高超声速飞机透水表面最佳热防护数学建模

2015 International Conference "Stability and Control Processes" in Memory of V.I. Zubov (SCP) Pub Date : 2015-12-03 DOI:10.1109/SCP.2015.7342145

N. Bilchenko

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引用次数: 12

摘要

研究了进入大气层的高超声速飞行器表面最佳射流热防护数学建模问题。研究了可压缩气体层流边界层中的物理化学过程(解离和电离)。将群理论方法应用于分布参数系统的优化。得到了一阶近似的最优控制。考虑了高超声速飞机表面热防护接近最优时采用特殊打击律的几种可能性。讨论了计算实验和数值结果。

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Permeable surfaces hypersonic aircraft optimal heat protection mathematical modeling

The problems of intended for the atmosphere entry hypersonic aircraft surfaces optimal effusion heat protection mathematical modeling are considered. The physico-chemical processes (the dissociation and the ionization) in laminar boundary layer of compressible gas are appreciated. The Groups theory approach to distributed parameters systems optimization is applied. An optimal control in the first approximation in analytical form is obtained. Some possibilities of special blow laws use for hypersonic aircraft surfaces heat protection nearing to optimal are considered. Computation experiments numerical results are discussed.

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2015 International Conference "Stability and Control Processes" in Memory of V.I. Zubov (SCP)

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