12.4 Design of System Integration and Assembly
409
12.4 Design of System Integration and Assembly
Generally, in the design of spacecraft system integration and assembly, there are
the design of systematic assembly process, systematic planning of technological
equipment, process test planning and technical process flow. Because of system
complexity of the lunar lander and specialty of system integration and assembly,
in the design of system integration and assembly of the lunar lander, there should
also be the design of digital assembly and automated assembly. In this chapter, it
is described with the practice of system integration and assembly of the Chang’E-3
lunar lander.
12.4.1 Design of Systematic Assembly Process
The systematic assembly process is the top-level document for spacecraft system
integration and assembly, whose objective is to ensure smooth manufacture and
development. It is based on the design requirements, combined with actual manufacture capacity and constraints. Then the process inheritance, assembly difficulties and
risks of the system integration and assembly process are analyzed, and the manufacture model is formulated, so as to establish support conditions in advance. Generally,
the major contents of systematic assembly process include the follows.
(1) Analysis of product structure, performance and process characteristics.
(2) Process inheritance analysis of system integration and assembly.
(3) Analysis of difficulties in process, process research and support condition.
(4) Analysis of major examination, professional test and its implementation plans.
(5) Analysis of application of new technology, new equipment, and its implementation approaches.
(6) Identification of technical risk and analysis of reliability and safety.
(7) Process quality assurance measures of product, including process examination,
technical status control, process review, tabular documentation, tools management, process document management and documentation requirements.
(8) Analysis of support condition, including Mechanical Ground Support Equipment (MGSE), resource planning and supply readiness of system assembly.
(9) Coordination and cooperation with partners.
The Chang’E-3 lunar lander was a complex spacecraft and it was necessary to design
the system integration and assembly in the early stage of phase B (preliminary design
and technology completion). In the design of system integration and assembly, it
should be analyzed as follows.
(1) Analysis of the impact of the lunar lander configuration and scientific payloads
on process of assembly and manufacture. The structure of the Chang’E-3 lunar lander
was a cross-support structure, and more than 80% of onboard instruments were newly
developed. It should be analyzed including how to assembly and conduct electrical
409
12.4 Design of System Integration and Assembly
Generally, in the design of spacecraft system integration and assembly, there are
the design of systematic assembly process, systematic planning of technological
equipment, process test planning and technical process flow. Because of system
complexity of the lunar lander and specialty of system integration and assembly,
in the design of system integration and assembly of the lunar lander, there should
also be the design of digital assembly and automated assembly. In this chapter, it
is described with the practice of system integration and assembly of the Chang’E-3
lunar lander.
12.4.1 Design of Systematic Assembly Process
The systematic assembly process is the top-level document for spacecraft system
integration and assembly, whose objective is to ensure smooth manufacture and
development. It is based on the design requirements, combined with actual manufacture capacity and constraints. Then the process inheritance, assembly difficulties and
risks of the system integration and assembly process are analyzed, and the manufacture model is formulated, so as to establish support conditions in advance. Generally,
the major contents of systematic assembly process include the follows.
(1) Analysis of product structure, performance and process characteristics.
(2) Process inheritance analysis of system integration and assembly.
(3) Analysis of difficulties in process, process research and support condition.
(4) Analysis of major examination, professional test and its implementation plans.
(5) Analysis of application of new technology, new equipment, and its implementation approaches.
(6) Identification of technical risk and analysis of reliability and safety.
(7) Process quality assurance measures of product, including process examination,
technical status control, process review, tabular documentation, tools management, process document management and documentation requirements.
(8) Analysis of support condition, including Mechanical Ground Support Equipment (MGSE), resource planning and supply readiness of system assembly.
(9) Coordination and cooperation with partners.
The Chang’E-3 lunar lander was a complex spacecraft and it was necessary to design
the system integration and assembly in the early stage of phase B (preliminary design
and technology completion). In the design of system integration and assembly, it
should be analyzed as follows.
(1) Analysis of the impact of the lunar lander configuration and scientific payloads
on process of assembly and manufacture. The structure of the Chang’E-3 lunar lander
was a cross-support structure, and more than 80% of onboard instruments were newly
developed. It should be analyzed including how to assembly and conduct electrical