Battery Current and Temperature Mission Profiles for CubeSats at Low Earth Orbit

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F68407700%3A21230%2F22%3A00357883" target="_blank" >RIV/68407700:21230/22:00357883 - isvavai.cz</a>

Výsledek na webu

<a href="https://doi.org/10.1109/TAES.2022.3164867" target="_blank" >https://doi.org/10.1109/TAES.2022.3164867</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.1109/TAES.2022.3164867" target="_blank" >10.1109/TAES.2022.3164867</a>

Jazyk výsledku

angličtina

Název v původním jazyce

Battery Current and Temperature Mission Profiles for CubeSats at Low Earth Orbit

Popis výsledku v původním jazyce

CubeSats, a branch of the space industry, has lately received great interest for being an affordable satellite platform. For proper functioning, they are nowadays practically dependent on Lithium-ion batteries as a power supply at moments, when there is not enough power generated by solar panels. Thus, batteries have to be thoroughly tested to ensure that they provide sufficient performance, lifetime and that they are safe. In other industry areas, such as electric vehicles, it is common to use mission profiles (often referred to as driving profiles) for battery testing to closely emulate conditions that are experienced in practice. However, mission profiles reflecting closely CubeSat conditions are not publicly available. Thus, this paper proposes a methodology to derive mission profiles, and resulting representative mission profiles, dedicated especially to battery testing. The proposed methodology is based on analyzed telemetry data from three GOMX CubeSats. At first, electrical current characteristics are obtained from the telemetry and are generalized across the satellites, to be subsequently used for the mission profile synthesis. The battery temperature is an important factor for the battery performance and lifetime, and it was identified to be very dynamic in CubeSats. Thus, a model describing battery temperature during their mission is proposed to enable generate realistic temperature mission profiles. Finally, the current and temperature profiles are synchronized to capture their mutual impact on the batteries, and they are formulated to be suitable for on-ground (laboratory) testing.

Název v anglickém jazyce

Battery Current and Temperature Mission Profiles for CubeSats at Low Earth Orbit

Popis výsledku anglicky

CubeSats, a branch of the space industry, has lately received great interest for being an affordable satellite platform. For proper functioning, they are nowadays practically dependent on Lithium-ion batteries as a power supply at moments, when there is not enough power generated by solar panels. Thus, batteries have to be thoroughly tested to ensure that they provide sufficient performance, lifetime and that they are safe. In other industry areas, such as electric vehicles, it is common to use mission profiles (often referred to as driving profiles) for battery testing to closely emulate conditions that are experienced in practice. However, mission profiles reflecting closely CubeSat conditions are not publicly available. Thus, this paper proposes a methodology to derive mission profiles, and resulting representative mission profiles, dedicated especially to battery testing. The proposed methodology is based on analyzed telemetry data from three GOMX CubeSats. At first, electrical current characteristics are obtained from the telemetry and are generalized across the satellites, to be subsequently used for the mission profile synthesis. The battery temperature is an important factor for the battery performance and lifetime, and it was identified to be very dynamic in CubeSats. Thus, a model describing battery temperature during their mission is proposed to enable generate realistic temperature mission profiles. Finally, the current and temperature profiles are synchronized to capture their mutual impact on the batteries, and they are formulated to be suitable for on-ground (laboratory) testing.

Druh

J_imp - Článek v periodiku v databázi Web of Science

CEP obor

—

OECD FORD obor

20201 - Electrical and electronic engineering

Projekt

—

Návaznosti

I - Institucionalni podpora na dlouhodoby koncepcni rozvoj vyzkumne organizace

Rok uplatnění

2022

Kód důvěrnosti údajů

S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů

Název periodika

IEEE Transactions on Aerospace and Electronic Systems

ISSN

0018-9251

e-ISSN

1557-9603

Svazek periodika

58

Číslo periodika v rámci svazku

5

Stát vydavatele periodika

US - Spojené státy americké

Počet stran výsledku

13

Strana od-do

4656-4668

Kód UT WoS článku

000866503000069

EID výsledku v databázi Scopus

2-s2.0-85127731721