9.5 Testing and Verification
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running under a higher intensity or a special bias status than normal operation conditions, as well as the impact of external faults or input errors on the software function,
to further fully verify the reliability of the OBDH software.
9.6 Summary
The OBDH subsystem of the Chang’E-3 lunar lander was designed to realize on
orbit telemetry, tracking and command, operation and scheduling and comprehensive information processing, which was also an important part of the autonomous
management function of the lunar lander. According to the characteristics of lunar
soft-landing mission, the application of onboard OBDH technology in deep space
exploration is described in this chapter.
The development of spacecraft electronic system has gone through the process
from simple to complex, from device, subsystem to spacecraft. Compared with the
past, the spacecraft electronic system shall be enhanced to improve the ability of
data processing, and be gradually converted into information processing. Through
the fusion of information, autonomous task planning and management of spacecraft
can be implemented autonomously to reduce the burden of ground users and improve
the intelligent level of spacecraft. At the same time, through the integration and
standardization of electronic products, the volume, mass and power consumption
of the product have been greatly reduced, and the generality and scalability are
greatly strengthened. With the continuous reuse of the products, the reliability can
be continuously improved.
In order to meet new requirements of deep space exploration missions, the system
analysis capability of data management technology and R&D platform shall be
enhanced. The design and analysis platform of spacecraft function and information flow shall be further developed, and the advanced electronic system design
technology shall be induced continuously, so that the system design of spacecraft
electronic system can be induced in mainline of spacecraft development process.
From the early stage of spacecraft system design, the design of electronic system
shall be integrated with the mechanical and thermal design, so as to realize the rational
design, classification and management of the functions and information flow of the
spacecraft. Through the simulation and iterative verification of spacecraft function
and information flow, the function design, simulation, verification and perfection
of the electronic system can be achieved in the process of spacecraft development,
so that the design of the electronic system can satisfy the system requirements of
the spacecraft and the shortage can be found as early as possible to provide reliable
basis for spacecraft system design. By this way, the integrated design, simulation and
verification of spacecraft electric, mechanical and thermal can be realized, while the
software and hardware coordinate simulation and design of the electronic system can
be realized, so as to improve integrated and efficient management of the information
flow of the spacecraft.
331
running under a higher intensity or a special bias status than normal operation conditions, as well as the impact of external faults or input errors on the software function,
to further fully verify the reliability of the OBDH software.
9.6 Summary
The OBDH subsystem of the Chang’E-3 lunar lander was designed to realize on
orbit telemetry, tracking and command, operation and scheduling and comprehensive information processing, which was also an important part of the autonomous
management function of the lunar lander. According to the characteristics of lunar
soft-landing mission, the application of onboard OBDH technology in deep space
exploration is described in this chapter.
The development of spacecraft electronic system has gone through the process
from simple to complex, from device, subsystem to spacecraft. Compared with the
past, the spacecraft electronic system shall be enhanced to improve the ability of
data processing, and be gradually converted into information processing. Through
the fusion of information, autonomous task planning and management of spacecraft
can be implemented autonomously to reduce the burden of ground users and improve
the intelligent level of spacecraft. At the same time, through the integration and
standardization of electronic products, the volume, mass and power consumption
of the product have been greatly reduced, and the generality and scalability are
greatly strengthened. With the continuous reuse of the products, the reliability can
be continuously improved.
In order to meet new requirements of deep space exploration missions, the system
analysis capability of data management technology and R&D platform shall be
enhanced. The design and analysis platform of spacecraft function and information flow shall be further developed, and the advanced electronic system design
technology shall be induced continuously, so that the system design of spacecraft
electronic system can be induced in mainline of spacecraft development process.
From the early stage of spacecraft system design, the design of electronic system
shall be integrated with the mechanical and thermal design, so as to realize the rational
design, classification and management of the functions and information flow of the
spacecraft. Through the simulation and iterative verification of spacecraft function
and information flow, the function design, simulation, verification and perfection
of the electronic system can be achieved in the process of spacecraft development,
so that the design of the electronic system can satisfy the system requirements of
the spacecraft and the shortage can be found as early as possible to provide reliable
basis for spacecraft system design. By this way, the integrated design, simulation and
verification of spacecraft electric, mechanical and thermal can be realized, while the
software and hardware coordinate simulation and design of the electronic system can
be realized, so as to improve integrated and efficient management of the information
flow of the spacecraft.