Cone type modularization satellite platform architecture

Abstract

A cone type modularization satellite platform architecture comprises a platform standard module and a load standard module. The platform standard module comprises a cone module, an attitude orbit control module, a communication module and a solar panel substrate module. The cone module a mechanical supporting module and a platform information flow pivot of the cone type modularization satellite platform architecture. The cone module comprises an information processor, a high-speed network switch, a power source and a standard interface. The attitude orbit control module, the communication module, the solar panel substrate module and a load standard module are fixedly connected with the cone module through the standard interface and perform information communication processing, and the power source inside the cone module supplies power to the attitude orbit control module, the communication module, the solar panel substrate module and / or the load standard module. According to the cone type modularization satellite platform architecture, by adopting the cone type coaxial configuration, exchange network information flow and grid-connected distributive energy flow technology, rapid satellite design, plug-in type assembling and adjusting and batch production are achieved, and rapid improvement of satellite functions and performance is promoted.

Description

technical field [0001] The invention relates to a satellite platform architecture, in particular to a vertebral column modular satellite platform architecture. Background technique [0002] Since the launch of the first satellite, the evolution of overall satellite design technology can be divided into three stages: (1) traditional design method; (2) multi-task public platform design method; (3) standardized modular design method; [0003] (1) The first stage: traditional design method [0004] After the space flight mission requirements and constraints are determined, the satellite's power supply, attitude determination and control, propulsion, structure, thermal control, communication, command and data processing, load and other sub-systems need to be designed separately, and then aggregated and superimposed . Each satellite needs to repeat the above process. The advantage of this design method is that the satellite can well meet the tasks undertaken. The disadvantage ...

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Problems solved by technology

However, China's work in this area is still in its infancy, and there are no public reports on related products.

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