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Computational Fluid Dynamic Simulation of Space Shuttle Orbiter During Contingency Abort Maneuvers

机译:应急中止机动中航天飞机轨道器的计算流体动力学仿真

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To improve the safety of the space shuttle orbiter (SSO), NASA is reexamining return-to- launch-site and transatlantic abort scenarios. Ames Research Center, in partnership with Boeing Reusable Space Systems (BRSS) and Johnson Space Center (JSC), has used computational fluid dynamics (CFD) to estimate the aerodynamic loads that would be experienced by the SSO during these abort maneuvers, for which very limited information exists relating to surface pressure distributions. Ames provided 38 cases that cover the Mach number range from 3.5 to 15, angle of attack range of 20 to 60 degrees, three elevon/body-flap combinations, and two speed-brake deflections. Additionally, five benchmark cases were computed and compared with data from the Orbiter Aerodynamic Data Book (OADB), which is the rigorous standard of SSO aerodynamics.

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