Combination on-orbit energy management method based on energy balance analysis

A technology for energy management and energy balance, applied in resources, data processing applications, electrical digital data processing, etc., can solve problems such as large energy management errors of spacecraft assemblies, improve accuracy, improve utilization, and ensure normal work Effect

Inactive Publication Date: 2018-07-31
BEIJING SPACE TECH RES & TEST CENT
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  • Abstract
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  • Claims
  • Application Information

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Problems solved by technology

[0003] The purpose of the present invention is to provide an on-orbit energy management method for an assembly based on energy balance analysis to solve the problem of large errors in the energy management of spacecraft assemblies

Method used

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  • Combination on-orbit energy management method based on energy balance analysis
  • Combination on-orbit energy management method based on energy balance analysis

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Embodiment approach

[0037] Such as figure 1 As shown, according to an embodiment of the present invention, a method for on-orbit energy management of an assembly based on energy balance analysis of the present invention includes:

[0038] S1. Construct the spacecraft model and connect it into an assembly model, and obtain the flight plan of the assembly model;

[0039] S2. Obtain the power generation capacity curve according to the combination model and the flight plan, and obtain the load working curve according to the flight plan;

[0040] S3. Evaluate the energy balance state of the combination model based on the generating capacity curve and the load working curve.

[0041] Such as figure 2 As shown, according to an embodiment of the present invention, step S1 includes:

[0042]S11. Construct a spacecraft model according to the actual size of the spacecraft, and connect the spacecraft models into an assembly model. In this embodiment, a spacecraft model including its main structure is es...

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Abstract

The invention relates to a combination on-orbit energy management method based on energy balance analysis. The method comprises the steps that S1. a spacecraft model is constructed and connected as acombination model, and the flight scheme of the combination model is acquired; S2. a power generation capacity curve is acquired according to the combination model and the flight scheme, and a load working curve is acquired according to the flight scheme; and S3. the energy balance state of the combination model is assessed based on the power generation capacity curve and the load working curve. The volt-ampere characteristics of all the battery strings on the sailboard can be accurately calculated through the algorithm of introducing the combination model and the flight scheme to be combinedto acquire the shielding shape of the sailboard in the flight process to obtain the power generation capacity, and the energy balance situation can be accurately analyzed through combination of the load demand and the energy system design so that the power generation capacity error caused by conventional average shielding or the shielding rate can be eliminated, and the power generation capacity of the sailboard can be accurately predicted.

Description

technical field [0001] The invention relates to an energy management method, in particular to an on-orbit energy management method for an assembly based on energy balance analysis. Background technique [0002] During the in-orbit flight of the combined spacecraft in orbit, the sailboards have many shapes and large shapes, and the sailboard control mode and attitude control mode are complex, resulting in large changes in power generation capacity. The energy balance analysis method of a traditional single spacecraft can no longer meet the energy balance analysis requirements of an on-orbit combined spacecraft, especially the power generation capacity calculated by the average shading or shading rate in the traditional method is difficult to accurately make the calculated power generation capacity and the actual The power consumption of the load is matched, so that there is a large error in the calculated power generation capacity, which leads to an increase in the error of e...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06Q10/06G06Q50/06G06F17/50
CPCG06Q10/0639G06Q50/06G06F30/15
Inventor 姜文彩杨宏何宇刘宏泰任筱强王鹏鹏梁晓锋王宏佳丁锐杜占超
Owner BEIJING SPACE TECH RES & TEST CENT
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