Japan Aerospace Exploration Agency(JAXA)
Japan Aerospace Exploration Agency(JAXA)
Japan Aerospace Exploration Agency(JAXA)
Japan Aerospace Exploration Agency(JAXA)
Japan Aerospace Exploration Agency(JAXA)
出版者（英）
American Institute of Aeronautics and Astronautics
雑誌名
Journal of Spacecraft and Rockets
発行年
2014-02
抄録（英）
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.
Numerical Analysis of Ignition Overpressure Effect on H-IIB Launch Vehicle
PA1410005.pdf
(2.33MB)
