高超声速ISR平台乘波外形优化设计及需求验证

Optimization Design and Requirement Verification of Waverider Based Hypersonic ISR Vehicle Configuration

对乘波构型在高超声速ISR平台气动外形设计上的应用问题进行了研究。基于高超声速ISR平台的总体参数,对锥导乘波体进行了参数化几何建模。以升阻比和容积率为优化目标,采用正交试验设计方法、非线性回归模型和粒子群算法对锥导乘波体进行了多目标优化设计。选取Pareto前沿中的4个特征点作为高超声速ISR平台的初步气动外形,采用数值计算方法对其进行了性能分析,并对设计需求进行了初步验证。研究结果表明:上下表面"双凸"、两侧近似机翼的乘波体在保持较高升阻比的同时又具有较大的容积率,满足航程、载荷和起飞重量等设计指标的需求,可用于高超声速ISR平台气动外形设计。由于航程指标值较大,对燃油结构质量比的要求较高。

In this paper, the application of cone-derived waverider to the configuration design of hypersonic ISR vehicle was studied. Based on the overall parameters of hypersonic ISR vehicle, cone-derived waverider was modeled by parametric method. The orthogonal experimental design method was introduced to analyze each design parameter effect on the waverider performance, the nonlinear models between performance and 3 design parameters were established by using regression analysis, lift-to-drag ratio and volumetric efficiency were chosen as the optimization objective. Multi-object particle swarm optimization algorithm was adopted to optimize the waverider. Four typical cases from pareto front were chosen as the preliminary aerodynamic shape of hypersonic ISR vehicle. CFD was used to analyze the aerodynamic performance of these waveriders. According to the numerical results, design requirement of hypersonic ISR vehicle was verified preliminary. The results shows that the waverder designed in this paper can be used as aerodynamic shape for hypersonic ISR vehicle, the value of lift-to-drag ratio and volumetric efficiency can meet the need of range, load and takeoff weight mainly,but the fuel-structure mass ratio must exceed 0.7.