| タイトル | Method of damping nutation motion with minimum spin axis attitude disturbance |
| 本文（外部サイト） | http://hdl.handle.net/2060/19830019793 |
| 著者（英） | Hoffman, H. C. |
| 著者所属（英） | NASA Goddard Space Flight Center |
| 発行日 | 1983-06-07 |
| 言語 | eng |
| 内容記述 | In a method of and apparatus for damping nutation of a spinning spacecraft, spin axis attitude disturbances are substantially reduced by controlling at least one nutation damping gas thruster to fire with nonuniform gas pulses. During the beginning of a nutation control sequence, the duration of successive gas pulses is gradually increased (up pulsed) from zero to a predetermined maximum duration. The duration of successive pulses is then maintained constant for a time period. Finally, at the end of the nutation control sequence, the duration of successive gas pulses is gradually reduced to zero (down pulsed). Up pulsing of the gas thruster is initiated in response to a predetermined maximum nutation angle measured by an accelerometer. Down pulsing of the thruster is initiated in response to a predetermined minimum nutation angle. |
| NASA分類 | SPACECRAFT DESIGN, TESTING AND PERFORMANCE |
| レポートNO | 83N28064 |
| 権利 | No Copyright |
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