Techniques of testing algorithms for controlling spacecraft angular motion
Authors: Merkuryev S.A.
Published in issue: #6(102)/2020
DOI: 10.18698/2308-6033-2020-6-1990
Category: Aviation and Rocket-Space Engineering | Chapter: Aircraft Dynamics, Ballistics, Motion Control
The paper considers the technique of the initial developing algorithms for controlling the angular motion of an automatic spacecraft as a solid body. The mathematical model of the control object is given by the Euler’s dynamic equations and kinematic equations written using the Rodrig — Hamilton parameters. The technique has a simple form and is intended for control algorithm rough testing. Its structure allows adding complexity in the initial model of the system by adding models of onboard devices and external effects. The efficiency of the method was tested on the example of working out an algorithm with a dead zone for the solar-pointing control mode of an automatic spacecraft. In this mode, a solar sensor was used as a measuring device, and flywheel engines were used as executive bodies. The results of simulation in the MathWorks MATLAB environment are presented.
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