JP6301980B2 - エレボン制御システム - Google Patents
エレボン制御システム Download PDFInfo
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Description
本願は、2009年9月9日に出願された米国仮特許出願第61/240,985号明細書の優先権を主張し、その特典を請求するものであり、かかる出願は、あらゆる目的のためにその全体が参照により本明細書に組み込まれる。
Claims (39)
- 発射筒内に格納され、当該発射筒から出た後に展開可能な航空機において:
外面を有する胴体と;
第1の一対の翼であって、当該対の各近位部分が、前記外面の一つの前方ピボット点に回転可能に取り付けられている第1の一対の翼と;
第2の一対の翼であって、当該対の各近位部分が、前記外面の一つの機尾ピボット点に回転可能に取り付けられている第2の一対の翼と;を具え、
前記第1の一対の翼が、前記第2の一対の翼の格納位置と整列している格納位置に対して回転できるように構成されており、前記第1の一対の翼がその格納位置にあるときに、前記第1の一対の翼の翼端が前記機尾ピボット点の近くに配置され、前記第2の一対の翼がその格納位置にあるときに、前記第2の一対の翼の翼端が前記前方ピボット点の近くに配置され、
前記格納位置において、前記第1の一対の翼と前記第2の一対の翼が、前記胴体の幅の内側に格納され、すべての翼と前記胴体との間に隙間がないことを特徴とする航空機。 - 請求項1に記載の航空機において、前記第1の一対の翼の各近位部分が、第1の同軸ピボット点に回転可能に取り付けられていることを特徴とする航空機。
- 請求項2に記載の航空機において、前記第2の一対の翼の各近位部分が、第2の同軸ピボット点に回転可能に取り付けられていることを特徴とする航空機。
- 請求項1に記載の航空機において、前記第1の一対の翼の各々が、前記外面に沿って配置された格納位置を有することを特徴とする航空機。
- 請求項4に記載の航空機において、前記第2の一対の翼の各々が、前記外面に沿って配置された格納位置を有することを特徴とする航空機。
- 請求項5に記載の航空機において、前記第2の一対の翼がさらに、機尾左側翼と機尾右側翼とを具えており、当該左側と右側の翼が、前記格納位置にあるときに、実質的に重なって整列していることを特徴とする航空機。
- 請求項6に記載の航空機において、前記第1および第2の一対の翼が、それぞれの格納位置にあるときに重なっていることを特徴とする航空機。
- 請求項5に記載の航空機において、前記第1および第2の一対の翼のそれぞれが、前記胴体の同じ側に格納位置を有することを特徴とする航空機。
- 請求項8に記載の航空機において、前記第1および第2の一対の翼が、それぞれの格納位置にあるときに、前記外面の第1のほぼ平らな部分に近接して配置されていることを特徴とする航空機。
- 請求項1に記載の航空機において、前記第1および第2の一対の翼が、それぞれの翼長に沿って一定の翼弦を有することを特徴とする航空機。
- 請求項10に記載の航空機において、前記それぞれの翼弦が、ほぼ胴体の最大幅であることを特徴とする航空機。
- 請求項1に記載の航空機において、前記第1の一対の翼が、それぞれの回転面で回転可能であることを特徴とする航空機。
- 発射筒内に格納され、当該発射筒から出た後に展開可能な航空機の操作方法において:
重なった第1の一対の翼を、第1の回転位置から第2の回転位置に、胴体の外面上の一つの前方ピボット点の周りを回転させるステップと;
重なった第2の一対の翼を、第3の回転位置から第4の回転位置に、前記胴体の外面上の一つの機尾ピボット点の周りを回転させるステップと;を具え、
前記重なった第1の一対の翼の第1の回転位置が、前記重なった第2の一対の翼の第3の回転位置と整列しており、前記第1の一対の翼が前記第1の回転位置にあるときに、前記重なった第1の一対の翼の翼端が前記機尾ピボット点の近くに配置され、前記重なった第2の一対の翼がその第3の回転位置にあるときに、前記重なった第2の一対の翼の翼端が前記前方ピボット点の近くに配置され、
