| タイトル | Test Data of Flow Field of Shuttle SRM Nozzle Joint with Bond Defects, Using Unheated Air |
| 本文（外部サイト） | http://hdl.handle.net/2060/19900009148 |
| 著者（英） | Hair, Leroy M.; McAnally, James V.; Hengel, John E. |
| 著者所属（英） | NASA Marshall Space Flight Center |
| 発行日 | 1989-05-01 |
| 言語 | eng |
| 内容記述 | The nozzle-to-case joint on the Shuttle SRM (as redesigned after the Challenger accident) features an adhesive sealant filling and bonding the joint, with a wiper O-ring to prevent the adhesive from reaching and disabling the closure O-ring. Flawless implementation of that joint design would ensure that hot, corrosive propellant combustion gases never reach the closure O-ring. However, understanding the flow field related to bonding defects is prudent. A comprehensive test program was conducted to quantify such flow fields and associated heating environments. A two-dimensional, full-scale model represented 65 inches of the nozzle joint, using unheated air as the test medium, in a blowdown mode. Geometry variations modeled RSRM assembly tolerances, and two types of bonding defects: pullaways and blowholes. A range of the magnitude of each type defect was tested. Also a range of operational parameters was tested, representative of the RSRM flow environment, including duplication of RSRM Mach and Reynolds numbers. Extensive instrumentation was provided to quantify pressures, heat rates, and velocities. The resulting data established that larger geometric defects cause larger pressure and larger heating, at the closure O-ring region. Velocity trends were not so straight-forward. Variations in assembly tolerances did not generally affect flow fields or heating. Operational parameters affected flow fields and heating as might be expected, increasing density or velocity increased heating. Complete details of this test effort are presented. |
| NASA分類 | SPACECRAFT PROPULSION AND POWER |
| レポートNO | 90N18464 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/138905 |
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