Guidance and Control Technology of Spacecraft on Elliptical Orbit by Fucheng Liu & Shan Lu & Yue Sun

Author:Fucheng Liu & Shan Lu & Yue Sun
Language: eng
Format: epub
ISBN: 9789811079597
Publisher: Springer Singapore

(2)The specific value output by accelerometer can be converted from the body coordinate system to the inertial coordinate system by using the attitude matrix.

Generally, the attitude matrix is solved by Euler angle method, directional cosine method, and quaternion method. Since the quaternion method has the advantages of full attitude, small computation, and little error, the current SINS system basically uses the quaternion method. The main steps of solving the attitude matrix by the quaternion method are as follows:(1)Solve differential equations of quaternion and normalize quaternion according to the current relative angular rate ;

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