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首页> 外文期刊>Acta astronautica >Design exploration of combinational spike and opposing jet concept in hypersonic flows based on CFD calculation and surrogate model
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Design exploration of combinational spike and opposing jet concept in hypersonic flows based on CFD calculation and surrogate model

机译：基于CFD计算和替代模型的高超音速流动组合尖峰与反向射流概念的设计探索。

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摘要

The combined thermal protection system has led the drag and heat reduction of hypersonic reentry vehicles to a new developing direction. In order to obtain better resistance to aerodynamic drag and heat while maintain the work stability of the aircraft at the same time, the optimization design of the combined thermal protection system is indispensable. In this paper, a CFD numerical simulation method is combined with a surrogate model based multi-objective optimization algorithm to optimize the configuration of a combinatorial spike and opposing jet thermal protection system in a hypersonic flow with the freestream Mach number of 5.75. The obtained results show that when the total drag coefficient (Cd) and the heat fluxes on the head of the blunt body (Q) are the objective functions, the diameter ratio of the aerodisk to the blunt body bottom (d/D) has no significant effect on the drag and heat flux reduction, and it can be neglected in the optimization process. While the objective functions Cd and Q are affected by the three variables the length-to-diameter ratio of the aerospike (L/D), the jet pressure ratio (PR), and the nozzle radius (r(0)) in similar ways. Therefore, in this case, the optimization problem can be transformed into a single-objective optimization problem. The quadratic response surface model established by sample points obtained by the orthogonal experimental design method is of high simulation accuracy, with the determination coefficients of Cd and Q are 0.964 and 0.965 respectively, and there is only a difference of -6.96% in the objective function Cd, -0.93% in Q between the optimization results and the CFD results. The combined thermal protection system has better performance in both drag and heat reduction than the single spike or opposing jet systems. Compared with the pure blunt body, the total drag coefficient and heat flux on the head of the blunt body with the combined thermal protection system have significantly decreased, with the Cd goes down 86.66%, and the wall heat flux Q drops off 96.37%.
机译：组合式热保护系统已将高超音速再入飞行器的减阻和降热带向了新的发展方向。为了在保持飞机的工作稳定性的同时获得更好的抵抗空气阻力和热量的能力，组合式热保护系统的优化设计是必不可少的。本文将CFD数值模拟方法与基于替代模型的多目标优化算法相结合，以在自由流马赫数为5.75的高超声速流中优化组合尖峰和反向射流热保护系统的配置。获得的结果表明，当总阻力系数（Cd）和钝体头部的热通量（Q）是目标函数时，航空器磁盘与钝体底部的直径比（d / D）不存在。对阻力和热通量的减少有很大影响，在优化过程中可以忽略不计。目标函数Cd和Q受三个变量影响时，气钉的长径比（L / D），喷射压力比（PR）和喷嘴半径（r（0）） 。因此，在这种情况下，可以将优化问题转换为单目标优化问题。通过正交实验设计方法得到的采样点建立的二次响应面模型具有较高的模拟精度，Cd和Q的测定系数分别为0.964和0.965，目标函数仅相差-6.96％ Cd，优化结果和CFD结果之间的Q值为-0.93％。组合式热保护系统在阻力和热量减少方面均比单尖峰或反向喷射系统具有更好的性能。与纯钝体相比，组合热保护系统的钝体头部总阻力系数和热通量显着降低，Cd下降86.66％，壁热通量Q下降96.37％。

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