Attitude control algorithms for a descent vehicle returning from the moon
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We consider the problem of attitude control of a descent vehicle in the Earth’s atmosphere returning from the Moon. A stabilization algorithm with a deadband and the optimal parameters, obtained with the numerical method, provide adequate landing accuracy and an allowable load factor under the influence of a set of disturbances. Using the method of mathematical simulation, it is shown that the fuel consumption is reduced by ~30% in comparison with the initial stabilization parameters for the descent from a near-Earth orbit.
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