MDO method and system for local control of spacecraft

Abstract

The invention discloses an MDO method of spacecraft local control. The method comprises the steps of receiving user demand information and recording a task source corresponding to the user demand information; generating an overall design index and engineering constraint; subjecting subsystems of a spacecraft to compatible decoupling to generate optimization objectives of the subsystems; and obtaining design parameters of the subsystems to form an overall scheme. The invention also provides a corresponding MDO system of the spacecraft local control. By fully utilizing an interactive cooperation mechanism in a spacecraft system to optimize the design of a large-scale complex system and based on the idea that local minimum serves overall optimization, the MDO method and system of the spacecraft local control can simplify the system optimization problem; compared with a traditional spacecraft design method, has the advantages of being well-targeted, clearly-structured and good in operability; and is a multidisciplinary optimization method applicable to engineering practice, and has some engineering use values.

Description

technical field [0001] The invention relates to spacecraft optimization design technology, in particular to a spacecraft optimization design method and system based on local control MDO (Multidisciplinary Design Optimization). Background technique [0002] Traditional spacecraft design methods usually decompose the spacecraft into subsystems such as structure, power supply, thermal control, attitude and orbit control, measurement and control, and data management. Each subsystem is designed according to the overall design requirements of the spacecraft and the technical characteristics of the subsystem. It is processed and made into hardware, and then all subsystems are assembled, tested, tested and adjusted to finally form a spacecraft. This method is not very adaptable and pertinent to the spacecraft design of different tasks, showing the following disadvantages: [0003] 1) Due to the serial design mode, in different design stages, designers optimize the design of the spa...

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Problems solved by technology

[0003] 1) Due to the serial design mode, in different design stages, designers optimize the design of the spacecraft according to different disciplines. Although the relationship between them is simple, the optical, mechanical, and electrical components that will substantially affect the performance of the spacecraft at the same time. The disciplines such as heat, magnetism, etc. are forcibly separated, and the synergistic effect produced by the coupling between various disciplines is not fully utilized.

[0004] 2) In the scheme design stage, there is a lack of reasonable allocation of system indicators, and the collaborative design of different disciplines cannot be integrated

The lack of design freedom in the later stage of design makes it impossible to achieve global optimization of complex systems

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