CAJ | 학술논문

研究高速巡航导弹动力装置优化问题,针对进气道结构严重影响速度的提高,为减少人工建模的工作量,以提高数值仿真分析工作效率和满足二元超声速进气道设计方案的快速评比和选型的需要,提出建立流场计算域通用的结构化分区几何模型,统一基于所构造的基准进气道模型,一次性人工划分进气道结构化计算网格,根据边界几何控制,运用网格映射和比例变换方法,编程自动化实现由基准进气道计算网格映射生成实际结构不同的系列化二元进气道计算网格.用建立的模型进行仿真.结果证明,减少了建模工作量和提高了工作效率.
연구고속순항도탄동력장치우화문제,침대진기도결구엄중영향속도적제고,위감소인공건모적공작량,이제고수치방진분석공작효솔화만족이원초성속진기도설계방안적쾌속평비화선형적수요,제출건립류장계산역통용적결구화분구궤하모형,통일기우소구조적기준진기도모형,일차성인공화분진기도결구화계산망격,근거변계궤하공제,운용망격영사화비례변환방법,편정자동화실현유기준진기도계산망격영사생성실제결구불동적계렬화이원진기도계산망격.용건립적모형진행방진.결과증명,감소료건모공작량화제고료공작효솔.
To reduce modeling workload,improve the efficiency of numerical simulation,and meet the needs for fast design evaluation and selection,a general geometric model of structural computational domain partition for 2-Dsupersonic inlet flow field is constructed.Based on baseline inlet,structural grids are created.Then,based on boundary geometric control,a serial of inlet computational grids with different structures are generated automatically from baseline grid by programming using grid mapping and proportional transformation techniques.This changes the method that every design scheme requires manual modeling.reduces modeling workload and improves efficiency remarkably.