Numerical Analysis of Ignition Overpressure Effect on H-IIB Launch Vehicle
この論文をさがす
抄録
A numerical simulation was conducted to investigate the ignition overpressure mechanism generated by theJapanese H-IIB launch vehicle. A simplified benchmark problem and analysis of a free jet exhausted from a singlesolid booster were used to verify the present numerical method; the unsteady Reynolds-averaged Navier-Stokessimulation was found to be essential for determining the typical features of ignition overpressure, such as the shockwave generated in front of the plume and following starting vortex. Comparing with the measured pressure history atthe launch complex, the numerical result agreed reasonably. The correlation between the wave pattern measured atthe launch complex and the ignition overpressure mechanism was clarified. The effect of ignition overpressure on thelaunch vehicle can be reduced by shielding the inlet of the flame duct with a mobile launcher; however, severe impacton the launch complex is unavoidable. The numerical technique and knowledge obtained in this study are applicablein the preliminary design of a launch pad to mitigate the impact of ignition overpressure.
資料番号: PA1410005000
収録刊行物
-
- Journal of Spacecraft and Rockets
-
Journal of Spacecraft and Rockets 2014-02
American Institute of Aeronautics and Astronautics
- Tweet
詳細情報 詳細情報について
-
- CRID
- 1050285299937479424
-
- NII論文ID
- 120006832325
-
- NII書誌ID
- AA00707776
-
- ISSN
- 00224650
-
- Web Site
- http://id.nii.ac.jp/1696/00022368/
-
- 本文言語コード
- en
-
- 資料種別
- journal article
-
- データソース種別
-
- IRDB
- CiNii Articles