Solid-Fuel Regression Rate for Standard-Flow Hybrid Rocket Motors

Journal of Thermal Science and Technology

Takakazu MORITA¹  Saburo YUASA²  Shigeru YAMAGUCHI³  Toru SHIMADA⁴ 

[1] Department of Aeronautics and Astronautics, Tokai University;Department of Aerospace Engineering, Tokyo Metropolitan University;Department of Physics, Tokai University;Institute of Space and Astronautical Science, JAXA;

关键词: hybrid rocket;    fuel regression rate;    turbulent boundary layer;    diffusion-limited analysis;    polymethylmethacrylate (pmma);    prandtl number;   

DOI  :  10.1299/jtst.7.387

来源: DOAJ

【 摘 要 】

Marxman's diffusion-limited analysis of hybrid rocket combustion has been often used to investigate various combustion problems in hybrid rocket motors. This analysis was developed on the basis of the Reynolds analogy in turbulent boundary layers. This analogy assumes that both molecular and turbulent Prandtl numbers are equal to one. In the present study, a semi-empirical correlation between the Stanton number and the skin-friction coefficient in a turbulent boundary layer was obtained. This is applicable to hybrid rocket combustion, and also includes the effects of the Prandtl numbers variation. Using this correlation, a fuel regression rate equation for standard-flow hybrid rocket motors was obtained, and its characteristics were examined. In addition, the calculated regression rate characteristics were compared with the experimental data from the laboratory-scale hybrid rocket motors that used gaseous oxygen (GOX) as oxidizer and polymethylmethacrylate (PMMA) as fuel.

【 授权许可】

Unknown