6.4 Design Methodology
207
After the solar array was deployed, the battery packs of the lunar lander and rover were
charged. The solar array was kept toward the Sun during LTO except period of trajectory correction maneuvers. During trajectory correction maneuvers, the solar array
was unfolded and did not generate electricity, when the lunar lander was powered by
battery packs. After trajectory correction maneuvers, the battery packs were charged.
(3) LOI
When the lunar lander approached the Moon, the LOI was performed to make the
lunar lander captured by Moon gravity. The lunar lander was inserted into a 100 km
altitude LLO. During LOI, the engine was firing to decelerate. The solar array would
be unfolded in advance. After LOI, it would be deployed again. After deployed, the
solar array would enter alternation process of light/shadow. The power would be
provided alternately by the solar array and the battery packs.
(4) 100 km circular LLO
After the lunar lander was inserted into LLO, the light/shadows alternated in a 2 h
cycle. The solar array and the battery pack would alternately power the lunar lander,
when the battery packs were charged and discharged alternately. The time of the
lunar lander in 100 km LLO was about 5 days.
(5) Orbit change on LLO
Five days after LOI, the lunar lander was inserted into a 100 km × 15 km elliptical
lunar low orbit. Before the engine was firing, the solar array would be folded in
advance. After orbit change, it would be deployed again. Then the solar array would
enter alternation process of light/shadow and the power would be provided alternately
by the solar array and the battery packs.
(6) 100 km × 15 km elliptical LLO
After the orbit was changed to 100 km × 15 km elliptical LLO, the light/shadows
alternated in a 2 h cycle. The solar array and the battery pack would alternately
power the lunar lander. On such orbit, the battery packs were charged and discharged
repeatedly. The time on such orbit was approximately 4 days.
(7) Powered descent
During powered descent, the engine was firing and the solar array would be unfolded
in advance. The lunar lander was powered by the battery packs. The battery packs
of the lunar rover could power the lunar lander jointly.
2. Occlusion Analysis of Solar Array during Initialization on Lunar Surface
After the lunar lander was landed on lunar surface, the operation status should be
setup as well as TT&C, thermal control and depletion of propellant. However, the
discharge depth of battery packs was higher after powered descent and the power
output of the solar array should be analyzed in order to manage operation procedure
of the lunar lander reasonably.
207
After the solar array was deployed, the battery packs of the lunar lander and rover were
charged. The solar array was kept toward the Sun during LTO except period of trajectory correction maneuvers. During trajectory correction maneuvers, the solar array
was unfolded and did not generate electricity, when the lunar lander was powered by
battery packs. After trajectory correction maneuvers, the battery packs were charged.
(3) LOI
When the lunar lander approached the Moon, the LOI was performed to make the
lunar lander captured by Moon gravity. The lunar lander was inserted into a 100 km
altitude LLO. During LOI, the engine was firing to decelerate. The solar array would
be unfolded in advance. After LOI, it would be deployed again. After deployed, the
solar array would enter alternation process of light/shadow. The power would be
provided alternately by the solar array and the battery packs.
(4) 100 km circular LLO
After the lunar lander was inserted into LLO, the light/shadows alternated in a 2 h
cycle. The solar array and the battery pack would alternately power the lunar lander,
when the battery packs were charged and discharged alternately. The time of the
lunar lander in 100 km LLO was about 5 days.
(5) Orbit change on LLO
Five days after LOI, the lunar lander was inserted into a 100 km × 15 km elliptical
lunar low orbit. Before the engine was firing, the solar array would be folded in
advance. After orbit change, it would be deployed again. Then the solar array would
enter alternation process of light/shadow and the power would be provided alternately
by the solar array and the battery packs.
(6) 100 km × 15 km elliptical LLO
After the orbit was changed to 100 km × 15 km elliptical LLO, the light/shadows
alternated in a 2 h cycle. The solar array and the battery pack would alternately
power the lunar lander. On such orbit, the battery packs were charged and discharged
repeatedly. The time on such orbit was approximately 4 days.
(7) Powered descent
During powered descent, the engine was firing and the solar array would be unfolded
in advance. The lunar lander was powered by the battery packs. The battery packs
of the lunar rover could power the lunar lander jointly.
2. Occlusion Analysis of Solar Array during Initialization on Lunar Surface
After the lunar lander was landed on lunar surface, the operation status should be
setup as well as TT&C, thermal control and depletion of propellant. However, the
discharge depth of battery packs was higher after powered descent and the power
output of the solar array should be analyzed in order to manage operation procedure
of the lunar lander reasonably.