Abstract
The design and analysis of the Earth Observing System AM-1 spacecraft Earth acquisition mode are presented. In addition to addressing the practical design of the spacecraft attitude control system, some mathematical proofs of the system stability based on the spacecraft nonlinear dynamics and kinematics are demonstrated. The main approach of the analysis is to identify all of the equilibrium points of the closed-loop system and then to investigate the stability of each of the equilibrium points. Since it is not restricted to near the nominal operating point, this work extends the previous linear analysis results to certain cases where large attitude errors are possible. All three control configurations in the Earth acquisition mode are investigated. The system convergence from any yaw attitude to the nominal Earth pointing attitude is proven, The results developed in the paper provide a deeper understanding of the system dynamics and are especially useful in analyzing off-nominal launch-vehicle/spacecraft separations and in determining submode tradition thresholds. The design and analysis are supported by high-fidelity spacecraft simulation. (Author)
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