| タイトル | Active Suppression of Pogo on the Space Shuttle |
| 本文（外部サイト） | http://hdl.handle.net/2060/19750016733 |
| 著者（英） | Rubin, S.; Lock, M. H. |
| 著者所属（英） | Aerospace Corp. |
| 発行日 | 1974-10-25 |
| 言語 | eng |
| 内容記述 | The use of active pogo suppressors on the space shuttle was qualitatively investigated. Suppressor design concepts and the effectiveness of these designs in maintaining the stability of the shuttle vehicle were the primary concerns. Suppressor design concepts were developed by means of a series of parametric stability analyses. These two designs together with two designs provided by NASA were evaluated in detail for control effectiveness, performance relative to a passive suppression device, sensitivity of performance to feedback error, suppressor volume flow requirements, and suppressor development requirements. An active device at the high pressure oxidizer pump inlet was shown to provide a simple and effective design that is insensitive to error in the feedback signal. The sizing of an active suppressor was demonstrated to be dependent upon knowledge of the dynamic characteristics of the system. |
| NASA分類 | SPACECRAFT DESIGN, TESTING AND PERFORMANCE |
| レポートNO | 75N24805
ATR-75(7428)-1
NASA-CR-134749 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/189827 |
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