Gyroscope-free independent space attitude maneuver control method of Martian probe

A Mars probe, attitude maneuvering technology, applied in attitude control and other directions, can solve the problems of using Euler angle singularity, limited maximum speed of flywheel, etc., to achieve the effect of ensuring accuracy and stability

Active Publication Date: 2013-04-03
上海航天控制工程研究所
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Problems solved by technology

[0003] When performing the control law of attitude maneuvering, the control feedback amount must be selected first. In the past, satellites used the gyro to measure the angular rate and integrate it into the Euler angle as the feedback input. Solve the calculation; when the angle of attitude maneuvering is large, using Euler angles may appear singular; the most important reason is that due to the limited maximum speed of the flywheel, using Euler angles for attitude maneuvering is more likely to saturate the flywheel. Therefore, it is necessary to develop a An Attitude Maneuvering Control Technique Without Gyro Data

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  • Gyroscope-free independent space attitude maneuver control method of Martian probe
  • Gyroscope-free independent space attitude maneuver control method of Martian probe
  • Gyroscope-free independent space attitude maneuver control method of Martian probe

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[0015] Such as figure 1 As shown, when the detector needs attitude maneuvering, first unload the flywheel speed to 200rpm, so that the angular momentum of the flywheel reaches the need before attitude maneuvering, and then perform attitude maneuvering, and the integrated electronic computer calculates the Euler angle and the Euler rotation axis, so that To realize the rotation of the star from the current pointing to the target pointing, and the determination of the time required for the attitude maneuver should be calculated according to the maximum rotational speed of the reaction flywheel and the maximum torque that can be provided.

[0016] The large-angle attitude maneuver control of the Mars rover is realized by making the star rotate around the Euler axis in a single axis. Get the desired target pointing to the quaternion q ir After that, according to the measurement of the star sensor, the q ib , you can calculate the error quaternion q required to rotate the current...

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Abstract

The invention discloses a gyroscope-free independent space attitude maneuver control method of a Martian probe. The gyroscope-free independent space attitude maneuver control method is applied to attitude maneuver control of the probe among different oriented targets, and can implement attitude maneuver in any direction by virtue of data of a star sensor without gyroscope data. The method comprises the following steps of: determining four elements of a target attitude before implementing the attitude maneuver of the probe, and performing closed-coop control on a star body by a flywheel to implement the attitude maneuver around an Euler axis within a shortest route. Compared with the prior art, the method has the advantages that the attitude maneuver in any orientation can be completed within the shortest route with the configuration of minimum hardware, namely the star sensor and the flywheel, and the method is practicable.

Description

technical field [0001] The invention relates to a Mars probe attitude maneuver control technology, especially for the gyro-free attitude maneuver control mode of the Mars probe between different orientation targets. The four elements of the target attitude are determined before the attitude maneuver of the probe, relying only on the star sensor Measure the data, use the flywheel closed loop to control the star around the Euler axis to complete the attitude maneuver with the shortest path. Background technique [0002] When carrying out the Mars exploration mission, it is necessary to complete the photo taking task for the Mars orientation, complete the data transmission task for the Earth orientation, and complete the orientation of the solar cell array to the sun to ensure the energy supply of the whole star. It is possible to perform attitude maneuvers at any angle when switching between orientation targets. [0003] When performing the control law of attitude maneuvering,...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08
Inventor 尹海宁周连文聂章海杜宁李芳华蔡陈生袁彦红
Owner 上海航天控制工程研究所
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