| 摘要: |
| 以某型发动机喷管为研究对象,在iSIGHT软件平台上利用单级优化算法对其进行多学科设计优化,目标为权衡喷管推力和质量的综合改善。采用了较为稳健的组合优化策略,依次进行试验设计、全局探索和局部寻优。优化目标函数是通过对多个优化目标的线性加权平均获得的。改进的计算结果表明了MDO在喷管设计中的可行性和实用性。 |
| 关键词: 液体推进剂火箭发动机 喷管 多目标优化+ 最优设计 |
| DOI： |
| 分类号:V231 |
| 基金项目: |
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| An MDO approach for engine nozzle design |
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FANG Jie,TONG Xiao-yan,MAO Xiao-fang,CAI Guo-biao
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1.School of Astronautics, Beijing Univ.of Aeronautics and Astronautics, Beijing 100083, China;2.Beijing Inst. of Control Engineering, Beijing 100080, China
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| Abstract: |
| A multidisciplinary design optimization (MDO) approach is developed and applied to engine nozzle design based on integrated simulation with multi-criteria trade off analysis about nozzle thrust and mass.A robust interdigitation design methodology combining design of experiments and multiple optimization algorithms embodied in iSIGHT software is investigated sequentially during the design optimization process.The linear weighted multi-objective optimization models with various design variables and constraints are set up.The results show significant improvements.It demonstrates the feasibility and applicability of the MDO approach for nozzle design. |
| Key words: Liquid propellant rocket engine Nozzle Multi-objective optimization~+ Optimum design |
