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Heat Transfer on a Jet Vane Surface Installed in a Rocket Nozzle  

Yu Man Sun (연세대학교 기계공학과)
Cho Hyung Hee (연세대학교 기계공학과)
Hwang Ki Young (국방과학연구소)
Bae Ju Chan (국방과학연구소)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.9, no.1, 2005 , pp. 9-16 More about this Journal
Abstract
Jet vane is an useful component which is installed at the end of a nozzle for the purpose of the posture control and the secure controlling stability during the initial launching of a rocket. During several seconds from its initial launching moment, the JV driving part is heated due to the direct contact of the vane with the combusted gas and the vane is ablated mechanically or chemically. In this study, as the fundamental study for the thermal analysis of jet vane, the heat transfer into a jet vane which is located in the uniform supersonic flow field is calculated. For this, boundary layer integral method and finite difference method are used simultaneously. Based on the thermal boundary conditions derived from the analysis, the transient heat conduction in the vane is also calculated.
Keywords
Jet vane; Heat transfer; Boundary layer integral method;
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