| タイトル | Effects of Control Hysteresis on the Space Shuttle Orbiter's Entry |
| 本文（外部サイト） | http://hdl.handle.net/2060/19770014195 |
| 著者（英） | Powell, R. W. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1975-06-01 |
| 言語 | eng |
| 内容記述 | There are six degree-of-freedom simulations of the space shuttle orbiter entry with aerodynamic control hysteresis conducted on the NASA Langley Research Center interactive simulator known as the Automatic Reentry Flight Dynamics Simulator. These were performed to determine if the presence of aerodynamic control hysteresis would endanger the mission, either by making the vehicle unable to maintain proper attitude for a safe entry, or by increasing the amount of the reaction control system's fuel consumption beyond that carried. |
| NASA分類 | ASTRODYNAMICS |
| レポートNO | 77N21139
NASA-TM-X-74681 |
| 権利 | No Copyright |
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