Abstract To progress towards as quick as possible feasible pre-design of space missions, spacecraft early design today is organized gathering together experts from different spacecraft subsystems that share information (and results). This Concurrent Design (CD) approach needs accurate but quick solutions from all subsystems involved in each phase of that mission early design. At IDR/UPM Institute researchers have been working in simplified models for the spacecraft power distribution subsystem. In the present paper three models, for solar panels, the battery and DC-DC converters are described and tested with experimental data. The models were designed to be coupled within the simulation of a spacecraft mission. The model regarding the solar panels is focused on accurately estimate the power production from the panels, whereas the model of the batteries is based on the discharged energy rate as the main/control parameter instead of the discharged/charged ampere·hour rate. Finally, the solar-panels/battery coupled design is described in this paper, the UPMSat-2 mission being used as case study.
Highlights The testing results related DC-DC spacecraft converters are used to model these parts. Spacecraft solar panels are modeled with simplified approaches based on information from the manufacturer. A simple model for Li-ion battery performance is proposed. The power system of the UPMSat-2 spacecraft mission is simulated. DET and MPPT are compared, DET being more efficient for the UPMSat-2 mission.
Simple solar panels/battery modeling for spacecraft power distribution systems
Acta Astronautica ; 179 ; 345-358
2020-10-16
14 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Simple Mathematical Models for the Dynamics of Spacecraft with Deployed Solar Panels
Online Contents | 2014
|METHOD FOR DETERMINING MAXIMUM OUTPUT POWER OF SPACECRAFT SOLAR PANELS
Europäisches Patentamt | 2017
|METHOD FOR DETERMINING THE OUTPUT POWER OF SOLAR PANELS OF SPACECRAFT
Europäisches Patentamt | 2017
|