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乘波构型是高超声速飞行器高升阻比气动布局设计的参考外形之一,设计中需要综合考虑升阻比、容积率和容积等要求。在锥导乘波构型参数化设计的基础上,采用工程估算和计算流体力学相结合的方法,通过正交试验设计分析了不同参数对目标影响的敏感性,合理选择设计参数优化区间,应用改进的多目标遗传算法对乘波构型进行了优化设计,针对优化外形开展了气动性能的数值模拟研究,并在高超声速炮风洞中完成了缩比模型的验证性实验。结果表明:优化设计外形具有良好的升阻比,且在一定攻角范围内升阻比较高,数值模拟和实验分析基本吻合。研究结果可为高超声速滑翔式飞行器的设计提供参考。
Waveform configuration is one of the reference designs of hypersonic vehicle's high lift-to-drag ratio pneumatic layout design. The design needs to consider the requirements of lift-drag ratio, volume ratio and volume. Based on the parametric design of conic guided multipulse structure, the sensitivity of different parameters to the target is analyzed by orthogonal experimental design based on the combination of engineering estimation and computational fluid dynamics, the rational selection of design parameters is optimized, The improved multi-objective genetic algorithm (GA) is used to optimize the design of the multiplicative wave. The aerodynamic performance of the multi-objective genetic algorithm is optimized and the numerical simulation of the aerodynamic performance is carried out. The confirmatory experiment of the scaling model is completed in the hypersonic gun-hole. The results show that the optimized design shape has a good lift-drag ratio, and the resistance is very high at a certain range of angle of attack. The numerical simulation and experimental analysis are in good agreement. The results can provide reference for the design of hypersonic gliding aircraft.