The invention provides a landing process plume characteristic simulation system of a lander, which comprises a suspension subsystem, a pose adjustment subsystem, a measurement subsystem and a control subsystem, and is characterized in that the lander and a lunar surface simulation tester are respectively mounted through the suspension subsystem and the pose adjustment subsystem; the lunar surface simulation tester is located under the lander through the coaxiality condition, and the measurement subsystem is used for measuring plume force thermal parameters of fuel gas plume of a lander engine; and the control subsystem is used for sending an ignition instruction to the lander, receiving the plume force thermal parameters and controlling the pose adjusting subsystem to adjust the static working condition position and the dynamic working condition relative movement between the lunar surface simulation tester and the lander. Therefore, plume characteristic simulation under various attitude static working conditions and dynamic working conditions in the lunar surface landing process of the lander can be realized.
本发明提供了一种着陆器的着陆过程羽流特性模拟系统,包括悬吊子系统、位姿调节子系统、测量子系统以及控制子系统,其中,通过悬吊子系统和位姿调节子系统分别安装着陆器和月面模拟试验器,并通过同轴度条件使得月面模拟试验器位于着陆器正下方,测量子系统用于测量着陆器发动机的燃气羽流的羽流力热参数;控制子系统,用于向所述着陆器发送点火指令、接收所述羽流力热参数以及用于控制位姿调节子系统调节所述月面模拟试验器与着陆器之间的静态工况位置和动态工况相对运动。如此,本发明能够实现着陆器着陆月面过程多种姿态静态工况及动态工况下羽流特性模拟。
Landing process plume characteristic simulation system of lander
着陆器的着陆过程羽流特性模拟系统
17.09.2024
Patent
Elektronische Ressource
Chinesisch
IPC: | B64G Raumfahrt , COSMONAUTICS |
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