6.5 Typical Technology
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lunar rover. The only difference was that the battery pack of the lunar rover was not
connected to BDR module of the lunar lander.
6.6 Testing and Verification
6.6.1 Contents of Verification
Compared with conventional spacecraft, in addition to the conventional performance
tests of mechanical, electrical and thermal, special tests should be conducted for the
power system of the lunar lander including hibernation and awakening function
verification, verification of large incident angle for solar cells and performance test
of solar cell circuit under extremes temperature.
6.6.2 Verification of Hibernation and Awakening
The hibernation and awakening circuit was in the power controller to control the
process of hibernation and awakening of the lunar lander. The solar array simulator
was used to simulate the current generated by sun light in the special test, while all
other status was consistent with condition on orbit. The output current of the solar
array simulator was adjusted to simulate the change of light intensity and reproduce
the transfer process of lunar daytime and night.
In the test of hibernation, the ground test station sent commands one by one to
shut off instruments of the lunar lander in sequence, while the output current of the
solar array simulator was reduced gradually to simulate the gradual weakening of
sun light. When the output current of the solar array simulator was less than the load
current, the secondary power supply of the power controller was shut off and the
lunar lander entered hibernation, while all telemetry remained in the last frame.
In the test of awakening, the output current of the solar array simulator was
gradually increased to simulate the gradual strengthening of sun light. When the
output current of the solar array simulator reached the load current, the secondary
power supply relay of the power supply controller was closed, and the secondary
power supply was powered on, and the pulse trigger circuit was triggered to generate
high level pulse to connect the battery packs and OBDH computer. The lunar lander
was awakened autonomously.
For the hibernation and awakening function, it was necessary to verify in normal
temperature and pressure, thermal cycle, thermal vacuum, system-level electrical
performance test, and system-level thermal test to ensure that the test items and
test conditions were comprehensively covered. The function must be tested at the
highest working temperature and lowest working temperature, and compared the
output current value of the solar array simulator at awakening time under different
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lunar rover. The only difference was that the battery pack of the lunar rover was not
connected to BDR module of the lunar lander.
6.6 Testing and Verification
6.6.1 Contents of Verification
Compared with conventional spacecraft, in addition to the conventional performance
tests of mechanical, electrical and thermal, special tests should be conducted for the
power system of the lunar lander including hibernation and awakening function
verification, verification of large incident angle for solar cells and performance test
of solar cell circuit under extremes temperature.
6.6.2 Verification of Hibernation and Awakening
The hibernation and awakening circuit was in the power controller to control the
process of hibernation and awakening of the lunar lander. The solar array simulator
was used to simulate the current generated by sun light in the special test, while all
other status was consistent with condition on orbit. The output current of the solar
array simulator was adjusted to simulate the change of light intensity and reproduce
the transfer process of lunar daytime and night.
In the test of hibernation, the ground test station sent commands one by one to
shut off instruments of the lunar lander in sequence, while the output current of the
solar array simulator was reduced gradually to simulate the gradual weakening of
sun light. When the output current of the solar array simulator was less than the load
current, the secondary power supply of the power controller was shut off and the
lunar lander entered hibernation, while all telemetry remained in the last frame.
In the test of awakening, the output current of the solar array simulator was
gradually increased to simulate the gradual strengthening of sun light. When the
output current of the solar array simulator reached the load current, the secondary
power supply relay of the power supply controller was closed, and the secondary
power supply was powered on, and the pulse trigger circuit was triggered to generate
high level pulse to connect the battery packs and OBDH computer. The lunar lander
was awakened autonomously.
For the hibernation and awakening function, it was necessary to verify in normal
temperature and pressure, thermal cycle, thermal vacuum, system-level electrical
performance test, and system-level thermal test to ensure that the test items and
test conditions were comprehensively covered. The function must be tested at the
highest working temperature and lowest working temperature, and compared the
output current value of the solar array simulator at awakening time under different