466
14 Electrical Testing Technology of Lunar Lander
lunar rover, hibernation and awakening function test and so on, which were
new for electrical test and should be considered and designed.
(d) The ground support equipment was complex. There are many information
sources and a great many data of the lunar lander. The data interface and information flow between ground support equipment and the lunar lander were also
complex. It was necessary to develop a highly-automatic ground test system
to meet the test requirements of all phases and test modes, which should be
highly automated and implement test process with central control of terminal
equipment.
(e) The requirement for test data interpretation was high. The test data of the
Lander in all phases of development process were strictly interpreted, and the
test data in different time and phases should be compared and analyzed. Based
on the characteristics of the lunar lander, the test data interpretation criterion
should be clearly defined, as well as the timing and interpretation rules of
all data. Meanwhile, more flexible requirements were come up for automatic
interpretation tools. Besides the traditional data query function, the data classification and extraction, characteristic value statistics, integrity analysis and
other statistical analysis functions should also be accomplished.
14.4 Electrical Testing Plan
14.4.1 Testing Process
The electrical test of the lunar lander was divided into two phases: Electrical Module
(EM) test and Flight Module (FM) test. In the EM test, there were electrical test in
AIT facility and EMC test. In the FM test, there were electrical test in AIT facility,
electrical test in environment tests and vacuum thermal test, interface tests with other
engineering systems, electrical test at launch site. The test process of FM electrical
test in AIT facility of the Chang’E-3 lunar lander test is shown in Fig. 14.1.
Unlike ordinary spacecraft, the lunar lander was usually designed to be a complex
of multiple probes in order to accomplish complicated lunar missions. To ensure that
the electrical test was completed within specified time in the project schedule, the
maximum parallel principle was applied in the design of the test process: independent tests in parallel were conducted for different probes, including interface test,
subsystem function and performance test, even parts of flight simulation test. After
the test of single probe, complex test of multiple probes would be conducted.
14 Electrical Testing Technology of Lunar Lander
lunar rover, hibernation and awakening function test and so on, which were
new for electrical test and should be considered and designed.
(d) The ground support equipment was complex. There are many information
sources and a great many data of the lunar lander. The data interface and information flow between ground support equipment and the lunar lander were also
complex. It was necessary to develop a highly-automatic ground test system
to meet the test requirements of all phases and test modes, which should be
highly automated and implement test process with central control of terminal
equipment.
(e) The requirement for test data interpretation was high. The test data of the
Lander in all phases of development process were strictly interpreted, and the
test data in different time and phases should be compared and analyzed. Based
on the characteristics of the lunar lander, the test data interpretation criterion
should be clearly defined, as well as the timing and interpretation rules of
all data. Meanwhile, more flexible requirements were come up for automatic
interpretation tools. Besides the traditional data query function, the data classification and extraction, characteristic value statistics, integrity analysis and
other statistical analysis functions should also be accomplished.
14.4 Electrical Testing Plan
14.4.1 Testing Process
The electrical test of the lunar lander was divided into two phases: Electrical Module
(EM) test and Flight Module (FM) test. In the EM test, there were electrical test in
AIT facility and EMC test. In the FM test, there were electrical test in AIT facility,
electrical test in environment tests and vacuum thermal test, interface tests with other
engineering systems, electrical test at launch site. The test process of FM electrical
test in AIT facility of the Chang’E-3 lunar lander test is shown in Fig. 14.1.
Unlike ordinary spacecraft, the lunar lander was usually designed to be a complex
of multiple probes in order to accomplish complicated lunar missions. To ensure that
the electrical test was completed within specified time in the project schedule, the
maximum parallel principle was applied in the design of the test process: independent tests in parallel were conducted for different probes, including interface test,
subsystem function and performance test, even parts of flight simulation test. After
the test of single probe, complex test of multiple probes would be conducted.