JP6989252B2 - エネルギー効率に優れた衛星の操縦 - Google Patents
エネルギー効率に優れた衛星の操縦 Download PDFInfo
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Description
ここで、τ→ ggは、(衛星100の本体フレーム内の)重力勾配に関するトルクであり、GMは、惑星208の重力定数であり、rは、惑星208の慣性フレーム中心(例えば、惑星208の質量中心)と衛星100の重力の中心との間の距離であり、O→ 3は、軸3に基づいて規定されるベクトル(例えば、ベクトル402)であり、それは、本体フレームの配列の第3の列に基づき、衛星100の重力の中心から惑星208の慣性フレーム中心(例えば、幾何学的中心及び/又は重力の中心)へ延伸し、Iは、衛星100の慣性テンソルである。この実施例では、O→ 3ベクトルは、惑星208に基づいて、本体フレーム(例えば、衛星100の本体リファレンスフレーム)を、軌道フレームに対して調整するために使用される。
ここで、IB’は、主要な慣性テンソルであり、TB’Bは、衛星100の幾何学的本体フレームから重力の中心における主要な軸への変換であり、O3は、軌道フレームに関する衛星100の前述の本体フレームの配列の第3の列であり、TBOは、衛星100の重力中心から惑星208の重力の中心への軌道を表す。数式(2)及び(3)の表記に基づいて、例示的な衛星100の主要な軸において、例示的な衛星100によって経験されるトルクを計算するために、数式4によって以下に表現されるように、O3及びIB’O3の外積が取得される。
ここで、TB’Bは、ある実施例で、[τ→ gg]B’を幾何学的本体フレームの中へ戻すために使用され得る。数式4内で見られ得るように、例示的な衛星100に働くトルクは、異なる方向内の主要な慣性の差異に比例する。最も大幅な主要な慣性の差異が、最も主要な受感軸に対応する。例えば、IX及びIZが同一であれば、yの主要な軸内の重力勾配トルクは、ゼロになるだろう。別の一実施例では、IYが大幅にIX及びIZを下回るならば、IYに対して及び/又はy方向において働くトルクは、最も大きなトルクを生み出し、それによって、IYが最も主要な受感軸であることをもたらす。図5を見ると、図4の主要な受感軸408が、穏やかな軸504、506と同様に示されている。図5の示されている実施例の穏やかな軸504、506は、衛星100が重力勾配トルクに対して受感的でない(すなわち、必要な程度まで受感的でないなど)軸を示している。
Claims (11)
- 衛星の主要な受感軸が軌道フレーム平面に方向付けられ、前記衛星に働く重力勾配トルクを低減させるように、天体の周りの軌道にある前記衛星を操縦することと、
推力ベクトルを、前記主要な受感軸と垂直に位置合わせすることと、
前記衛星の軌道高度を変更するためにスラスタを操作することと、
を含み、前記軌道フレーム平面が、軌道フレームベクトルに基づき、前記軌道フレームベクトルは、前記衛星が周回する前記天体の重力の中心から前記衛星の重力の中心へ規定され、前記軌道フレーム平面は、前記衛星の重力の中心において、前記軌道フレームベクトルに垂直に規定され、前記主要な受感軸は、重力勾配が前記衛星に対して最も高い量のトルクを生成する、前記衛星の軸である、方法。 - 前記衛星を操縦することが、前記衛星の推力ベクトルの周りで前記衛星を回転させることを含む、請求項1に記載の方法。
- 前記主要な受感軸を決定することを更に含む、請求項1又は2に記載の方法。
- 前記衛星を操縦することが、スラスタ又はモーメンタムストレージデバイスのうちの少なくとも一方を起動させることを含む、請求項1から3のいずれか一項に記載の方法。
- 前記軌道の一部分の間で、前記衛星を方向付けることが行われる、請求項1から4のいずれか一項に記載の方法。
- 衛星の操縦デバイス、及び
前記操縦デバイスが、前記衛星の主要な受感軸を軌道フレーム平面に方向付けて、前記衛星に働く重力勾配トルクを低減させることをもたらす、方向付けコントローラであって、前記軌道フレーム平面は、軌道フレームベクトルに基づき、前記軌道フレームベクトルは、前記衛星が周回する天体の重力の中心から前記衛星の重力の中心へ規定され、前記軌道フレーム平面は、前記衛星の重力の中心において、前記軌道フレームベクトルに垂直に規定され、前記主要な受感軸は、重力勾配が前記衛星に対して最も高い量のトルクを生成する、前記衛星の軸である、方向付けコントローラを備える、装置であって、
前記方向付けコントローラはさらに、前記操縦デバイスが推力ベクトルを前記主要な受感軸と垂直に位置合わせすること、及び前記衛星の軌道高度を変更するように前記操縦デバイスがスラスタを操作することをもたらす、装置。 - 前記方向付けコントローラは、前記操縦デバイスが、前記衛星の動作ベクトルを前記軌道フレーム平面に方向付けることをもたらす、請求項6に記載の装置。
- 前記動作ベクトルが推力ベクトルを含む、請求項7に記載の装置。
- 前記操縦デバイスがスラスタを含む、請求項6から8のいずれか一項に記載の装置。
- 前記方向付けコントローラは、前記スラスタが、前記衛星の推力ベクトルを前記主要な受感軸と垂直に方向付けることをもたらす、請求項9に記載の装置。
- 前記操縦デバイスがモーメンタムストレージデバイスを含む、請求項6から10のいずれか一項に記載の装置。
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US14/940,811 US10005568B2 (en) | 2015-11-13 | 2015-11-13 | Energy efficient satellite maneuvering |
US14/940,811 | 2015-11-13 |
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JP2017137040A JP2017137040A (ja) | 2017-08-10 |
JP6989252B2 true JP6989252B2 (ja) | 2022-01-05 |
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EP (1) | EP3170753B1 (ja) |
JP (1) | JP6989252B2 (ja) |
KR (1) | KR102644042B1 (ja) |
CN (1) | CN106697331B (ja) |
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US10005568B2 (en) | 2015-11-13 | 2018-06-26 | The Boeing Company | Energy efficient satellite maneuvering |
FR3047813B1 (fr) * | 2016-02-16 | 2019-11-08 | Airbus Defence And Space Sas | Procede de commande de guidage d'attitude d'un satellite, satellite, pluralites de satellites et programme d'ordinateur associe |
US10569909B2 (en) | 2016-03-30 | 2020-02-25 | The Boeing Company | Systems and methods for satellite orbit and momentum control |
US10543939B2 (en) * | 2018-02-09 | 2020-01-28 | Launchspace Technologies Corporation | Apparatus and methods for creating artificial near-earth orbits |
US11091280B1 (en) * | 2018-06-05 | 2021-08-17 | United States Of America As Represented By The Administrator Of Nasa | Modelling and analyzing inter-satellite relative motion |
US11279501B2 (en) * | 2018-10-25 | 2022-03-22 | General Atomics | Satellite attitude control system using eigen vector, non-linear dynamic inversion, and feedforward control |
CN109649689B (zh) * | 2018-12-07 | 2021-10-01 | 北京空间飞行器总体设计部 | 一种有限推力变轨重力损耗计算方法、推力计算装置 |
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KR20230155576A (ko) * | 2021-03-16 | 2023-11-10 | 에이에스티 앤 사이언스, 엘엘씨 | 우주 내 물체를 위한 운동량 휠 및 반동 휠 |
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