An algorithm for solving the flow around the Orbital Vehicle at the time of its re-entry has been formulated. The physics behind the behavioral pattern of a re-entry vehicle has been a topic of research for a long time. It has been seen that a blunt nose configuration is preferred over a sharp nose configuration. Direct Simulation Monte Carlo method has been used to develop a code in Matlab to simulate the flow. The main equation governing the flow is Maxwell-Boltzmann equation which is due to consideration of rarefied flows at altitudes beyond 80 km. A unique method of introducing the coordinates of the geometry is used. The results for Knudsen number 0.03 were compared with Ansys results. Also an optimized model of the Orbital Vehicle is suggested without compromising the purpose, which can be used for further studies and development.
|Title of host publication||International Conference on Mechatronics and Mechanical Engineering|
|Number of pages||5|
|Publication status||Published - Oct 2016|
Krishnamurthy, V., Periasamy, R. A. S., Saxena, V., Hari, N. H., & Chandrasekhar, S. (2016). DSMC solver for an optimized Space Crew reentry Orbital Vehicle. In International Conference on Mechatronics and Mechanical Engineering