| Abstract: | The aerodynamic configuration of reentry module of manned spacecraft is satisfied by a number of requirements, primary of these are aerodynamic stability,controllability, trim lift to drag ratio, maximum load factor, maximum heat transfer rate,total heat load,aerodynamic maneuvering capability, accuracy of landing and volumetric efficiency,etc. The spherical segment cone module of small lift to drag ratio vehicles is the optimum shape than others.This paper introduces the selective method of reentry module configuration,presents its parametersresearc hed for spherical nose bluntness,semiapex angle of truncated cone, curvature radius of nose corner, module fineness ratio,diameter of maximum cross section.The analysis results are obtained quantitatively and qualit atively in this paper. |
