514
15 System Testing and Validation Technology of Lunar Lander
Test article
fixing tool
Vacuum pump
system
Engine
Propellant supply system
Measurement
subsystem
Vacuum measurment
subsystem
3D moving
mechanism
3D moving control system
Heatflow
meter
Test article
E-4
E-5
Liquid nitrogen supply system
Fig. 15.18 Configuration of test system for plume effect on thermal control
3. Engine
The engine should be flight model. When the engine was installed, the engine vector
line should be perpendicular to the tested surface of test article (installation surface).
The axis of the engine nozzle was coaxial with the axis of the heat flow meter
installation tool.
4. Test Article with Thermal Control Material
The test article was the thermal control coating material used in the landing gears,
bottom plate and protrusion instrument on bottom plate.
5. Parameter Measurement Subsystem
The test parameter measurement subsystem was applied to measure and acquire data
of heat flux and temperature in the test, which was composed of heat flow sensor,
pressure sensor, thermocouple, vacuum gauge and resistance gauge.