The main purpose of this paper is to study the application of cone - derived waverider to the configuration design of hypersonic cruise missile. Using the upper base line of waverider as parametric modeling object, orthogonal experimental design 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, then multi - object genetic algorithm was adopted to optimize the waverider. Using the optimized waverider as the configuration of hypersonic cruise missile, CFD was used to analyze the aerodynamic performance of the missile. The results show that hypersonic cruise missile configuration based on cone -derived waverider has excellent geometry capability and aerodynamic performance, the volumetric efficiency is more than 0.34, the lift - to - drag ratio is only a little below 6. Parametric design method can control the waverider configuration conveniently based on its application object, which makes waverider closer to application. the veracity of regression model is very good, the precision of CFD is very high, these models and methods can be used to the conceptual and preliminary design of hypersonic cruise missile. The result can be useful in the configuration design of hypersonic cruise missile.%对锥导乘波构型在高超声速巡航导弹气动外形设计上的应用问题进行了研究.以乘波体上表面底部基线为参数化几何建模对象,运用正交试验设计方法,分析了不同设计参数对乘波体几何性能和气动性能的影响.采用回归分析法建立了乘波体容积率和升阻比与设计参数之间的非线性数学模型,然后应用多目标遗传算法对乘波构型进行了优化设计.将优化后的乘波体作为高超声速巡航导弹的初步外形并对其气动性能进行f数值模拟分析.结果表明:以锥导乘波体为基础生成的高超声速巡航导弹初步外形其有良好的几何性能和气动性能,容积率大于0.42,升阻比接近6;参数化设计方法可根据应用对象来方便地控制乘波体的外形尺寸,大大提高了乘波体的适用性;通过回归分析建立的数学模型准确性好,数值模拟精度高,这些方法可以用于高超声速巡航导弹的总体概念设计和初步设计.
展开▼
