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Rapid stable joint control method for attitude maneuver of spacecraft

A technology of attitude maneuvering and joint control, applied in attitude control and other directions, which can solve the problems of difficult compromise between rapidity and stability

Inactive Publication Date: 2013-08-07
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

[0006] The purpose of the present invention is to solve the problem that the rapidity and stability are difficult to compromise in the existing traditional attitude maneuver control, and to provide a fast attitude maneuver, fast and stable joint control method of the spacecraft, by combining trajectory planning technology and input shaping The advantages of technology enable the spacecraft to not only ensure the rapid maneuvering and stability of the spacecraft, but also avoid the saturation limit of the attitude control actuator

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  • Rapid stable joint control method for attitude maneuver of spacecraft
  • Rapid stable joint control method for attitude maneuver of spacecraft
  • Rapid stable joint control method for attitude maneuver of spacecraft

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Embodiment 1

[0088] A fast attitude maneuver fast stability joint control method of a spacecraft can be accomplished through the following steps:

[0089] Step 1: According to the Euler rotation theorem, the attitude of the rigid body can be changed from a given orientation to any other orientation by rotating around the Euler characteristic axis, during which the angular travel experienced is the shortest, and the Euler characteristic axis is in the rigid body During the rotation process, it is fixedly connected to the rigid body, and it is also immobile relative to the inertial space. Therefore, in order to realize the fast maneuvering and fast stable control of the spacecraft, let the spacecraft maneuver along the shortest path according to the Euler characteristic axis-angle method. This requires first planning the maneuvering path around the characteristic axis, and then performing tracking control on it. This step is to calculate the characteristic axis and determine the rotation an...

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Abstract

The invention relates to a rapid stable joint control method for attitude maneuver of spacecraft and belongs to the field of spacecraft attitude control and vibration control. The method is invented by absorbing advantages in spacecraft attitude maneuver trajectory planing technology and input shaping technology, and allows spacecraft to maneuver in task-required time and keep attitude quickly stable within index required values after maneuvering. Torque outputting capacity of a spacecraft attitude control actuator and maximum angular velocity maneuverability of spacecraft are further considered comprehensively, so that output torque of the spacecraft attitude control actuator is easy to implement.

Description

technical field [0001] The invention relates to a fast attitude maneuver fast stability joint control method of a spacecraft, which belongs to the fields of spacecraft attitude control and vibration control. Background technique [0002] In recent years, the development of large and complex spacecraft such as high-resolution remote sensing satellites and laser communication satellites has received extensive attention. In addition to the ability to control attitude with high precision and high stability, this type of spacecraft also needs to have the ability to maneuver quickly and stabilize quickly to complete space tasks such as agile imaging and fast tracking and targeting. [0003] During the rapid attitude maneuver of the above types of spacecraft, it is inevitable to arouse the structural vibration of the large flexible appendages it carries. This type of vibration is difficult to attenuate due to its own damping characteristics. If effective vibration suppression meas...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08
Inventor 张尧张景瑞何慧东翟光许涛
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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