| アイテムタイプ |
学術雑誌論文 = Journal Article(1) |
| 公開日 |
2023-11-15 |
| 資源タイプ |
|
|
資源タイプ識別子 |
http://purl.org/coar/resource_type/c_6501 |
|
資源タイプ |
journal article |
| タイトル |
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|
タイトル |
Scalable and Configurable Electrical Interface Board for Bus System Development of Different CubeSat Platforms |
|
言語 |
en |
| 言語 |
|
|
言語 |
eng |
| 著者 |
Sejera, Marloun
Yamauchi, Takashi
Orger, Necmi Cihan
Otani, Yukihisa
趙, 孟佑
|
| 抄録 |
|
|
内容記述タイプ |
Abstract |
|
内容記述 |
A flight-proven electrical bus system for the 1U CubeSat platform was designed in the BIRDS satellite program at the Kyushu Institute of Technology. The bus utilizes a backplane board as the mechanical and electrical interface between the subsystems and the payloads. The electrical routes on the backplane are configured by software using a complex programmable logic device (CPLD). It allows for reusability in multiple CubeSat projects while lowering costs and development time; as a result, resources can be directed toward developing the mission payloads. Lastly, it provides more time for integration and system-level verification, which are critical for a reliable and successful mission. The current trend of CubeSat launches is focused on 3U and 6U platforms due to their capability to accommodate multiple and complex payloads. Hence, a demonstration of the electrical bus system to adapt to larger platforms is necessary. This study demonstrates the configurable electrical interface board’s scalability in two cases: the capability to accommodate (1) multiple missions and (2) complex payload requirements. In the first case, a 3U-size configurable backplane prototype was designed to handle 13 mission payloads. Four CPLDs were used to manage the limited number of digital interfaces between the existing bus system and the mission payloads. The measured transmission delay was up to 20 ns, which is acceptable for simple serial communications such as UART and SPI. Furthermore, the measured energy consumption of the backplane per ISS orbit was only 28 mWh. Lastly, the designed backplane was proven to be highly reliable as no bit errors were detected throughout the functionality tests. In the second case, a configurable backplane was implemented in a 6U CubeSat with complex payload requirements compared to the 1U CubeSat platform. The CubeSat was deployed in ISS orbit, and the initial on-orbit results indicated that the designed backplane supported missions without issues. |
|
言語 |
en |
| 書誌情報 |
en : Applied Sciences
巻 12,
号 18,
p. 8964,
発行日 2022-09-06
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| 出版社 |
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|
出版者 |
MDPI |
| DOI |
|
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|
識別子タイプ |
DOI |
|
|
関連識別子 |
https://doi.org/10.3390/app12188964 |
| ISSN |
|
|
収録物識別子タイプ |
EISSN |
|
収録物識別子 |
2076-3417 |
| 著作権関連情報 |
|
|
権利情報Resource |
https:// creativecommons.org/licenses/by/ 4.0/ |
|
権利情報 |
Copyright (c) 2022 by the authors. Licensee MDPI, Basel, Switzerland. This article is an open access article distributed under the terms and conditions of the Creative Commons Attribution (CCBY)license. |
| キーワード |
|
|
主題Scheme |
Other |
|
主題 |
CubeSat |
| キーワード |
|
|
主題Scheme |
Other |
|
主題 |
electrical interface |
| キーワード |
|
|
主題Scheme |
Other |
|
主題 |
scalability |
| キーワード |
|
|
主題Scheme |
Other |
|
主題 |
bus system development |
| 出版タイプ |
|
|
出版タイプ |
VoR |
|
出版タイプResource |
http://purl.org/coar/version/c_970fb48d4fbd8a85 |
| 査読の有無 |
|
|
値 |
yes |
LaSEINE-2022_014.pdf (3.1 MB)
