摘要
分析了基于响应面近似模型的并行子空间方法CSSO/RSA的执行步骤和特点,并介绍了逐步逼近响应面近似模型的构建方法。给出了包含气动、弹道、发动机3个耦合学科的整体式冲压发动机飞航导弹的学科分析模型和系统优化模型,分别采用CSSO/RSA方法和单级多学科优化方法对飞航导弹进行优化设计。结果表明CSSO/RSA方法的性能要优于单级多学科优化方法。
Concurrent Subspace Optimization (CSSO) method performs better than single-level Multidisciplinary Design Optimization (MDO) method in some test problems, but these test problems are not complex enough. Our aim is to see whether or not CSSO/RSA, a special form of CSSO based on RSA (Response Surface Approximation) performs better in the design of integral rocket-ramjet cruise missile. In the full paper, we explain in much detail how to use CSSO/RSA to design integral rocket-ramjet cruise missile; here we give only a briefing. CSSO/RSA utilizes some parameters obtained from RSA model and can exploit the optimization capabilities of disciplines to improve the system level optimization result. Discipline optimization processes, which can be executed concurrently, avoid multidisciplinary analysis which cost most of computational time during MDO process. So, compared to single-level method, CSSO/ RSA method can improve the design optimization result and reduce computation time. We obtained design optimization results with both CSSO/RSA method and single-level MDO method. For CSSO/RSA method, the improvement in design optimization was 4.34% and the computation time was 1.25 h; for single-level MDO method, the improvement in design optimization was 3.47% and the computation time was 1.50 h. These results show preliminarily that CSSO/RSA method is better than single-level MDO method in the design of integral rocket-ramjet cruise missile.
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
2005年第3期392-395,共4页
Journal of Northwestern Polytechnical University
基金
西北工业大学博士论文创新基金(CX200404)
国家863计划项目(2003AA721052)
航天基金资助项目
关键词
飞航导弹
并行子空间优化
响应面近似
Approximation theory
Costs
Improvement
Mathematical models
Optimization
Ramjet engines
Rockets
Structural design
