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• W2795146210 abstract "Validating the stability and evaluating the performance of an autonomous space system is crucial for space missions. Hardware-in-the-loop simulation is a suitable strategy for addressing this demand. This article describes the procedure for the hardware-in-the-loop test of the attitude control system of a small upper stage built at the Iranian Space Research Center. The hardware and software verification procedure in two main modes of the attitude control system, i.e. detumbling and pointing, is considered. The control efforts are produced by 12 reaction control thrusters which are capable of producing torques around roll, pitch and yaw axes. The test procedure is devised in two parts: In the first part, the controller parameters are tuned to optimize two performance criteria in the detumbling and pointing modes in the presence of time-varying disturbing torques and disturbances, while in the second part, the controller parameters are optimized with respect to the pointing precision regardless of fuel consumption." @default.
• W2795146210 created "2018-04-06" @default.
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• W2795146210 date "2017-12-01" @default.
• W2795146210 modified "2023-09-23" @default.
• W2795146210 title "Low-cost hardware-in-the-loop test of a spacecraft attitude control system" @default.
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• W2795146210 doi "https://doi.org/10.1109/kbei.2017.8324873" @default.
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