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ナノ衛星の展開するソーラーパネル上の熱誘導ダイナミクスと太陽放射トルク
https://doi.org/10.18997/00007796
https://doi.org/10.18997/0000779633058a12-ddbd-45d2-b046-9015cfda0815
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
kou_k_488.pdf (2.9 MB)
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| Item type | 学位論文 = Thesis or Dissertation(1) | |||||||
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| 公開日 | 2020-06-10 | |||||||
| 資源タイプ | ||||||||
| 資源タイプ識別子 | http://purl.org/coar/resource_type/c_db06 | |||||||
| 資源タイプ | doctoral thesis | |||||||
| タイトル | ||||||||
| タイトル | Thermally Induced Dynamics and Solar Radiation Torque on Deployable Solar Panels of Nanosatellite | |||||||
| 言語 | en | |||||||
| タイトル | ||||||||
| タイトル | ナノ衛星の展開するソーラーパネル上の熱誘導ダイナミクスと太陽放射トルク | |||||||
| 言語 | ja | |||||||
| 言語 | ||||||||
| 言語 | eng | |||||||
| 著者 |
Syahrim Azhan bin Ibrahim
× Syahrim Azhan bin Ibrahim
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| 抄録 | ||||||||
| 内容記述タイプ | Abstract | |||||||
| 内容記述 | Small satellites in low-Earth orbit （LEO） often experience energy constrictions owing to small solar panel areas and eclipse transitions. Much like larger satellites, these small satellites, including nanosatellite class such as CubeSats always opt for deployable solar panels to generate more power. By using deployable solar panels, the satellite’s surface that faces the Sun will be more exposed; yet, the force generated by the pressure of solar radiation can disrupt spacecraft orbits. For the time being, the study on deployable solar panels for CubeSats has largely focused on panel configuration, deployment mechanism, deployment mechanics and dynamics, and power harnessing capacity. Meanwhile, when dealing with solar radiation pressure, the interest is largely on its use as a thrust force to control satellite trajectories. An apparent research gap is addressed on the thermal effects of solar radiation, as well as on the increase in solar radiation pressure, to CubeSats with deployable solar panels. This study is divided into two parts. First, a methodology is presented to predict the types of thermally induced dynamics （TID） that can occur on deployable solar panels of a CubeSat in LEO. A computational method combining finite difference method and finite element method is developed to examine the TID effect on the CubeSat body. A 3U CubeSat with four short-edged deployable solar panels, has been considered. Time historic temperature readings of the solar panels operating in-orbit are obtained using a thermal analysis software. The results are used in a numerical analysis software to identify the structural response of the solar panel. Next, the effect of solar panels’ sudden motion on the satellite’s pointing direction is examined through a static analysis with inertia relief. A thermal snap motion could occur during eclipse transitions due to rapid temperature changes in the solar panels’ cross-sections. In the case of asymmetric solar panel configuration, noticeable displacements in the pointing direction can be observed during the eclipse transitions. This work only examines an LEO mission, where the solar cells on the solar panels are directly exposed to sunlight throughout daylight and pointed to the Earth while orbiting in shadow. Simplification is made to the CubeSat’s structure and in some parameters of the space environment. The conducted TID analysis reveals the effect of TID phenomenon on deployable solar panels and the CubeSat’s pointing direction. Therefore, in a situation of partial solar panel deployment, or in an asymmetric deployable solar panel design configuration, the attitude control system designer could anticipate the order of the required magnitude motions to mitigate the disturbance. In addition, the methodology developed in this research can be applied to simplify the study of TID on satellite appendages. In the second part of the study, solar radiation torque characteristics consequential from the solar panels’ enlarged surface on the CubeSats are investigated. Three commonly used, commercially available solar panel configurations are introduced and their reference missions are established for comparative purposes. The software algorithms used to simulate various orbital situations are described in detail and some issues are highlighted based on the observed results. The solar power generated for each corresponding configuration is also presented. The obtained data on solar radiation torque and generated solar power are intended to be used by designers of nanosatellite to predict the characteristics of solar radiation torques to be encountered and the solar power to be generated when applying a variety of deployable solar panels; hence, aiding them to choose appropriate panel configuration and attitude control system for their design. Furthermore, the methodology and algorithm employed should provide insight on how to develop the source code for calculating the in-orbit solar radiation and solar power. | |||||||
| 言語 | en | |||||||
| 目次 | ||||||||
| 内容記述タイプ | TableOfContents | |||||||
| 内容記述 | 1: Introduction||2: Thermally Induced Dynamics of Deployable Solar Panels of Nanosatellite||3: Comparison of Solar Radiation Torque and Power Generation on Deployable Solar Panels Configurations of Nanosatellite||4: Conclusions and Future Work | |||||||
| 備考 | ||||||||
| 内容記述タイプ | Other | |||||||
| 内容記述 | 九州工業大学博士学位論文 学位記番号：工博甲第488号 学位授与年月日：令和2年3月25日 | |||||||
| キーワード | ||||||||
| 主題Scheme | Other | |||||||
| 主題 | CubeSat | |||||||
| キーワード | ||||||||
| 主題Scheme | Other | |||||||
| 主題 | Thermally induced dynamics | |||||||
| キーワード | ||||||||
| 主題Scheme | Other | |||||||
| 主題 | Deployable solar panel | |||||||
| キーワード | ||||||||
| 主題Scheme | Other | |||||||
| 主題 | Inertia Relief | |||||||
| キーワード | ||||||||
| 主題Scheme | Other | |||||||
| 主題 | Solar radiation torque | |||||||
| アドバイザー | ||||||||
| 山口, 栄輝 | ||||||||
| 学位授与番号 | ||||||||
| 学位授与番号 | 甲第488号 | |||||||
| 学位名 | ||||||||
| 学位名 | 博士（工学） | |||||||
| 学位授与年月日 | ||||||||
| 学位授与年月日 | 2020-03-25 | |||||||
| 学位授与機関 | ||||||||
| 学位授与機関識別子Scheme | kakenhi | |||||||
| 学位授与機関識別子 | 17104 | |||||||
| 学位授与機関名 | 九州工業大学 | |||||||
| 学位授与年度 | ||||||||
| 内容記述タイプ | Other | |||||||
| 内容記述 | 令和元年度 | |||||||
| 出版タイプ | ||||||||
| 出版タイプ | VoR | |||||||
| 出版タイプResource | http://purl.org/coar/version/c_970fb48d4fbd8a85 | |||||||
| アクセス権 | ||||||||
| アクセス権 | open access | |||||||
| アクセス権URI | http://purl.org/coar/access_right/c_abf2 | |||||||
| ID登録 | ||||||||
| ID登録 | 10.18997/00007796 | |||||||
| ID登録タイプ | JaLC | |||||||
