4.4 Mechanism Design and Verification of Lunar Lander
127
Table 4.3 (continued)
Requirement
Definition
Description
Information needed
Mass
The total mass was less
than the specified value
Preliminary allocation in
phase B, adjustment after
detailed design
Mass allocated
Orientation requirements Requirement of relative
position between solar
panels and the lunar
lander coordinate system
Requirements of the solar
panel position during
flight and operation on
lunar surface
Given position
requirements to
spacecraft coordinate
system in all flight phases
Drive capability
Output torque of drive
1) The motion
requirements of the
solar panel were
different in flight and
operation on lunar
surface
2) The maintenance
capability
requirements of the
solar panel at stop
position were also
different in flight and
operation on lunar
surface
1) Mass property
2) Load
3) Resistance moment
4) Operation temperature
(1) Launch phase: The solar panels should withstand the load during launch.
(2) Flight phase: After orbit injection, the solar panels would be deployed at 180°
according to power supply requirements of the lunar lander. At this phase, the
solar panels should provide sufficient driving capacity to carry out folding and
unfolding under vacuum and radiation conditions by command and provide
correct position signal. At the same time, the solar panels also had to withstand
the load of 7500 N engine ignition and stop during orbit maneuver.
(3) Landing phase: Solar panels should withstand landing impact loads.
(4) Operation phase on lunar surface: On the lunar daytime, solar panel mechanism should perform folding/unfolding and change angle under environmental
conditions such as high temperature, radiation and lunar dust on lunar surface
to provide sufficient power energy. The drive assembly should have sufficient
capability of driving and position maintenance under different attitude of the
lunar lander and 1/6 lunar gravity. The position switch should provide correct
in-position signal. On the lunar night, the solar panel mechanism should survive
in extreme low-temperature environment and recover to normal operation after
lunar night.
From above analysis, it could be seen that the key design of solar panels of the
Chang’E-3 lunar lander is as follows:
(1) The solar panels could withstand mechanical loads caused by launch, landing,
high and low temperature environments, and the structural strength can meet
requirements.
127
Table 4.3 (continued)
Requirement
Definition
Description
Information needed
Mass
The total mass was less
than the specified value
Preliminary allocation in
phase B, adjustment after
detailed design
Mass allocated
Orientation requirements Requirement of relative
position between solar
panels and the lunar
lander coordinate system
Requirements of the solar
panel position during
flight and operation on
lunar surface
Given position
requirements to
spacecraft coordinate
system in all flight phases
Drive capability
Output torque of drive
1) The motion
requirements of the
solar panel were
different in flight and
operation on lunar
surface
2) The maintenance
capability
requirements of the
solar panel at stop
position were also
different in flight and
operation on lunar
surface
1) Mass property
2) Load
3) Resistance moment
4) Operation temperature
(1) Launch phase: The solar panels should withstand the load during launch.
(2) Flight phase: After orbit injection, the solar panels would be deployed at 180°
according to power supply requirements of the lunar lander. At this phase, the
solar panels should provide sufficient driving capacity to carry out folding and
unfolding under vacuum and radiation conditions by command and provide
correct position signal. At the same time, the solar panels also had to withstand
the load of 7500 N engine ignition and stop during orbit maneuver.
(3) Landing phase: Solar panels should withstand landing impact loads.
(4) Operation phase on lunar surface: On the lunar daytime, solar panel mechanism should perform folding/unfolding and change angle under environmental
conditions such as high temperature, radiation and lunar dust on lunar surface
to provide sufficient power energy. The drive assembly should have sufficient
capability of driving and position maintenance under different attitude of the
lunar lander and 1/6 lunar gravity. The position switch should provide correct
in-position signal. On the lunar night, the solar panel mechanism should survive
in extreme low-temperature environment and recover to normal operation after
lunar night.
From above analysis, it could be seen that the key design of solar panels of the
Chang’E-3 lunar lander is as follows:
(1) The solar panels could withstand mechanical loads caused by launch, landing,
high and low temperature environments, and the structural strength can meet
requirements.