Multidisciplinary design optimization of space plane considering rigid body characteristics

作     者：Yokoyama, Nobuhiro Suzuki, Shinji Tsuchiya, Takeshi Kanda, Takeshi 

作者机构：Univ Tokyo Operat & Safety Technol Team Tokyo 1138656 Japan Univ Tokyo Dept Aeronaut & Astronaut Bunkyo Ku Tokyo 1138656 Japan Japan Aerosp Explorat Agcy Combined Prop Res Grp Kakuda Miyagi 9811525 Japan 

出 版 物：《JOURNAL OF SPACECRAFT AND ROCKETS》 (航天器与火箭杂志)

年 卷 期：2007年第44卷第1期

页      面：121-131页

核心收录：

学科分类：08[工学] 0825[工学-航空宇航科学与技术] 

基　　金：Japan Society for the Promotion of Science  JSPS 

主　　题：MDO Aerodynamic Characteristics Nonlinear Programming Airframes Pressure Coefficient Single Stage to Orbit Lift Coefficient Internal Pressure Propellant Structural Analysis 

摘      要：Multidisciplinary design optimization is an important approach for the conceptual design of space planes because these planes are characterized by disciplines that interact with one another. A multidisciplinary design optimization problem of a single-stage-to-orbit space,plane is formulated and solved in this study. The modeling and optimization of rigid body characteristics, such as trim and stability, are focused on because a single-stage-to-orbit space plane has a tendency for considerable shift of both the aerodynamic center and the center of gravity. Moreover, the design of the air -breathing engines are integrated with the airframe and its effect on the rigid body characteristics are also modeled in the framework of multidisciplinary design optimization. Using the all-at-once-based multidisciplinary design optimization approach, which incorporates sparse nonlinear programming and metamodeling, the design of the vehicle and its flight trajectory are successfully optimized. Finally, the characteristics of the optimal solution are investigated, especially the relationships among the airframe-engine integration, rigid body characteristics, and payload transportation capability.