attitude maneuver control method based on binomial approximation model
  • Flexible satellite attitude maneuver control method based on binomial approximation model

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Embodiment Construction

[0046] The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0047] At present, in the study of attitude control of flexible satellites, how to design a simple and feasible control law to complete the attitude maneuver of the satellite is an important issue to enhance the application of satellites. In the present invention:

[0048] Such as figure 1 As shown, firstly, the expected maneuvering path of the satellite’s three axes is introduced, and the sampler is used to sample the output of the satellite’s attitude gyroscope to obtain the sampling value of the three-axis attitude; value, construct a discrete approximate model of the satellite attitude, on this basis, shift and make difference with the sampling value of the expected path, obtain an approximate model of the expected error, and further design a sampling control law based on this model; pass this control law through the zero-order The hold...

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Abstract

The invention provides a flexible satellite attitude maneuver control method based on a binomial approximation model, which can realize rapid rotation control of a satellite attitude by utilizing output sampling and input zero-order keeping under the condition of partial system parameters. The method can be applied to a satellite attitude system, not only can be used for realizing attitude stabilization, but also can be used for tracking a set target, and is different from a traditional control algorithm which can be used for a system with unknown system parameters due to low complexity and high calculation efficiency, and has relatively high robustness for various external interferences; The method has the characteristics of flexible application and strong functions, and has a wide application prospect.

Description

technical field [0001] The invention relates to the field of satellite attitude control, in particular to a satellite attitude maneuver control method based on a simplified model. Background technique [0002] With the rapid development of modern satellites, the attitude maneuverability of satellites has received more and more attention. Higher requirements are put forward for the reliability of the satellite attitude control law. [0003] At present, traditional controllers are used to exert control on simple satellites to achieve attitude maneuvering. The increase in mission requirements of satellites causes the structure of satellites to become increasingly complex, forming a flexible body with multiple structures. Due to the limitations of traditional control methods in the face of complex flexible bodies, there are potential risks in modern satellite applications. [0004] Therefore, how to achieve attitude maneuvering of flexible satellites with low cost and easy tr...

Claims

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Application Information

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IPC IPC(8): G06F30/15G06F30/20B64G1/24G06F17/12
CPCG06F30/15G06F30/20B64G1/244G06F17/12B64G1/245
Inventor 吕金虎陈磊刘克新谷海波朱国梁
Owner BEIHANG UNIV
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