Spacecraft orbital orientation stabilization by the inertial executive devices using unloading by the structure transformation method
Published: 14.05.2024
Authors: Simonyants R.P., Bulavkin V.N.
Published in issue: #5(149)/2024
DOI: 10.18698/2308-6033-2024-5-2359
Category: Aviation and Rocket-Space Engineering | Chapter: Design, construction and production of aircraft
The paper presents a method of unloading the inertial executive bodies in the spacecraft orbital orientation stabilization system without consuming the working fluid mass. It is based on application of the structure adaptive transformation principle. The properly changed object parameters form the external moments providing release of the kinetic moment accumulated during stabilization. An analysis of the external moment’s sensitivity to variations in the transformed structure parameters is provided creating a basis to select the influence parameter that realizes the most effective unloading. The paper considers an example of a geostationary spacecraft equipped with solar panels with the autonomous drive making it possible to control the structure configuration and ensure unloading by the solar light pressure moments without violating the orbital orientation. For a simplified model of the plane pitch motion dynamics, analytical solutions were obtained, they were confirmed by simulation.
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