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4 Structure and Mechanism Technology of Lunar Lander
gravity on orbit, but also be unfolded, folded and maintain under gravity environment
of 1/6 g on lunar surface. Therefore, for the functional verification of the solar panel
mechanism of the Chang’E-3 lunar lander, it was not only necessary to simulate
unfolding and folding under zero gravity on orbit, but also to simulate unfolding,
folding and maintaining functions under 1/6 g gravity and different landing attitude
conditions.
The functional tests of solar panel mechanism in simulated zero-gravity environment could be carried out on the hanging-type simulated zero-gravity deployment
equipment. After the weight of solar panel substrate was balanced by spring, it could
be verified for unfolding and folding.
The function tests of unfolding, folding and maintaining for solar panel mechanism under simulated 1/6 g gravity could be carried out by adjusting vehicle attitude
angle to simulate possible landing attitude of the lander and balancing 5/6 ground
gravity of solar panel substrate by balloon.
2) Environmental tests
The Chang’E-3 lunar lander solar wing should adapt to environment of launch,
orbit flight, powered descent, soft-landing and lunar surface. Therefore, environmental tests were conducted for solar panel mechanism of the Chang’E-3 lunar
lander including:
(1) Mechanical environmental tests were conducted for the loads during launch and
landing including sinusoidal vibration tests, random vibration tests, acoustic
environment and static test tests for launch, and static tests for landing.
(2) Thermal environment tests were conducted for thermal environment during
flight. The temperature conditions for the solar panel mechanism of the
Chang’E-3 lunar lander’s on orbit and lunar surface were worse than solar panel
mechanism of general spacecraft. Therefore, thermal environment tests were
conducted during development of solar panel mechanism including extreme
high and low temperature vacuum environment tests, extreme low temperature
environment tests on lunar surface, and life tests under extreme high and low
temperature environment tests on lunar surface.
(3) Lunar dust environmental adaptability tests were conducted in order to verify
the adaptability of motion parts of solar panel mechanism to lunar dust
environment.
(4) Low temperature function tests were conducted to verify the function of
unfolding and folding of solar panel mechanism under low-temperature
environment.
4 Structure and Mechanism Technology of Lunar Lander
gravity on orbit, but also be unfolded, folded and maintain under gravity environment
of 1/6 g on lunar surface. Therefore, for the functional verification of the solar panel
mechanism of the Chang’E-3 lunar lander, it was not only necessary to simulate
unfolding and folding under zero gravity on orbit, but also to simulate unfolding,
folding and maintaining functions under 1/6 g gravity and different landing attitude
conditions.
The functional tests of solar panel mechanism in simulated zero-gravity environment could be carried out on the hanging-type simulated zero-gravity deployment
equipment. After the weight of solar panel substrate was balanced by spring, it could
be verified for unfolding and folding.
The function tests of unfolding, folding and maintaining for solar panel mechanism under simulated 1/6 g gravity could be carried out by adjusting vehicle attitude
angle to simulate possible landing attitude of the lander and balancing 5/6 ground
gravity of solar panel substrate by balloon.
2) Environmental tests
The Chang’E-3 lunar lander solar wing should adapt to environment of launch,
orbit flight, powered descent, soft-landing and lunar surface. Therefore, environmental tests were conducted for solar panel mechanism of the Chang’E-3 lunar
lander including:
(1) Mechanical environmental tests were conducted for the loads during launch and
landing including sinusoidal vibration tests, random vibration tests, acoustic
environment and static test tests for launch, and static tests for landing.
(2) Thermal environment tests were conducted for thermal environment during
flight. The temperature conditions for the solar panel mechanism of the
Chang’E-3 lunar lander’s on orbit and lunar surface were worse than solar panel
mechanism of general spacecraft. Therefore, thermal environment tests were
conducted during development of solar panel mechanism including extreme
high and low temperature vacuum environment tests, extreme low temperature
environment tests on lunar surface, and life tests under extreme high and low
temperature environment tests on lunar surface.
(3) Lunar dust environmental adaptability tests were conducted in order to verify
the adaptability of motion parts of solar panel mechanism to lunar dust
environment.
(4) Low temperature function tests were conducted to verify the function of
unfolding and folding of solar panel mechanism under low-temperature
environment.