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6 Power Technology of Lunar Lander
low resource consumption and to minimize the complexity of interface for tests and
reduce mass of test interface as much as possible.
Following principles should be followed when the power system was designed.
(1) Miniaturization
The mass constraint of the lunar lander was very strict. On the basis of guaranteeing
reliability, comprehensive measures should be taken including instrument function
integration, components selection, housing material selection, housing design, selection of internal and external connectors, and wire selection to achieve miniaturization,
so as to improve specific power of power system as much as possible.
(2) Integration of inheritance and advancement
The power system of the lunar lander should fully inherit power supply technology of
previous spacecraft, especially mature experience of the Chang’E lunar probes and
Shenzhou spacecraft. At the same time, it was necessary to research key technologies. The system requirements could be satisfied by three aspects including system
optimization, high specific energy and high specific power products, high integration
and lightweight design. For the research products of key technology, ground simulation analysis and test verification should be strengthened as well as risk analysis
and control to ensure that the product design could satisfy the mission requirements
reliably and reasonably.
6.4.2 Illumination Conditions
Analysis of illumination condition was the basis of power system design [8]. For
the lunar lander, the analysis of illumination included analysis of LTO, initialization
process after landing and operation on lunar surface.
1. Illumination During Flight
During flight phases before the lunar lander was landed, the solar array was always
toward the Sun. The incident angle of solar array depended on the accuracy of attitude
control of the lunar lander. During launch, orbit change and powered descent, the
solar array was unfolded and did not generate electricity. In circumlunar orbit, the
lunar lander would pass alternation process of light/shadow. For example, analysis
of illumination conditions is described as follows.
(1) Launch
The solar array was unfolded before launch and deployed till the lunar lander was
separated with launch vehicle, when there was no power generated and the lunar
lander was fully powered by the battery packs. The battery packs of the lunar rover
could power the lunar lander jointly.
(2) LTO
6 Power Technology of Lunar Lander
low resource consumption and to minimize the complexity of interface for tests and
reduce mass of test interface as much as possible.
Following principles should be followed when the power system was designed.
(1) Miniaturization
The mass constraint of the lunar lander was very strict. On the basis of guaranteeing
reliability, comprehensive measures should be taken including instrument function
integration, components selection, housing material selection, housing design, selection of internal and external connectors, and wire selection to achieve miniaturization,
so as to improve specific power of power system as much as possible.
(2) Integration of inheritance and advancement
The power system of the lunar lander should fully inherit power supply technology of
previous spacecraft, especially mature experience of the Chang’E lunar probes and
Shenzhou spacecraft. At the same time, it was necessary to research key technologies. The system requirements could be satisfied by three aspects including system
optimization, high specific energy and high specific power products, high integration
and lightweight design. For the research products of key technology, ground simulation analysis and test verification should be strengthened as well as risk analysis
and control to ensure that the product design could satisfy the mission requirements
reliably and reasonably.
6.4.2 Illumination Conditions
Analysis of illumination condition was the basis of power system design [8]. For
the lunar lander, the analysis of illumination included analysis of LTO, initialization
process after landing and operation on lunar surface.
1. Illumination During Flight
During flight phases before the lunar lander was landed, the solar array was always
toward the Sun. The incident angle of solar array depended on the accuracy of attitude
control of the lunar lander. During launch, orbit change and powered descent, the
solar array was unfolded and did not generate electricity. In circumlunar orbit, the
lunar lander would pass alternation process of light/shadow. For example, analysis
of illumination conditions is described as follows.
(1) Launch
The solar array was unfolded before launch and deployed till the lunar lander was
separated with launch vehicle, when there was no power generated and the lunar
lander was fully powered by the battery packs. The battery packs of the lunar rover
could power the lunar lander jointly.
(2) LTO