Small Satellite Attitude Control Using Linear Moving Mass Actuators
نویسندگان
چکیده
The subject of this research is to study the use of internal moving masses as the primary means of attitude control for a small satellite platform. The goal of this research is to validate the dynamic model formulated in [1] which describes the under-actuated rotational dynamics of a 3U cubesat with two internal orthogonal linearly translating masses. Models have been developed to simulate angular velocity profiles based on different moving mass profiles. These numerical simulations have been compared to experiment data using the Whorl-I spacecraft simulator at the Space Systems Simulation Laboratory (SSSL) at Virginia Tech. This simulator provides a near frictionless environment which allows for testing of rotational dynamics in a simulated microgravity environment. In this paper, the trends in the angular velocity profiles obtained from experimental data are compared to results from the numerical simulations and show agreeable results.
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