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

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,...

AI Technical Summary

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

Images