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Hypersonic Analysis of Mu Space Engineering Spacecraft (Muses-C) Re-Entry Capsule

Sravankumar Kota, P.V. Subbaraju


During the most recent decade, a quick development of learning in the field of reemergence and planetary passage has brought about numerous critical advances helpful to the understudies, specialists and researchers. The issue related with space flight, interplanetary travel or satellite circle is the physical recuperation or survival of the vehicle and its payload (faculty, instruments, etc.) on the earth surface or planetary surface. For atmospheric planets, the issue includes basically deceleration, streamlined warming and control of the time and area of landing. For non-atmospheric planets, the issue essentially incorporates just deceleration and control of the time and territory of landing. A general delineation of atmospheric and non-atmospheric planetary segment goes before the examinations of the issue. The main objective of this paper is to study and analysis over new re-entry vehicle and their concept of Mu Space Engineering Spacecraft, i.e., MUSES-C, also the other name called as HAYABUSA. Unlike other papers that held analysis only in ground conditions, here various altitudes have been chosen. For the purpose of analysis, we are using a tool called as computational fluid dynamics. Analysis is carried out for earth entry conditions at an angle of attack 0°, and 30°. The Mach number here we are choosing for MUSE-C is 5, 9, 11 and 12. The flow field over MUSE-C entry capsule is computed at hypersonic speeds using commercial CFD software FLUENT for ideal gas model. Viscous flow models are considered for standard flow properties. The key challenge is to capturing the shock wave, shock stand-off distance and properties behind the shock wave accurately by using laminar model. The results that can be compared with previous journal application of the TAU Code to Re-Entry Capsule Concepts.



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