Study on optimal filtering for attitude determination applied to the moon-sun sensor
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The paper presents a Nonlinear Adaptive State Estimator (NASE) based on an adaptive technique. This technique uses the sensor out-puts for directly building the estimator gain, and the difference between the output of the sensors and the estimate outputs is defined as output error. Then the gain computation algorithm involves an integration of a weighted dyatic form of the output error. If the linearized system is observable, the estimator stability can be demonstrated even in the presence of the higher order terms due to the linearization. Moreover the NASE approach does not involve the computation of the linearized state equation matrix, which is a great simplification when the nonlinear system equation is not so simple to handle. The applicability of NASE approach is also demonstrated for noisy systems. The adaptive estimator is applied to the attitude determination problem by using three-axis rate gyros, and the Moon Sun Sensor (MSS). The MSS is an attitude sensor recently presented, which enables us to have more information about the spacecraft attitude, than it is usually case. A brief description of MSS sensor is given, with an assessement on the instrument accuracy. Finally, some numerical tests are given.
SPACEFLIGHT MECHANICS 1997, PTS 1 AND 2
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