Proceedings of the Korean Society of Propulsion Engineers Conference (한국추진공학회:학술대회논문집)
- 2004.03a
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- Pages.687-692
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- 2004
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- 1975-342X(pISSN)
Dynamic Behavior of Liquid Propellant in Reusable Rocket Vehicle
- Himeno, Takehiro (Department of Aeronautics and Astronautics, University of Tokyo) ;
- Nonaka, Satoshi (Institute of Space and Astronautical Sciences, Japan Aerospace Exploration Agenc) ;
- Naruo, Yoshihiro (Institute of Space and Astronautical Sciences, Japan Aerospace Exploration Agenc) ;
- Inatani, Yoshifumi (Institute of Space and Astronautical Sciences, Japan Aerospace Exploration Agenc) ;
- Watanabe, Toshinori (Department of Aeronautics and Astronautics. University of Tokyo)
- Published : 2004.03.01
Abstract
For the prediction of sloshing in the propellant tank of rocket vehicle utilized in RVT (reusable rocket vehicle testing) conducted by ISAS/JAXA, the flow field in the propellant tank during the ballistic flight was experimentally reproduced with the sub-scale model of it. The lateral acceleration as large as about 0.8 G was provided with a mechanical exciter and the deformation of liquid surface in the vessel was visualized with a high-speed camera. The several con-figurations of damping devices were installed and tested in the vessel, which should keep the ullage gas away from the outlet port. It was consequently suggested that the combination of a baffle plate and a perforated cylinder could be effective against the gas suction before the re-ignition of the engine. The sloshing phenomena were also simulated with the CFD code, called CIP-LSM. The numerical results showed good agreement with the corresponding data obtained in the experiment.