12.5 Typical Application of System Integration and Assembly
419
and bound, the cable should be wrapped with the protective layer to prevent abrasion
during vibration.
(2) High-frequency cables should be installed separately and not be mixed with
low-frequency cables. When it was installed, shaping and trial installation in cable
installation were acceptable, but damage to metal surface was not allowed; Similarly,
the distance between the cable and the instrument, the fixed spacing and the inner
bending radius should be controlled during installation.
(3) When the electrical connector was inserted, the consistence of the code of the
plug and the socket should be carefully examined, as well as cleanness and intact
condition of the pin and the socket. When the electrical connector was inserted, it
should be installed in place and anti-loosening treatment should be conducted after
insertion.
(4) When the cable of moving parts was fixed, it was necessary to strictly control
the bending radius of the cable to ensure its activity margin. Not only the cable length
requirement during movement should be satisfied, but also interference with others
during movement should be avoided.
For the Chang’E-3 lunar lander, because there were lots of moving parts and the
environment on orbit was harsh, the focus of cable assembly was the cable length
reserved for moving parts, as well as the margin for expansion and contraction under
extreme temperature change. In order to satisfy the deployment requirements of the
landing legs and solar panels, the appropriate movement margin for binding and fixing
should be reserved. At the same time, because of extreme hot and cold temperature in
lunar day and night, not only the process should be designed for firm fix, but also the
binding material for the cable should be adaptive to the extreme temperature change.
12.5.4 Structural Assembly
In the AIT process, part spacecraft structures shall be disassembled to meet the
requirements of system integration and assembly. At the end, the modules are
reassembled in position. In the process of spacecraft system integration and assembly,
generally only module or deck is reassembled to maintain the status of main structure.
1. Module Assembly
The layout of cable among the modules and main structure of the Chang’E-3 lunar
lander was different from other spacecraft. For the complex cable layout in the lunar
lander structure, a special technological method with a 6-DOF module attitudeadjusting and tilting carriage was proposed for the solution to dock and disassembly
of the deck with the lunar lander. The new attitude-adjusting and tilting carriage was
a side-opening tilting carriage, which could implement a smooth lateral opening and
closing of the module and might provide a new idea for module assembly of other
spacecraft.
2. Assembly of Deck (including Transfer Mechanism)
419
and bound, the cable should be wrapped with the protective layer to prevent abrasion
during vibration.
(2) High-frequency cables should be installed separately and not be mixed with
low-frequency cables. When it was installed, shaping and trial installation in cable
installation were acceptable, but damage to metal surface was not allowed; Similarly,
the distance between the cable and the instrument, the fixed spacing and the inner
bending radius should be controlled during installation.
(3) When the electrical connector was inserted, the consistence of the code of the
plug and the socket should be carefully examined, as well as cleanness and intact
condition of the pin and the socket. When the electrical connector was inserted, it
should be installed in place and anti-loosening treatment should be conducted after
insertion.
(4) When the cable of moving parts was fixed, it was necessary to strictly control
the bending radius of the cable to ensure its activity margin. Not only the cable length
requirement during movement should be satisfied, but also interference with others
during movement should be avoided.
For the Chang’E-3 lunar lander, because there were lots of moving parts and the
environment on orbit was harsh, the focus of cable assembly was the cable length
reserved for moving parts, as well as the margin for expansion and contraction under
extreme temperature change. In order to satisfy the deployment requirements of the
landing legs and solar panels, the appropriate movement margin for binding and fixing
should be reserved. At the same time, because of extreme hot and cold temperature in
lunar day and night, not only the process should be designed for firm fix, but also the
binding material for the cable should be adaptive to the extreme temperature change.
12.5.4 Structural Assembly
In the AIT process, part spacecraft structures shall be disassembled to meet the
requirements of system integration and assembly. At the end, the modules are
reassembled in position. In the process of spacecraft system integration and assembly,
generally only module or deck is reassembled to maintain the status of main structure.
1. Module Assembly
The layout of cable among the modules and main structure of the Chang’E-3 lunar
lander was different from other spacecraft. For the complex cable layout in the lunar
lander structure, a special technological method with a 6-DOF module attitudeadjusting and tilting carriage was proposed for the solution to dock and disassembly
of the deck with the lunar lander. The new attitude-adjusting and tilting carriage was
a side-opening tilting carriage, which could implement a smooth lateral opening and
closing of the module and might provide a new idea for module assembly of other
spacecraft.
2. Assembly of Deck (including Transfer Mechanism)