Spacecraft visual axis maneuvering control device considering dynamic pointing constraint

Abstract

The invention provides a spacecraft visual axis maneuvering control device considering a dynamic pointing constraint. The method includes the steps that a spacecraft visual axis control system model is established, a mathematic model of the dynamic constraint is provided, and a potential function and a control rule of a design system are established. Aiming at the spacecraft visual axis maneuvering control problem, the practical problem that the dynamic pointing constraint exists in spacecraft rotating space is considered, the spacecraft control rule combined with a potential function method is provided, and a spacecraft can complete control tasks and autonomously achieve the dynamic constraint. By means of the method, the stability of a spacecraft attitude control system is guaranteed when the dynamic pointing constraint exists in the space, the constraint can be autonomously avoided, the requirements of the spacecraft on ground communication are reduced, and the autonomous control capacity of the spacecraft is improved.

Description

technical field [0001] The present invention relates to the technical field of spacecraft control, in particular to a method for maneuvering control of the boresight of a spacecraft in consideration of dynamic pointing constraints, which is mainly applied to spacecraft performing boresight maneuvering tasks in space and there are dynamic pointing constraints of the boresight in space In this case, a control method is proposed so that the spacecraft can autonomously avoid the dynamic constraints when performing boresight maneuver control. Background technique [0002] The attitude control problem of spacecraft is an integral part of spacecraft control and has very important engineering application significance. In the general attitude control problem, the designer uses all the attitude information of the spacecraft, but in some control tasks, all the attitude information of the spacecraft is not needed. For example, in the task of controlling the pointing of an instrument su...

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Problems solved by technology

Chinese patent CN201610323291.7 proposes a single-axis pointing pure magnetic control algorithm for another space vehicle based on geometric analysis. The single-axis control is realized through the interaction between the magnetic torque output by the magnetic torque device and the geomagnetic field. However, this method only considers the magnetic control algorithm. does not take into account the pointing constraints of the single axis

In the Chinese patent CN201710521561.X, the attitude constraint and the spacecraft attitude maneuver control problem dealing with anti-unwinding are considered, and a new potential function is proposed by combining the attitude constraint and the anti-unwinding problem, but the four elements of attitude are used in this method To represent the attitude of the spacecraft, that is, all the information of the attitude of the spacecraft is required, and this invention only considers the static constraints and does not consider the dynamic constraints

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