火星探测器降落伞拉直过程中的“绳帆”现象研究  

Study on Line Sail During Mars Probe Parachute Deployment

作　　者：鲁媛媛[1] 荣伟[1] 吴世通[1] 

机构地区：[1]北京空间机电研究所,北京100094

出　　处：《宇航学报》2014年第11期1238-1244,共7页Journal of Astronautics

摘　　要：针对火星探测器降落伞在拉直过程中出现的"绳帆"现象,以及火星探测器降落伞开伞前初始参数和大气密度与地球环境下的差异,建立了火星探测器降落伞拉直过程的数学模型,研究了火星环境下,伞包弹射速度、开伞前进入器的攻角、开伞马赫数以及大气密度对"绳帆"现象的影响。研究结果表明,选择较大的伞包弹射速度,并将开伞前进入器的攻角严格限定在较小范围内,将有利于避免或降低"绳帆"现象的发生。这一研究结果可为我国实施火星探测时减速着陆系统的设计分析提供一定参考。For the line sail phenomena during Mars probe parachute deploying,and the differences in initial parameters of deployment atmospheric density between Mars environment and Earth environment,a dynamics model is developed to study the deployment process of Mars probe parachute. The parachute bag is treated as a variable mass 6-DOF rigid. The probe is treated as a 6-DOF rigid. The parachute system is treated as a mass-spring-damper model. The effects of parachute＇s ejection velocity,angle of attack of entry vehicle,Mach number and atmospheric density on line sail are studied under Mars environment. The research result shows that taking great parachute ejection velocity and small angle of attack of entry vehicle are propitious to avoid or decrease the line sail phenomena. The study provides a reference for descent and landing system design of Mars probe in China.

关 键 词：火星探测器 降落伞拉直 绳帆 伞包弹射速度 攻角 开伞马赫数 

分 类 号：V412.44[航空宇航科学与技术—航空宇航推进理论与工程]