| Summary: | 碩士 === 中正理工學院 === 兵器系統工程研究所 === 88 === The flow field induced by the separation of a strap-on booster during the flight of strap-on launch vehicles is highly complex and inherently unsteady. Most previous studies on these flow fields were focused on experimental works. However, the experiment works are usually expensive, difficult to be operated and even dangerous. Therefore, a numerical model on the near field flow environment can be used to reduce the development and testing costs, and also to provide detailed information needed for structural design.
An inviscid, three-dimensional numerical model of the time-dependent near field flow environment of separating strap-on booster has been developed in this thesis. The accuracy of the present work in simulating both steady and unsteady flowfields has been verified too. The present result shows that the booster control wing will enhance the vortex near the main missile. Besides, the gap between booster and main missile can also affect the missile performance. Moreover, it is believed that the present computer code can be used to assist the development work of supersonic vehicle in future.
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