吸气式空空导弹外形多学科一体化优化设计

针对采用整体式固冲发动机的吸气式空空导弹外形气动与推进耦合的推阻匹配设计难题,引入多学科优化设计方法提出了一种综合考虑气动/推进/质量/弹道的导弹外形多学科一体化优化设计技术。其中,气动性能预测采用代理模型技术,主要基于外形参数化建模、非结构网格技术和流场精细数值计算来自动构建气动数据库,据此建立了包含外形几何信息的气动预测代理模型,并对其预测精度进行了验证;推进性能预测采用推进求解模型,该模型根据固冲发动机理论建立,精度满足工程要求。对所建立的学科预测模型完成一体化集成后,以质点弹道仿真评估的战技指标为优化目标,对一款吸气式空空导弹进气道和翼面外形进行了优化设计,取得了推阻匹配的优化外形,优化后导弹动力射程提高10%。所提出的一体化优化设计技术,有助于吸气式空空导弹外形气动与推进耦合推阻匹配设计和提高导弹动力射程。

Multidisciplinary integrated design optimization for an airbreathing air-to-air missile shape

It is challenging for aerodynamic configuration design of an airbreathing air-to-air missile using integrated solid ramjet rocket motor,which is difficult to solve aerodynamic and propellant interaction.In this paper,multidisciplinary integrated design optimization method is introduced to solve the problem.The disciplines include aerodynamics/propulsion/weight/trajectory.Aerodynamic forces are carried through the surrogate models,which are created from aerodynamic database constructed automatically by the techniques of parametric geometric modeling,unstructured grid and CFD.Propulsion characteristics are evaluated by an engineering method,which is developed according to solid ramjet rocket propulsion theory.The accuracy of aerodynamic surrogate model and propulsion engineering method are validated before being used,and both of them are acceptable.The trajectory path is gained from 3-DOF point mass simulation.After the integration of above disciplines,inlet and wing shape of an airbreathing air-to-air missile are designed by multidisciplinary integrated design optimization method.The objective of missile dynamic range is improved by 10% after design optimization,which shows good thrust-drag match.The proposed method is useful to solve aerodynamic and propellant interaction for similar airbreathing missile shape design.