JP6872545B2 - 展開可能な構成要素を備えた航空機 - Google Patents
展開可能な構成要素を備えた航空機 Download PDFInfo
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Description
この概要は、以下でさらに説明する概念の選択を簡略化した形で紹介するために提供される。この概要は、特許請求される主題の重要な特徴または本質的な特徴を特定するものではない。この概要は、特許請求される主題の範囲を制限するために使用されるものでもない。
・航続時間を増加させる空気力学的効率の改善。
・最大積載量の増加。
・パラシュートまたはバルーンのような外部空気力学的処理の助けを借りない発射および飛行への移行。
・任務能力の最大化(すなわち、モジュール式ペイロードおよび再構成可能で高効率の機体により、例えば、これらに限定されないが、情報・監視・偵察(ISR)、シグナル・インテリジェンス(SIGINT)、天気、地球物理、環境などのより多様な任務をUAVDCが効率的に実行できるようにする。
図1Cは、本開示の実施形態に従うUAVDCを示す。本開示の実施形態は、胴体106と、1つまたは複数のアンテナ705と、電源1310と、スイープするおよび/または入れ子式に伸縮するように構成され得る翼110と、安定板125と、ペイロード140とを備え得る。さらなる実施形態は、例えば、プロペラ135のような推進機構を備え得る。
図14は、UAVDCを操作するための本開示の一実施形態に従う方法1400に含まれる一般的な段階を示すフローチャートである。方法1400は、図15に関して以下でより詳細に説明されているように、少なくとも部分的にコントローラ1500(例えば、搭載コンピューティングデバイス)を使用して実施され得る。コントローラ1500は、展開可能な構成要素を操作するだけでなく、飛行制御、ペイロード操作、および通信を含むがこれらに限定されない他の任務詳細を実行するためのコントローラを備え得る。したがって、コントローラ1500は、動作可能な構成であり、例えば、これらに限定されないが、モジュール式ペイロード140、スイープギアボックスアクチュエータ210、補助翼120用の制御機構(例えば、サーボ機構1320)、安定板125用のサーボ機構410、プロペラ135を駆動するためのモータ1315、電源1310、慣性計測装置、全地球測位システム、様々なテレメトリセンサ、およびアンテナ705、さらに他の全てのユニットと通信状態であり得る。図15を参照して詳細に説明するように、コントローラ1500は、アンテナ705に関して上述したような遠隔操作を可能にする遠隔通信モジュールを備え得る。他の実施形態では、コントローラ1500は、構成時に完全に自己操作式であり得る。このように、UAVDCは自己操縦式であり得る。
UAVDCは、搭載コンピューティングモジュールを備え得るが、これに限定されない。コンピューティングモジュールは、動作可能な構成であり、例えば、これらに限定されないが、モジュール式ペイロード140、スイープギアボックスアクチュエータ210、補助翼120用の制御機構(例えば、サーボ機構1320)、安定板125用のサーボ機構410、プロペラ135を駆動するためのモータ1315、電源1310、全地球測位システム、様々なテレメトリセンサ、およびアンテナ705と通信状態であり得る。さらに、コンピューティングデバイスは、本明細書内の説明に従う別のコンピューティングデバイスと動作可能な通信状態であり得、デスクトップコンピュータ、ラップトップ、タブレット、または移動体通信デバイスを備え得るが、これらに限定されない。このような遠隔装置は、搭載コンピューティングモジュール(例えば、展開条件、任務制御など)を制御および/または構成するために使用され得る。
Claims (15)
- 展開可能な構成要素を備えた無人航空機(UAVDC)であって、
胴体と、
左翼部と右翼部との間のほぼ対称な側面で可変スイープを可能にするための前記左翼部と前記右翼部に分割された翼配置であって、前記翼配置は、第1の配置、第2の配置、第3の配置で構成可能であり、
前記第1の配置は、第1のスイープ展開角度で前記胴体に寄せて格納された前記左翼部および前記右翼部を備え、
前記第2の配置は、第2のスイープ展開角度で飛行するために完全に展開された前記翼配置を備え、
前記第3の配置は、前記第1のスイープ展開角度と前記第2のスイープ展開角度との間の任意のスイープ展開角度で展開された前記翼配置を備える、翼配置と、
前記左翼部および前記右翼部を枢動させて、前記翼配置を前記第1の配置から前記第2の配置に任意のスイープ展開角度でスイープさせることができるように構成されたスイープ手段と
