Abstract: The topology optimization technique is introduced into the frame structure design of monolithic wing of missile for improving the designing quality of missile structure, and a frame structure of missile wing of a missile is optimized. A typical load environment for frame structure of missile wing is constructed with a method of converting aerodynamic load to node load, and the conflict that the element located at a area under design not only participates in load bearing but also is deleted due to optimization is solved. The topologically optimized computer aided engineering (CAE) model can be interpreted as computer aided design (CAD) model which can be redesigned in CAD software directly with CAD-CAE interface technology, and the practicability of topology optimization is improved. By analyzing the empirical and optimized frame models and comparing the mass, strength, deformation and modal of these two models, it is founded that, under the condition of satisfying the structural strength and deformation, the mass of the optimized frame model is reduced by 9.39%, meanwhile the natural frequencies for the first and second bending modes and the natural frequency for the first torsional mode are increased. The proposed method can be seen as supplement and improvement of traditional structure design method of missile wing. Key

Key words: ordnancescienceandtechnology, missilewingframe, topologyoptimization, structuralproperty, light-weight