14.3 Requirements and Technical Characteristics
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(d) To verify the correctness and compatibility of electrical interface design
between the lunar lander and the lunar rover.
(e) To check and identify defects in the hardware and software design of the lunar
lander and all subsystem.
For above tasks, the design and implementation of electrical test was conducted as
the following principles and requirements.
(a) To conduct design of electrical test plan and develop ground support equipment in accordance with principles of safety, standardization, comprehension,
accuracy, integrity, reliability and automation.
(b) To provide electric energy for the lunar lander with solar cells simulator.
(c) To receive telemetry data and payload data downlink, and send telecommand.
(d) To establish ground support system to unify data processing, distribution,
display, storage, query and analysis, as well as control and manage ground
test equipment centrally.
(e) To implement processing of data, image resolution and closed-loop test of
subsystems.
(f) To meet the requirements of lunar lander test as well as test of the complex of
the lunar lander and the lunar rover.
(g) To meet the requirements of local test and remote test.
14.3.2 Technical Characteristics
The challenges to electrical test of the lunar lander are listed as follows.
(a) The test process was complex. The electrical test of the lunar lander was classified into two phases: Electrical Module (EM) test and Flight Module (FM)
test. For the FM test, besides electrical performance test in AIT facility, there
were also tests including test in environment tests and test at launch site. At
the same time, there were also joint test for complex of the lunar lander and
the lunar rover, release and separation test. The test process at launch site was
different from traditional spacecraft, which put forward new requirements for
the design and optimization of the test process.
(b) There were lots of test modes. In order to adapt to test requirements in all phases,
a variety of test modes should be designed. During environment test and test
at launch site, the remote test mode was necessary, which should support the
remote transmission of multiple frequency signals such as X band, S band and
UHF band. In addition, there were also test modes for the lunar lander and the
complex of the lunar lander with the lunar rover in the test process. All above
modes and status were new in electrical test.
(c) The test methods were innovative. In order to cover the verification of all
functions and performance specifications of the lunar lander, new test plan
should be designed. For example, there were flight simulation test of powered
descent, telecommunication function test between the lunar lander and the
465
(d) To verify the correctness and compatibility of electrical interface design
between the lunar lander and the lunar rover.
(e) To check and identify defects in the hardware and software design of the lunar
lander and all subsystem.
For above tasks, the design and implementation of electrical test was conducted as
the following principles and requirements.
(a) To conduct design of electrical test plan and develop ground support equipment in accordance with principles of safety, standardization, comprehension,
accuracy, integrity, reliability and automation.
(b) To provide electric energy for the lunar lander with solar cells simulator.
(c) To receive telemetry data and payload data downlink, and send telecommand.
(d) To establish ground support system to unify data processing, distribution,
display, storage, query and analysis, as well as control and manage ground
test equipment centrally.
(e) To implement processing of data, image resolution and closed-loop test of
subsystems.
(f) To meet the requirements of lunar lander test as well as test of the complex of
the lunar lander and the lunar rover.
(g) To meet the requirements of local test and remote test.
14.3.2 Technical Characteristics
The challenges to electrical test of the lunar lander are listed as follows.
(a) The test process was complex. The electrical test of the lunar lander was classified into two phases: Electrical Module (EM) test and Flight Module (FM)
test. For the FM test, besides electrical performance test in AIT facility, there
were also tests including test in environment tests and test at launch site. At
the same time, there were also joint test for complex of the lunar lander and
the lunar rover, release and separation test. The test process at launch site was
different from traditional spacecraft, which put forward new requirements for
the design and optimization of the test process.
(b) There were lots of test modes. In order to adapt to test requirements in all phases,
a variety of test modes should be designed. During environment test and test
at launch site, the remote test mode was necessary, which should support the
remote transmission of multiple frequency signals such as X band, S band and
UHF band. In addition, there were also test modes for the lunar lander and the
complex of the lunar lander with the lunar rover in the test process. All above
modes and status were new in electrical test.
(c) The test methods were innovative. In order to cover the verification of all
functions and performance specifications of the lunar lander, new test plan
should be designed. For example, there were flight simulation test of powered
descent, telecommunication function test between the lunar lander and the