を備え、
前記スイープ手段は、前記左翼部および前記右翼部の根元に位置決めされたフェアリングによって覆われ、前記フェアリングは、少なくとも1つのスリットおよび少なくとも1つの切欠きを備える可撓性材料で構成され、前記フェアリングは、前記第1の配置において前記左翼部および前記右翼部を収容するために前記少なくとも1つのスリットの位置で撓むように構成される、UAVDC。 - 前記翼配置は、前記第2の配置の翼幅を増加させるために入れ子式に伸長するようにさらに構成される、請求項1に記載のUAVDC。
- 前記左翼部および前記右翼部は、前記第1の配置において、前記左翼部が前記右翼部から垂直方向にオフセットされた状態で前記胴体に対して積み重ねられる、請求項1に記載のUAVDC。
- 前記フェアリングは、
前記左翼部と前記右翼部とが前記第1の配置において前記フェアリングの下に格納されるように撓むことによって開放され、
前記第2の配置において空気力学的な利点を提供するように閉鎖される
ように構成される、請求項3に記載のUAVDC。 - 前記フェアリングの前記切欠きは、前記第2の配置における前記左翼部および前記右翼部の前記根元の外形に適応するように構成される、請求項4に記載のUAVDC。
- 前記フェアリングは、前記左翼部および前記右翼部の前記第1の配置に対応する開放形態において第1の張力を生じさせ、前記第1の張力は、前記左翼部および前記右翼部が前記第2の配置に達したときに、前記フェアリングを閉鎖させる、請求項4に記載のUAVDC。
- 前記フェアリングは、前記第2の配置に適応するように前記少なくとも1つのスリットの位置で撓まない、請求項6に記載のUAVDC。
- 前記左翼部および前記右翼部の前記第2の配置に対応する閉鎖形態において、前記フェアリングを前記胴体に固定するように構成された磁石をさらに備える、請求項4に記載のUAVDC。
- 前記フェアリングは、+/−45度の複合層を使用することによって複合積層体の可撓性を促進するような配向で構成される、請求項4に記載のUAVDC。
- 第1の展開角度で前記胴体に寄せて格納された第1の安定板形態から第2の展開角度で飛行するために展開された第2の安定板形態へと展開するように構成された少なくとも1つの安定板をさらに備え、前記少なくとも1つの安定板は、前記第2の安定板形態にある間に正の飛行制御を提供するためにその幅方向の軸を中心として偏向/回転することができる、請求項1に記載のUAVDC。
- 少なくとも1つのバネであって、前記少なくとも1つの安定板を前記第1の安定板形態から前記第2の安定板形態へと付勢するように構成された少なくとも1つのバネ、或いは
前記少なくとも1つの安定板をその幅方向の軸を中心として回転させるために前記少なくとも1つの安定板に結合された制御ホーンを移動させるように構成されたサーボ機構であって、前記制御ホーンは、前記少なくとも1つの安定板が前記第1の安定板形態から前記第2の安定板形態へと展開するときに、相対的に固定された位置でとどまるように構成される、サーボ機構
をさらに備える、請求項10に記載のUAVDC。 - プロペラをさらに備え、前記プロペラは、第1のプロペラ配置になるように折り畳まれ、第2のプロペラ配置において伸張するように構成された少なくとも1つの羽根を備える、請求項1に記載のUAVDC。
- 前記胴体は、前記第1のプロペラ配置において、前記プロペラの少なくとも1つの羽根を受容するように構成された少なくとも1つの溝を備え、前記プロペラは、プロペラ羽根バネ、空気力学的な力、または前記プロペラの回転による求心力のうちの少なくとも1つを使用して、前記第2のプロペラ配置へと開くように構成され、或いは、前記少なくとも1つの羽根は、前記UAVDCが飛行中に前記少なくとも1つの羽根が主流の中に入るように、前記第2のプロペラ配置において開くように構成される、請求項12に記載のUAVDC。
- モジュール式ペイロード胴体部分をさらに備える、請求項1に記載のUAVDC。
- ペイロードは、前記胴体内の少なくとも1つのスロット内を移動するように構成された少なくとも1つの突起を備え、前記ペイロードは、ブームに取り付けられるように構成され、前記ブームは、第1のペイロード配置から第2のペイロード配置へと移動するように構成され、前記第1のペイロード配置から前記第2のペイロード配置へと前記ペイロードの展開をトリガするように構成されたコントローラをさらに備える、請求項1に記載のUAVDC。
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