摘要
针对亚轨道运载器总体设计多学科耦合的特点,从任务规划、学科建模、集成和求解策略等方面对多学科优化方法进行了研究。以助推亚轨道飞行器为对象,确定了学科模块组成、功能和数据耦合关系。建立了与总体设计过程相适应的7个学科模型,包括几何主模型、气动、推进、弹道、气动热、传热/热防护系统、结构。结合飞行器任务要求和基准方案,从系统级定义了多学科优化问题,包括目标函数、约束条件和设计变量。基于多学科软件框架集成学科模型,采用多学科可行法作为求解框架,建立了亚轨道飞行器多学科优化系统,选择SQP算法完成了以起飞总重为目标的优化。结果显示,优化后,发动机结构、热防护系统有所增加,但结构质量和燃油消耗减小,综合作用使总重减小2.4%,体现了多学科优化的协同作用。
In order to figure out tight-coupling overall design problem of Suborbital Reusable Launch Vehicle （ SRLV）, the crucial technologies of Multidisciplinary Design Optimization （MDO） were investigated, namely task planning, discipline modeling, integration and solving strategy. A SRLV concept serving as the booster of orbital vehicle was selected as the baseline. First, the overall design task of SRLV was decomposed into seven disciplinary components including geometry, aerodynamics, structure, propulsion, trajectory, aero-heating, and thermal conduction/TPS design. The functions of disciplines and dataflow between them were defined. Then, the computational models of these disciplines were established, which met the requirements of overall design. Based on the task of SRLV, the MDO problems were presented,including objectives, constraints and variables. Within multidisciplinary frame- work software,the architecture of Multi-Disciplinary Feasible （MDF） was created. By integrating seven disciplinary models into MDF architecture,a MDO software system for SRLV overall design was established. Genetic Algorithm was chosen to optimize the take-off weight of SRLV. The obtained results show that the mass of propulsion structure and TPS parts both increase slightly, but the fuel mass and airframe structural mass decrease, and the take-off weight decreases about 2.4%.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2012年第1期5-10,16,共7页
Journal of Solid Rocket Technology
关键词
亚轨道
重复使用运载器
多学科优化
总体设计
suborbital
reusable launch vehicle
muhidisciplinary design optimization
overall design
