HYBRID SIMULATION OF A TEMPERATURE RATE FLIGHT CONTROL SYSTEM FOR RE-ENTRY VEillCLES
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چکیده
This Study describes a six degree -of-freedom hybrid simulation for the optimum design of a space vehicle re entry flight control system, utilizing the E A I HYDAC ® 2400 Combined Hybrid Computing System. The specific purpose of the simulation is the evaluation of a temperature-rate flight control system (TRFCS) which utilizes temperature sensors to provide shortperiod stabilization and long term guidance during atmospheric re-entry.
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تاریخ انتشار 2014