196
5 Thermal Control Technology of Lunar Lander
During landing process and operation on lunar surface, a great many temperature
data and changes of key products such as VCHP, high-temperature heat shield, twophase fluid loops, RHUs and different parts of the lunar lander were obtained. With
these data, the rules and actual effects of environmental conditions such as engine
plume, lunar dust deposition and 1/6 g of lunar gravity on lunar surface could be
analyzed. These data and analysis results were important for further exploration of
the Moon and other celestial bodies.
5.7 Summary
Compared with spacecraft on Earth and circumlunar orbit, the lunar lander should
pass special environment on lunar surface. There were technical challenges in development of thermal control including design principles of thermal control, thermal
analysis and calculation, thermal balance test and new thermal materials. On the
basis of successful experiences of spacecraft on Earth and circumlunar orbit, it
was necessary to study innovative technology and products such as VCHP, high
temperature protection of the engine, application of RHU, controlled fluid loop
to develop design and ground test method of thermal control. In this chapter, the
design constraints, design principles and methods, typical thermal control technology, ground test methods and flight results on orbit of thermal control of the
Chang’E-3 lunar lander are described. The thermal control technology was verified
through the development and verification on orbit of the Chang’E-3 lunar lander.
According to the strategic plan of CLEP, robotic sample and return mission was
under development and subsequent manned lunar missions and lunar base construction would be implemented. Further study shall be conducted including high-power
and adaptable fluid loop, VCHP, loop heat pipe, new thermal radiator and lunar dust
prevention and etc., which can provide necessary support for further lunar exploration
missions and other space exploration missions.
References
1. Ouyang Z (2005) Introduction to lunar science. China Astronautic Publishing House, Beijing
2. Liu Z, Xiang Y, Si D, et al (2014) Design and verification of thermal control system for
Chang’E-3 probe. Sci Sin Tech 44:353–360
3. Gaier JR, Siamidis J, Panko SR, et al (2008) The effect of simulated lunar dust on the absorptivity, emissivity, and operating temperature on AZ-93 and Ag/FEP thermal control surfaces.
NASA/TM-2008-215492
4. Agui JH, Nakagawa M (2005) Dust on the Moon and Mars. AIAA 2005-539
5. Gaier JR, Jaworske DA (2007) Lunar dust on heat rejection system surfaces: problems and
prospects. NASA/TM-2007-214814
6. Stephan RA (2011) Overview of the Altair lunar lander thermal control system design and the
impacts of global access. AIAA 2011–5001
5 Thermal Control Technology of Lunar Lander
During landing process and operation on lunar surface, a great many temperature
data and changes of key products such as VCHP, high-temperature heat shield, twophase fluid loops, RHUs and different parts of the lunar lander were obtained. With
these data, the rules and actual effects of environmental conditions such as engine
plume, lunar dust deposition and 1/6 g of lunar gravity on lunar surface could be
analyzed. These data and analysis results were important for further exploration of
the Moon and other celestial bodies.
5.7 Summary
Compared with spacecraft on Earth and circumlunar orbit, the lunar lander should
pass special environment on lunar surface. There were technical challenges in development of thermal control including design principles of thermal control, thermal
analysis and calculation, thermal balance test and new thermal materials. On the
basis of successful experiences of spacecraft on Earth and circumlunar orbit, it
was necessary to study innovative technology and products such as VCHP, high
temperature protection of the engine, application of RHU, controlled fluid loop
to develop design and ground test method of thermal control. In this chapter, the
design constraints, design principles and methods, typical thermal control technology, ground test methods and flight results on orbit of thermal control of the
Chang’E-3 lunar lander are described. The thermal control technology was verified
through the development and verification on orbit of the Chang’E-3 lunar lander.
According to the strategic plan of CLEP, robotic sample and return mission was
under development and subsequent manned lunar missions and lunar base construction would be implemented. Further study shall be conducted including high-power
and adaptable fluid loop, VCHP, loop heat pipe, new thermal radiator and lunar dust
prevention and etc., which can provide necessary support for further lunar exploration
missions and other space exploration missions.
References
1. Ouyang Z (2005) Introduction to lunar science. China Astronautic Publishing House, Beijing
2. Liu Z, Xiang Y, Si D, et al (2014) Design and verification of thermal control system for
Chang’E-3 probe. Sci Sin Tech 44:353–360
3. Gaier JR, Siamidis J, Panko SR, et al (2008) The effect of simulated lunar dust on the absorptivity, emissivity, and operating temperature on AZ-93 and Ag/FEP thermal control surfaces.
NASA/TM-2008-215492
4. Agui JH, Nakagawa M (2005) Dust on the Moon and Mars. AIAA 2005-539
5. Gaier JR, Jaworske DA (2007) Lunar dust on heat rejection system surfaces: problems and
prospects. NASA/TM-2007-214814
6. Stephan RA (2011) Overview of the Altair lunar lander thermal control system design and the
impacts of global access. AIAA 2011–5001