着陆器的着陆过程羽流特性模拟系统
By designing a combination of suspension subsystem, attitude adjustment subsystem and measurement subsystem, the plume characteristics of a high-thrust engine in a vacuum environment were simulated, solving the problem of lack of measurement of the force and heat effects of the plume of a high-thrust engine in the existing technology, and improving the verification capability of ground test.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- BEIJING INST OF SPACECRAFT ENVIRONMENT ENG
- Filing Date
- 2024-06-05
- Publication Date
- 2026-07-17
AI Technical Summary
Existing technologies lack systems capable of measuring and simulating the plume thermal effects of high-thrust engines in a vacuum environment, especially during lunar landing, and particularly for simulating plume characteristics under dynamic conditions.
A landing process plume characteristic simulation system was designed, comprising a suspension subsystem, an attitude adjustment subsystem, a measurement subsystem, and a control subsystem. The suspension subsystem mounts the lander and responds to the ignition command of the control subsystem. The attitude adjustment subsystem adjusts the position of the lunar surface simulation tester. The measurement subsystem measures the plume's mechanical and thermal parameters. The control subsystem coordinates the operation of each system to achieve plume characteristic simulation under static and dynamic conditions.
It enables the simulation of plume characteristics of the lander under various attitudes, improves the verification capability of ground tests, is applicable to plume tests on the lunar surface and other extraterrestrial bodies, and features high safety and large range of motion.
Smart Images
Figure CN118651443B_ABST