吸气式空空导弹外形多学科一体化优化设计

doi:10.7527/S1000-6893.2015.0206

Abstract

Abstract:

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.

Key words: airbreathing air-to-air missile, multidisciplinary, integrated design optimization, aerodynamic surrogate model, thrust-drag match

CLC Number:

WANG Rong, ZHANG Hongjun, WANG Guidong, CHEN Guangqiang, BAI Peng, ZHANG Zhenming, LI Xiaodong, FU Jianming. Multidisciplinary integrated design optimization for an airbreathing air-to-air missile shape[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(1): 207-215.

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

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