Ejection Separation Characteristic Analysis of Parachute Container Cover from Return Capsule for Lunar Exploration  

作　　者：高树义 王海涛 程文科 荣伟 贾贺 江长虹 

机构地区：[1]Northwestern Polytechnical University [2]Beijing Institute of Space Mechanics & Electricity [3]National University of Defense Technology

出　　处：《Transactions of Nanjing University of Aeronautics and Astronautics》2014年第5期552-558,共7页南京航空航天大学学报（英文版）

基　　金：Supported by the Aeronautical Science Foundation of China(2012ZC52035)

摘　　要：The parachute container cover ejection separation is the first and foremost motion for the return capsule recovery system,which is related to the success of a recovery system.Adopting the computational fluid dynamics(CFD)simulation and flight dynamics coupling method,the parachute container cover ejection separation is simulated.The rationality of the ejection separation speed and dynamic characteristics of the separation process is analyzed.Meanwhile,the influences of angle of attack,Mach number and ejection separation speed on the parachute container cover ejection are also investigated.Results show that the ejection separation speed design is reasonable.It has a certain design margin for parachute container cover to escape from the wake region,and to pull out the drag parachute completely.The results may provide a theoretical basis for recovery system engineering design of the lunar exploration project.The parachute container cover ejection separation is the first and foremost motion for the return capsule recovery system, which is related to the success of a recovery system. Adopting the computational fluid dynamics （CFD） simulation and flight dynamics coupling method, the parachute container cover ejection separation is simu lated. The rationality of the ejection separation speed and dynamic characteristics of the separation process is ana- lyzed. Meanwhile, the influences of angle of attack, Mach number and ejection separation speed on the parachute container cover ejection are also investigated. Results show that the ejection separation speed design is reasonable. It has a certain design margin for parachute container cover to escape from the wake region, and to pull out the drag parachute completely. The results may provide a theoretical basis for recovery system engineering design of the lunar exploration project.

关 键 词：lunar sample return recovery system ejection separation computational fluid dynamics(CFD) 

分 类 号：V215.2[航空宇航科学与技术—航空宇航推进理论与工程]