Spacecraft in-orbit multifunctional structure integrated management and control system

Abstract

A spacecraft in-orbit multifunctional structure integrated management and control system comprises a multifunctional structure unit, a power management unit, a data processing unit, and a discharge load unit. The multifunctional structure unit integrates the bearing, power supply and vibration reduction functions. The power management unit controls charge / discharge operation, detects and adjusts the electrical performance parameters of power modules in real time, and transmits the parameters to the data processing unit. The data processing unit acquires the mechanical / electrical performance parameters of system operation and submits the parameters to a spacecraft platform through a remote sensing and data transmission interface, and the parameters are finally transmitted back to the ground. The discharge load unit consumes power under control of the power management unit. According to the system, a spacecraft structure and a power source are fused in a multifunctional manner, power source charge / discharge management, structure mechanics / electrical performance monitoring, and data management and transmission are integrated together, and the task process from remote control instruction receiving to multifunction implementation and further to state monitoring and data management and transmission can be executed systematically.

Description

technical field [0001] The invention belongs to the technical field of spacecraft structure and design, and in particular relates to a comprehensive management and control system for an in-orbit multifunctional structure of a spacecraft. Background technique [0002] At present, spacecraft have higher and higher requirements for its payload ratio and available space. For this reason, multifunctional structure technology has gradually been paid attention to and applied in the aerospace field. Multifunctional structure technology is a technology that organically integrates functions such as data processing, radiation protection, thermal control, and power storage with the spacecraft's own structure. By adopting the integrated design of structure, function, and materials, a large number of redundant masses are eliminated. and volume, thereby significantly improving the spacecraft's load / mass ratio, load / volume ratio, and function / structure ratio. [0003] However, for a specif...

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Problems solved by technology

So far, there are no literature reports or engineering application precedents about this kind of management and control system at home and abroad.

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