超低轨道卫星气动特性分析与优化设计  

ANALYSIS AND OPTIMIZATION OF AERODYNAMIC CHARACTERISTICS FOR VERY LOW EARTH ORBIT SATELLITES

作　　者：蒋亦凡 李帅辉[2] 李志辉[3] 张俊[1] Jiang Yifan;Li Shuaihui;Li Zhihui;Zhang Jun(School of Aeronautic Science and Engineering,Beihang University,Beijing 100191,China;State Key Laboratory of High Temperature Gas Dynamics,Institute of Mechanics,Chinese Academy of Sciences,Beijing 100190,China;China Aerodynamics Research and Development Center,Mianyang 621000,Sichuan,China)

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191 [2]中国科学院力学研究所高温气体动力学国家重点实验室,北京100190 [3]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《力学学报》2025年第3期616-626,共11页Chinese Journal of Theoretical and Applied Mechanics

基　　金：国家自然科学基金资助项目(92371102和12272028).

摘　　要：超低地球轨道(VLEO)卫星在提升对地观测平台性能和降低观测成本方面具有显著优势.然而,在超低轨道环境下,大气分子与卫星表面碰撞所产生的气动阻力与气动热载荷给卫星的在轨运行寿命和安全带来了巨大挑战不可忽视.首先采用直接模拟蒙特卡洛(DSMC)方法,对100~300 km高度范围内超低轨卫星的气动阻力、气动力矩与气动热特性进行了分析,系统研究了轨道高度、表面适应系数和飞行迎角等条件对卫星气动力和气动热特性的影响规律.随后,基于平板外形与旋成体外形的减阻优化分析,提出了两种超低轨卫星减阻优化方案,分别为基于表面特性的侧面光滑设计与基于遗传算法的头部外形优化.通过DSMC计算评估了两种优化方案的可行性,结果表明,在100 km的轨道高度下,侧面光滑设计的减阻效果可达40%,头部外形优化的减阻效果可达26%.两种优化方案均有效降低了超低轨卫星的气动阻力,对超低轨卫星的气动优化设计具有重要的参考和指导意义.There are significant advantages in enhancing the performance of Earth observation platforms and reducing observation costs for very low Earth orbit(VLEO)satellites.However,in the VLEO environment,the aerodynamic drag and aerodynamic thermal load caused by collisions between atmospheric molecules and the satellite surface cannot be ignored,posing substantial challenges to the satellite's on-orbit lifespan and safety.This paper first employs the direct simulation Monte Carlo(DSMC)method to analyze the aerodynamic drag,aerodynamic moments,and aerodynamic thermal characteristics of VLEO satellites within an orbit altitude range of 100 to 300 km,systematically studying the effects of orbital altitude,surface accommodation coefficients,and flight angle of attack on the satellite's aerodynamic performance.Subsequently,based on drag reduction optimization analyses for flat plate and conical shapes,two optimization designs for VLEO satellites,referred to as lateral side smoothing design based on surface characteristics and head shape optimization using genetic algorithm,are proposed.The feasibility of these two optimization designs is evaluated by DSMC calculations.The results indicate that at an altitude of 100 km,the lateral side smoothing design achieves a drag reduction of up to 40%,while the head shape optimization yields a reduction of 26%.Both of two optimization designs effectively reduce the aerodynamic drag of VLEO satellites,providing significant references and guidance for aerodynamic optimization design of VLEO satellites.

关 键 词：超低地球轨道 卫星 气动 直接模拟蒙特卡洛 减阻优化 

分 类 号：V211.25[航空宇航科学与技术—航空宇航推进理论与工程]