前記第1および第3の回転位置における格納位置において、前記第1の一対の翼と前記第2の一対の翼が、前記胴体の幅の内側に格納され、すべての翼と前記胴体との間に隙間がないことを特徴とする方法。 - 請求項13に記載の方法において、前記重なった第1の一対の翼を第1の回転位置から第2の回転位置に回転させるステップが、さらに、前記重なった第1の一対の翼を、前記胴体の外面に沿って配置された格納位置から展開位置に回転させるステップを具えることを特徴とする方法。
- 請求項14に記載の方法において、前記重なった第1の一対の翼が、その格納位置にあるときに、前記前方と機尾のピボット点の間に整列していることを特徴とする方法。
- 請求項14に記載の方法において、前記重なった第2の一対の翼を第3の回転位置から第4の回転位置に回転させるステップが、さらに、前記重なった第2の一対の翼を、前記胴体の外面に沿って配置された格納位置から展開位置に回転させるステップを具えることを特徴とする方法。
- 請求項16に記載の方法において、前記重なった第2の一対の翼が、その格納位置にあるときに、前記前方と機尾のピボット点の間に整列していることを特徴とする方法。
- 請求項16に記載の方法において、前記重なった第1の一対の翼がその格納位置にあるときに、前記重なった第1の一対の翼の翼端が前記機尾ピボット点の近くに配置されることを特徴とする方法。
- 請求項16に記載の方法において、前記重なった第2の一対の翼がその格納位置にあるときに、前記重なった第2の一対の翼の翼端が前記前方ピボット点の近くに配置されることを特徴とする方法。
- 請求項16に記載の方法において、前記重なった第1および第2の一対の翼がそれぞれの格納位置からそれぞれの展開位置に移行したときに、前記重なった第1の一対の翼の両翼が、前記重なった第2の一対の翼の両翼が形成する鋭角と対向する逆の鋭角をはじめに形成するように構成されていることを特徴とする方法。
- 請求項20に記載の方法において、前記重なった第1の一対の翼が、その格納位置から展開位置に移行するときに、機尾の位置から前方位置に回転することを特徴とする方法。
- 請求項20に記載の方法において、前記重なった第2の一対の翼が、その格納位置から展開位置に移行するときに、前方位置から機尾の位置に回転することを特徴とする方法。
- 請求項13に記載の方法において、前記重なった第1および第2の翼の格納位置が、前記外面の第1の側面にあることを特徴とする方法。
- 請求項13に記載の方法において、前記重なった第1の一対の翼を第1の回転位置から第2の回転位置に回転させるステップが、前記第1の一対の翼をそれぞれの回転面で回転させるステップを具えることを特徴とする方法。
- 請求項24に記載の方法において、前記それぞれの回転面が、平行な回転面であることを特徴とする方法。
- 発射筒内に格納され、当該発射筒から出た後に展開可能な航空機において:
外面を有する胴体と;
第1の一対の翼であって、当該対の各近位部分が、重なる構成で配置されているとともに、前記外面の一つの前方ピボット点に回転可能に取り付けられている第1の一対の翼と;
第2の一対の翼であって、当該対の各近位部分が、重なる構成で配置されているとともに、前記外面の一つの機尾ピボット点に回転可能に取り付けられている第2の一対の翼と;を具え、
前記前方と機尾のピボット点が胴体の長手軸に同一線上に配置されており、前記第1の一対の翼が、前方の同軸ピボット点の周りを回転可能に配置され、前記第2の一対の翼が、機尾の同軸ピボット点の周りを回転可能に配置されており、前記前方と機尾の同軸ピボット点が、胴体の中心線に同一線上に配置されており、
前記重なる構成における格納位置において、前記第1の一対の翼と前記第2の一対の翼が、前記胴体の幅の内側に格納され、すべての翼と前記胴体との間に隙間がないことを特徴とする航空機。 - 請求項26に記載の航空機において、前記第2の一対の翼の各々が、前記外面に沿って配置された格納位置を有することを特徴とする航空機。
- 請求項27に記載の航空機において、前記第1の一対の翼の各々が、前記第2の一対の翼の各々の格納位置と整列している格納位置を有することを特徴とする航空機。
