Modelica model-based spacecraft energy system model construction method

Abstract

The invention discloses a Modelica model-based spacecraft energy system model construction method. The method comprises the following steps of: 1, carrying out design composition on an energy system model; 2, constructing a Modelica language-based energy system model library; and 3, demarcating and verifying the Modelica language-based energy system model library. The spacecraft energy system model construction method is oriented to objects and equations and has favorable reusability and hierarchy; and through applying the method, the difficulty of model development can be greatly reduced, the reusability of models can be remarkably improved, the energy system design period can be effectively shortened, the dynamic design ability can be enhanced and the design efficiency can be improved.

Description

technical field [0001] The present invention relates to the design field of spacecraft energy system (also called power supply and overall circuit system, power supply and distribution system, hereinafter referred to as energy system), and mainly relates to a construction method of spacecraft energy system based on Modelica model. Because there are many types of spacecraft energy systems, the model library described here only involves the energy system of battery-solar array combination. Background technique [0002] At present, the design of spacecraft energy systems, especially in the overall design stage, generally adopts the method of combining empirical formulas and typical parameters to perform static energy balance and power flow calculations. However, under normal circumstances, the power generation and load power of the energy system change dynamically. , and is closely related to task scheduling and the design of other subsystems, its dynamic design is extremely ...

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Problems solved by technology

[0003] At the same time, with the deepening of design verification, it is necessary to establish simulation models according to different stages to meet the needs of simulation verification at different levels. However, under normal circumstances, a simulation model can only be used for simulation verification of a single design stage. For different design stages simulation analysis, it is necessary to re-model

This makes it difficult to carry out dynamic energy balance analysis and optimization in the design analysis and verification process of the entire spacecraft energy system. The workload of the designers is heavy, the design verification cycle is long, and the efficiency is not high.

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