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Numerical simulation of the lateral aerodynamics of an orbital stage at stage separation flow conditions

机译：级分离流动条件下轨道级横向空气动力学的数值模拟

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The unsteady flow of an idealized two-stag hypersonic vehicle during the separation process is investigated. In particular, the aerodynamic characteristics of the orbital stage performing yaw and roll oscillations with Defined frequencies at a certain distance above the lower stage are addressed. The numerical simulations of The flowfield are based on an explicit finite-volume method for solutions of the three-dimensional unsteady Euler equations. The discretization of the computational domain around the entire configuration is performed Using a flexible multiblock grid generator. The results focus on the flowfields and the pressure distributions As well as on the aerodynamic coefficients. The latter provide an essential mean for the stability and control Evaluations for lateral motion in hypersonic flight. The analysis show that unsteadiness cannot be neglected.
机译：研究了理想的两级高超音速飞行器在分离过程中的非稳态流动。特别地，解决了在下级上方一定距离处以限定的频率执行偏航和侧倾振荡的轨道级的空气动力学特性。流场的数值模拟基于显式有限体积方法，用于求解三维非稳态Euler方程。使用灵活的多块网格生成器执行围绕整个配置的计算域的离散化。结果集中在流场和压力分布以及空气动力学系数上。后者为高超声速飞行中横向运动的稳定性和控制评估提供了必要的手段。分析表明，不稳定是不能忽略的。

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