高超声速飞行器尾喷管的优化设计

以喷管上壁折转角、下壁长度、舵面长度及其折转角为设计变量,结合遗传算法和特征线法对高超声速飞行器尾喷管进行了优化设计,并对设计变量进行了参数研究.结果表明,所采用的优化设计方法计算效率高且比较准确,特别适合于高超声速飞行器尾喷管的优化设计;所采用的4个设计参数均能有效地影响尾喷管的气动性能,其中喷管上壁折转角和舵面折转角分别对喷管的升力和推力的影响相对明显,对其进行均衡选择方能得到最优的结果. 

Optimal design of nozzle for hypersonic vehicle

An optimal design procedure was proposed by utilizing the method of characteristics in conjunction with a multi-island genetic algorithm.The reflection angle of the nozzle upper wall,the length of the lower wall,and the flap length and angle were chosen to be the design variables,and a parametric study with respect to these variables was performed.The numerical results demonstrate that the proposed procedure is highly efficient,and capable of providing sufficiently accurate data for nozzle optimal design.It is also found that all four parameters chosen as the design variables will substantially affects the aerodynamic performances of the nozzle,among them,the reflection angle of the nozzle upper wall and the flap have remarkable influence on lift and thrust respectively.Hence,the trade-off among these variables must be taken into account to achieve the optimum result.