Multi-objective optimization design method, system and storage medium for spacecraft power system

Abstract

The invention discloses a spacecraft power system multi-objective optimization design method, system, and a storage medium. The method comprises the following steps of establishing an objective function based on a spacecraft power system pre-optimization objective; determining design variables of the objective function; determining constraint conditions of the objective function; according to theobjective function, building a power model and an external environment model of a spacecraft power system; by using an optimization algorithm, calling the power model and the external environment model of the spacecraft power system to perform simulation, and under the design variables and the constraint conditions, performing multi-objective optimization design by taking the objective function asan objective, thereby obtaining Pareto optimal solutions; and in combination with preference information of a power system designer, from the Pareto optimal solutions, selecting one as a final spacecraft system design scheme. The method lowers the difficulty in comprehensive quantitative analysis of spacecraft power system design, and realizes the multi-target optimization of the spacecraft powersystem.

Description

technical field [0001] The invention relates to the technical field of spacecraft power supply systems, in particular to a multi-objective optimization design method, system and storage medium for spacecraft power supply systems. Background technique [0002] The design of the spacecraft power system is an important part of the development of the spacecraft power system, and the design quality of the power system plays a key role in the performance of the power system. The optimal design of the spacecraft power system is of great significance to increase the system payload, improve the performance and efficiency of the spacecraft, and so on. [0003] The solar array-battery pack power system is the most widely used spacecraft power system in the world. More than 90% of the spacecraft launched in the world use the solar array-battery pack power supply system. The design of the spacecraft power system depends on the working life of the power system, load characteristics and ...

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Problems solved by technology

[0004] There are two problems in the current design of the spacecraft power supply system: First, it is difficult to conduct a comprehensive quantitative analysis of the design scheme in the face of many constraints, especially for some design schemes that have many constraints and are difficult to calculate. Parameters, designers can only estimate based on their own experience, resulting in a large power margin in the final design; second, most studies have considered single-objective optimization, such as minimizing the total cost of the system, minimizing The total quality of the system, etc. However, from a practical point of view, the design of the spacecraft power system is a multi-objective optimization problem, that is, multiple objectives such as cost, quality, reliability, etc. need to be optimized simultaneously, and the design of the spacecraft power system is a multi-objective optimization problem. variable, nonlinear complex optimization problems

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