| 摘要 |
The method involves obtaining two plate formed modules and binding the two module during mounting in orbit. One module (22) has a frame (20) structure pattern which defines an interior space and the other module is chosen such that both modules have the same volume. In each module is provided e.g. a thermal subsystem (32), a telemetry, tracking, and command subsystem (42), an electrical supply subsystem (30), and a command and orientation attitude subsystem (34) together with a payload (44). After mounting in orbit, the two units are detached from one another and removed from orbit independently one after the other after detachment.
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