ABSTRACT
Based on the analysis of a spacecraft mission, the spacecraft system concept design can be carried out. The design of the spacecraft system concept is complex, involving the design of multiple disciplines such as mechanical, electrical and thermal disciplines and including the design of internal and external interfaces of the spacecraft system. This chapter describes in detail the overall design contents of the system, puts forward the overall design requirements for the subsystems, presents the contents of flight program design and discusses the design and verification of internal and external system interfaces. The influence on the design of spacecraft information flow is analyzed and finally the code rate of telemetry/telecontrol information channels and the rate of payload downlink are determined. The main task of microwave ground-receiving system is to automatically track the satellite; receive, demodulate, decode and save remote sensing data sent by the satellite; descramble, decrypt and decompress the demodulated data stream; and save and archive the received data.
