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5 Thermal Control Technology of Lunar Lander
technologies such as VCHP, high-temperature thermal shield and two-phase fluid
loop.
5.6.1 Thermal Balance Test of Lunar Lander
The objective of the thermal balance test was to verify design of thermal control
subsystem actual performance of thermal control products by experiments. The
implementation method was to simulate the environmental conditions such as
vacuum, low temperature and typical external heat flow in each phases of the lunar
lander in space environment simulator so as to verify whether the temperature of the
lunar lander components met the requirements under different conditions.
In different phases of development, thermal balance test of probe was generally
classified into thermal balance test in prototype phase and thermal balance test in
flight model phase, where the difference was the state of test articles. In thermal
balance test in prototype phase, the test articles were generally analog articles with
same external dimensions, surface conditions, heat capacity, heat consumption and
operation mode as instruments prototypes. In thermal balance tests of flight model,
the test articles are generally flight models. Considering the capabilities of flight
models such as pressure and heat sink temperature, safety and other special requirements, analog articles with same thermal parameters could be used to simulate individual flight models. But the analog articles should adapt to test conditions such as
temperature, pressure, and duration in thermal balance test.
1. Test Objectives
The major objectives of thermal balance test were as follows:
(1) To obtain temperature distribution data of the lunar lander, and verify the
ability of thermal control subsystem to maintain temperature of instruments
and structure within specification.
(2) To provide ground test data for correction and improvement of thermal analysis
model.
(3) To obtain temperature distribution of instruments in special phases such as
landing, hibernation and awakening, and support for formulation of flight
control strategies.
For the thermal balance test of flight model, the obtained temperature data could also
provide basis for determination of temperature in thermal vacuum test of the lunar
lander.
2. Simulation of Space Thermal Environment
The space environment simulator is used to simulate the vacuum and low background
temperature environment of spacecraft in orbit. Since the effect of heat convection
and conduction of gas is almost negligible when the pressure is less than 10
−2 Pa,
5 Thermal Control Technology of Lunar Lander
technologies such as VCHP, high-temperature thermal shield and two-phase fluid
loop.
5.6.1 Thermal Balance Test of Lunar Lander
The objective of the thermal balance test was to verify design of thermal control
subsystem actual performance of thermal control products by experiments. The
implementation method was to simulate the environmental conditions such as
vacuum, low temperature and typical external heat flow in each phases of the lunar
lander in space environment simulator so as to verify whether the temperature of the
lunar lander components met the requirements under different conditions.
In different phases of development, thermal balance test of probe was generally
classified into thermal balance test in prototype phase and thermal balance test in
flight model phase, where the difference was the state of test articles. In thermal
balance test in prototype phase, the test articles were generally analog articles with
same external dimensions, surface conditions, heat capacity, heat consumption and
operation mode as instruments prototypes. In thermal balance tests of flight model,
the test articles are generally flight models. Considering the capabilities of flight
models such as pressure and heat sink temperature, safety and other special requirements, analog articles with same thermal parameters could be used to simulate individual flight models. But the analog articles should adapt to test conditions such as
temperature, pressure, and duration in thermal balance test.
1. Test Objectives
The major objectives of thermal balance test were as follows:
(1) To obtain temperature distribution data of the lunar lander, and verify the
ability of thermal control subsystem to maintain temperature of instruments
and structure within specification.
(2) To provide ground test data for correction and improvement of thermal analysis
model.
(3) To obtain temperature distribution of instruments in special phases such as
landing, hibernation and awakening, and support for formulation of flight
control strategies.
For the thermal balance test of flight model, the obtained temperature data could also
provide basis for determination of temperature in thermal vacuum test of the lunar
lander.
2. Simulation of Space Thermal Environment
The space environment simulator is used to simulate the vacuum and low background
temperature environment of spacecraft in orbit. Since the effect of heat convection
and conduction of gas is almost negligible when the pressure is less than 10
−2 Pa,