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HYBRID SIMULATION OF A TEMPERATURE RATE FLIGHT CONTROL SYSTEM FOR RE-ENTRY VEillCLES
| Content Provider | Semantic Scholar |
|---|---|
| Copyright Year | 2014 |
| Abstract | 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. |
| File Format | PDF HTM / HTML |
| Alternate Webpage(s) | http://bitsavers.trailing-edge.com/pdf/eai/applicationsLibrary/3.4.13h_Hybrid_Simulation_of_a_Temperature_Rate_Flight_Control_System_for_Re-Entry_Vehicles_1965.pdf |
| Language | English |
| Access Restriction | Open |
| Content Type | Text |
| Resource Type | Article |