Single- and Multi-objective Optimization of Scramjet Components Using Genetic Algorithms Based on a Parabolized Navier-Stokes Solver
Single- and Multi-objective Optimization of Scramjet Components Using Genetic Algorithms Based on a Parabolized Navier-Stokes Solver
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DOI：
10.2514/6.2006-4686
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发表时间：
2006-07
期刊：
影响因子：
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通讯作者：
Chen Bing;Xu Xu-Xu;Cai Guobiao
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文献类型：
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作者：
Chen Bing;Xu Xu-Xu;Cai Guobiao
设计了一种可在继电器马赫数（Ma=3.5）下自启动的二维高超声速进气道。然后利用序列二次规划（SQP）、多岛遗传算法（MIGA）和多目标遗传算法（MOGAs），即邻域培育遗传算法（NCGA）和非支配排序遗传算法II (NSGA-II)，在Ma=7.0的巡航作业点上对二维进气道进行单目标或多目标优化设计。在这些优化中，使用单掠抛物线化Navier-Stokes （SSPNS）算法代码计算进气道流场，该算法代码先前在超声速/高超声速流场模拟中被证明是高精度和高效的。单目标优化结果表明，压力恢复最大模型优于有效动能系数最大模型。多目标优化结果揭示了总压恢复、静压上升和阻力系数之间的权衡。基于多目标设计过程，研究了多工作点设计和设计点确定过程。结果表明，将设计点设置在巡航点，非设计运行质量捕获系数相对较低；而当设计马赫数为6.5时，二维进气道在恒定动态轨迹上的整体运行性能较好。将相同的优化设计方法应用于多个2D单扩展斜坡喷管（sern）的设计。单目标优化设计结果表明，目标即推力系数有所提高，但相应的升力系数相对较低。在二目标和三目标情况下，得到了推力系数、升力系数和俯仰力矩系数的权衡。结果表明，冷罩长度和坡道初始膨胀角对SERNs的性能有显著影响。结果表明，整流罩越短，升力越高；初始膨胀角越大，俯仰动量越小。
A 2D hypersonic inlet which can self-start at relay Mach number (Ma=3.5) is designed. Then single- or multi-objective optimization designs of the 2D inlet are carried out on cruise operation point (Ma=7.0) by Sequential Quadratic Programming (SQP), Multi-Island Genetic Algorithm (MIGA), and Multi-Objective Genetic Algorithms (MOGAs), i.e. Neighborhood Cultivation Genetic Algorithm (NCGA) and Nondominated Sorting Genetic Algorithm II (NSGA-II). In these optimizations, the inlet flowfields are calculated with the Single-Sweep Parabolized Navier-Stokes (SSPNS) algorithm codes which are proved highly accurate, highly efficient for supersonic/hypersonic flowfield simulations previously. Singleobjective optimization results show that pressure recovery maximum model is better than effective kinetic energy coefficient maximum model. Multi-objective optimization results reveal the tradeoffs among total pressure recovery, static pressure rise, and drag coefficients. Based on multi-objective design process, a multi-operation-point design and a design point determi-nation process are investigated. Results show if design point is set at cruise point, the off-design operation mass capture coefficients is relatively low; whereas if the design Mach number is 6.5, the 2D inlet will get good overall operation performances along the constant dynamic trajectory. The same optimization design methods are applied to design several 2D Single-Expansion-Ramp Nozzles (SERNs). Result of the single-objective optimization design shows that the objective, i.e. the thrust coefficient, is improved, but the corresponding lift coefficient is relatively low. In the 2- and 3-objective cases, tradeoffs of the thrust coefficient, the lift coefficient and the pitching moment coefficient, are obtained. Results show that cowl length and initial expansion angle of ramp influence the SERNs performance significantly. It is also shown that the shorter the cowl is, the higher the lift is; whereas the larger the initial expansion angle is, the smaller the pitching momentum is.