- 請求項28に記載の航空機において、前記第1および第2の一対の翼が、それぞれの格納位置にあるときに重なっていることを特徴とする航空機。
- 請求項26に記載の航空機において、前記第1の一対の翼が、それぞれの回転面で回転可能であることを特徴とする航空機。
- 請求項30に記載の航空機において、前記第2の一対の翼が、それぞれの回転面で回転可能であることを特徴とする航空機。
- 請求項31に記載の航空機において、前記第1および第2の一対の翼の回転面が、平行な回転面であることを特長とする航空機。
- 発射筒内に格納され、当該発射筒から出た後に展開可能な無人航空機(UAV)において:
胴体面と;
前記胴体面の前方ピボット領域の周りを回転可能に配置された第1の翼と;
前記胴体面の前方ピボット領域の周りを回転可能に配置された第2の翼と;
前記胴体面の機尾ピボット領域の周りを回転可能に配置された第3の翼と;
前記胴体面の機尾ピボット領域の周りを回転可能に配置された第4の翼と;を具え、
前記胴体面の前方ピボット領域が一つの前方ピボット点を具え、前記胴体面の機尾ピボット領域が一つの機尾ピボット点を具えており、前記前方と機尾のピボット点が胴体の長手軸に同一線上にあり、前記第1および第2の翼のそれぞれが、前方の同軸ピボット点の周りを回転可能に配置され、前記第3および第4の翼が、機尾の同軸ピボット点の周りを回転可能に配置されており、前記前方と機尾の同軸ピボット点が、胴体の中心線に同一線上に配置されており、
格納位置において、前記第1、第2、第3および第4の翼が、前記胴体の幅の内側に格納され、すべての翼と前記胴体との間に隙間がない
いることを特徴とする無人航空機。 - 請求項33に記載のUAVにおいて、前記第1および第2の翼が、それぞれの操縦面を具えていることを特徴とするUAV。
- 請求項33に記載のUAVにおいて、前記第1の翼が、前記胴体面の前方ピボット領域と前記第2の翼との間に挟まれた第1の回転面を回転するように構成されており、前記第2の翼が、前記第1の回転面と平行な第2の回転面を有することを特徴とするUAV。
- 請求項33に記載のUAVにおいて、前記第1の翼が、前記胴体面の前方ピボット領域と前記第2の翼との間に挟まれた第1の回転面を回転するように構成されており、前記第2の翼が、前記第1の回転面と同一平面状の第2の回転面を有することを特徴とするUAV。
- 請求項33に記載のUAVにおいて、前記第1および第2の翼がそれぞれの格納位置から前方に回転するように構成されており、前記第3および第4の翼がそれぞれの格納位置から後方に回転するように構成されていることを特徴とするUAV。
- 発射筒内に格納され、当該発射筒から出た後に展開可能な無人航空機(UAV)において:
外面と最大の胴体幅を有する胴体と;
前記外面の一つの前方ピボット点に同軸上に回転可能に取り付けられた第1の一対の重なった翼であって、それぞれが前記最大の胴体幅とほぼ等しい一定の翼弦を翼長に沿って有している第1の一対の重なった翼と;
前記外面の一つの機尾ピボット点に同軸上に回転可能に取り付けられた第2の一対の重なった翼であって、それぞれが前記最大の胴体幅とほぼ等しい一定の翼弦を翼長に沿って有しており、前記前方および機尾のピボット点が、前記胴体の中心線に同一線上に配置されている第2の一対の重なった翼と;を具え、
前記第1の一対の重なった翼が、前記第2の一対の翼の格納位置と整列している格納位置に回転できるように構成されており、前記第1の一対の重なった翼がその格納位置にあるときに、前記第1の一対の重なった翼の翼端が前記機尾ピボット点の近くに配置され、前記第2の一対の重なった翼がその格納位置にあるときに、前記第2の一対の重なった翼の翼端が前記前方ピボット点の近くに配置され、
前記格納位置において、前記第1の一対の重なった翼と前記第2の一対の重なった翼が、前記胴体の幅の内側に格納され、すべての翼と前記胴体との間に隙間がないことを特徴とする無人航空機。 - 請求項38に記載のUAVにおいて、前記外面が上外面と底外面とを具えており、前記第2の一対の重なった翼が、前記底外面に同軸上に回転可能に取り付けられていることを特徴とするUAV。
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