サブオービタル有翼ロケットの概念設計最適化問題における初期解生成法

抄録

Kyushu Institute of Technology has been developing experimental winged rocket for fully reusable space transportation system since 2005. For the conceptual design of the suborbital winged rocket, it is necessary to solve the coupled design problem of the vehicle sizing and flight trajectory. Therefore, multidisciplinary design optimization for the system composed of several design disciplines using an efficient gradient-based optimizer is useful. Using the gradient-based method, however, the converged solution and the computation time highly depend on the initial solution supplied by the user, and its appropriate design requires experiences. In this paper, a methodology for automatically generating initial solutions is developed. A set of problems starting from a simplified one to an increasingly complicated one is solved, and the solution obtained is used as an initial solution in the succeeding problem. Its validity is demonstrated by designing a suborbital winged rocket that carries 100 kg payload up to 120 km altitude.