| タイトル | Evaluation by step response tests of prototype relief valves designed for YF-12 inlet stability bleed system |
| 本文（外部サイト） | http://hdl.handle.net/2060/19750021045 |
| 著者（英） | Neiner, G. H.; Dustin, M. O. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1975-08-01 |
| 言語 | eng |
| 内容記述 | Two stability bleed system relief valves were tested in a special dynamic test facility. These poppet valves are prototypes for a stability bleed system designed for use in a YF-12 flight inlet. One valve is unshielded, while the other has a special shield to eliminate the flow effect pressures on the piston. The tests determined the size of a damping orifice to be used during wind tunnel tests of the bleed system and verified an analog simulation of the valves. The effects of initial pressure level, pressure step size, and spring rate were investigated. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 75N29118
NASA-TM-X-3262
E-8135 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/189167 |
