A Stable Deployment Control Method for Space Tethered Formation

A technology of space tethering and control method, which can be applied to control/adjustment systems, non-electric variable control, three-dimensional position/channel control, etc., and can solve problems such as difficulty in stable deployment of the system

Active Publication Date: 2021-11-16
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

[0004] Due to the characteristics of nonlinear and strong coupling in system dynamics, the deployment of the system includes not only the complete release of the tether, but also the rotation of the system. Therefore, how to realize the stable deployment of the system is a relatively difficult problem. technology to study this unfolding process

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  • A Stable Deployment Control Method for Space Tethered Formation
  • A Stable Deployment Control Method for Space Tethered Formation
  • A Stable Deployment Control Method for Space Tethered Formation

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Embodiment Construction

[0044] Embodiments of the present invention are described in detail below, and the embodiments are exemplary and intended to explain the present invention, but should not be construed as limiting the present invention.

[0045] To realize the stable deployment of the triangular space tether formation and provide guarantee for the completion of related space tasks, the present invention proposes a stable deployment control method for the triangular space tether formation, which provides a feasible method for the actual deployment of the space tether formation. The plan laid the foundation for the formation system to successfully perform space tasks such as earth observation and earth orientation.

[0046] In order to achieve the above object, the technical solution adopted in the present invention comprises the following steps:

[0047] 1) Establish the dynamic model of the triangular configuration space tether formation;

[0048] 2) Design the control law for the stable deplo...

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Abstract

The present invention proposes a stable deployment control method of a space tether formation. Firstly, by substituting the kinetic energy and potential energy of the formation system into the Lagrangian dynamic equation, a dynamic model of the triangular configuration space tether formation is established. Secondly, according to the obtained The dynamic model of the triangular configuration space tether formation is used to determine the control law for the stable deployment of the triangular configuration space tether formation. The present invention considers the elasticity in the tether on the basis of the traditional particle link model when establishing the dynamic model of the triangular configuration space tether formation, and fully retains the flexibility of the system. Moreover, in the stable deployment control of the triangular configuration space tether formation, the present invention comprehensively considers the length of the tether and the angular velocity of rotation, so that the system can be deployed stably in a state of elongation while rotating, which is beneficial to the subsequent formation of various spaces. The completion of the task.

Description

technical field [0001] The invention belongs to the field of control technology research of a multi-spacecraft formation system, and in particular relates to a stable deployment control method of a triangular configuration space tether formation. Background technique [0002] The space tether formation connects multiple satellites through tethers to form a specific structure. It not only has the characteristics of low cost, good performance, high reliability and strong flexibility of the traditional multi-spacecraft system, but also has the ability to reduce fuel consumption while precise positioning. The advantages of energy consumption and improved life are then widely used in space tasks such as earth observation and earth orientation. [0003] A typical triangular space tether formation is a planar triangular closed system formed by three satellites and three tethers separated and connected in series. After the system is launched into space, it needs to be controlled fr...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/10
CPCG05D1/104
Inventor 黄攀峰周合张帆刘正雄
Owner NORTHWESTERN POLYTECHNICAL UNIV
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