The aerodynamic design of the configuration with modular components is investigated for the multi-mission Unmanned Aerial Vehicle(UAV) performing reconnaissance and strike missions. Based on the internal layout features, the aircraft major components can be divided into three types:common modules, special modules, and general modules. Various module partition methods for the forebody, wing and tail are analyzed, and the best partition methods for special and general modules are chosen according to aerodynamic characteristics. On the basis of the surrogate-based multi-objective optimization platform, module coupling optimization processes are developed in the configuration and component levels. The aerodynamic characteristics of the proposed design is assessed by a comparison with the current typical UAV configurations. The results show that the scheme of shorter length but the same volume is the optimal selection for the forebody of the strike configuration regarded as a special module, the straight wing with inflection leading edge and the sweptback trapezoidal wing are the optimal schemes respectively for the reconnaissance configuration and the strike configuration regarded as general modules, and adjustable shape and variable dihedral angle tail are the optimal scheme for the tail regarded as a general module. Module coupling optimization for general modules can effectively improve the lift-drag ratio of both the reconnaissance and strike configurations, and achieve the best aerodynamic performance of multi-mission UAV.
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