中国空间科学技术2024，Vol.44Issue(3)：120-126,7.DOI:10.16708/j.cnki.1000-758X.2024.0045
超低轨飞行器迎风面减阻构型优化研究
Optimization of drag reduction configuration on windward side of very low orbit spacecraft
摘要
Abstract
Aiming at the problem that the windward side of very low orbit spacecraft is subjected to too much aerodynamic resistance,based on the theoretical solution to the aerodynamic drag of free molecular flow,the aerodynamic resistance of several typical windward side configurations with different length was calculated and the reasons for their changes were analyzed.After which an expression of the windward side was designed and an intelligent algorithm was introduced to iteratively optimize it.Given the constraints of the configuration,the penalty function was introduced to reduce the fitness of the infeasible solution.The results show that this method can obtain the approximate optimal solution of the windward side with minimum resistance.Under the constraints of existing materials,the maximum drag reduction of this method can be more than 5％compared with the conical structure,and the head volume of the spacecraft can be effectively increased.With the increase of windward height,the minimum resistance configuration gradually changes from near frustum to cone.The optimization method proposed in this paper can provide a reference for subsequent drag-reducing configuration design of very low orbit spacecraft.关键词
超低轨飞行器/稀薄气体/Boltzmann方程/PSO算法/罚函数/减阻构型Key words
very low orbit spacecraft/rarefied gas/Boltzmann equation/PSO algorithm/penalty function/drag reduction configuration分类
航空航天引用本文复制引用
江一鹏,崔玉福,刘质加,秦江..超低轨飞行器迎风面减阻构型优化研究[J].中国空间科学技术,2024,44(3):120-126,7.基金项目
国家自然科学基金(52075043) （52075043）
