An adaptive estimator is presented and performance is demonstrated which successfully tracks a powered spacecraft and estimates the spacecraft state. The system dynamics are inherently nonlinear due to the presence of gravity. The measurement model, with measurements of line-of-sight range, azimuth, and elevation, is also nonlinear. The estimator assumes a linearized, time varying dynamical system with a constant deterministic acceleration. In the paper, an algorithm is derived which makes use of the innovations to compute a constant acceleration approximation to the real system dynamics. The optimality and performance of the algorithm are demonstrated via repeated Monte Carlo simulations of a typical space tracking scenario. The scenario under consideration consists of tracking a spacecraft which performs an orbit transfer maneuver. Sensor line-of-sight measurements are simulated using the tracking geometry and a synthetic noise model.
Adaptive estimation of a powered spacecraft
Adaptivabschaetzung eines angetriebenen Raumfahrzeuges
Control and Computers ; 14 , 1 ; 17-20
1986
4 Seiten, 3 Quellen
Aufsatz (Zeitschrift)
Englisch
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