Jean-Sébastien Ardaens

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Roman Symbols a = Semimajor axis A = Plant matrix B = Deterministic matrix e = Eccentricity ec = Control error vector GM = Gravitational parameter i = Inclination K = Gain matrix l = Reference separation between the occulter and the coronagraph M = Mean anomaly Q = Control error weighting matrix ∗Research Assistant, Institute for Space Sciences, CSIC, 08034(More)
This work describes the design of an impulsive manoeuvres’ planner meant for onboard autonomous optimum formation flying reconfigurations in near-circular orbit. The whole variation of the relative orbit is stepwise achieved through intermediate configurations, so that passive safety and delta-v consumption minimisation are pursued. The description of the(More)
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