48th Fluid Dynamics Conference /the 34th Aerospace Numerical Simulation Symposium (July 6-8, 2016. The Kanazawa Theatre), Kanazawa, Ishikawa, Japan
抄録（英）
The objective of this study is to reveal extinction-reignition ascendancy, which is one of the beneficial points of hybrid rocket, for expanding downrange and duration in the lower thermosphere in view of simple control of oxidizer mass flow. Swirling-flow oxidizer is furnished with solid fuel; we adopt polypropylene for solid fuel and liquid oxygen for oxidizer. A multidisciplinary design optimization has been implemented by using a hybrid evolutionary computation; data mining has been also conducted by using a scatter plot matrix to efficiently perceive the entire design space. It is consequently revealed that the hypothesis in the prior study is proved; extinction-reignition extends not only duration but also, downrange. Scatter plot matrix results express physical mechanisms of design-variable behaviors for the objective functions and also the roles of the design variables via bird's-eye visualization of the entire design space constitution.
内容記述
形態: カラー図版あり
内容記述（英）
Physical characteristics: Original contains color illustrations
Effective operations of hybrid-rocket extinction-reignition via oxidizer-mass-flow control
AA1630031015.pdf
(1.41MB)
