JP2010524765A - 環状航空機体 - Google Patents
環状航空機体 Download PDFInfo
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- JP2010524765A JP2010524765A JP2010503578A JP2010503578A JP2010524765A JP 2010524765 A JP2010524765 A JP 2010524765A JP 2010503578 A JP2010503578 A JP 2010503578A JP 2010503578 A JP2010503578 A JP 2010503578A JP 2010524765 A JP2010524765 A JP 2010524765A
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Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/06—Aircraft not otherwise provided for having disc- or ring-shaped wings
- B64C39/062—Aircraft not otherwise provided for having disc- or ring-shaped wings having annular wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
- B64U30/26—Ducted or shrouded rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/18—Thrust vectoring
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
- B64U2101/30—UAVs specially adapted for particular uses or applications for imaging, photography or videography
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/13—Propulsion using external fans or propellers
- B64U50/14—Propulsion using external fans or propellers ducted or shrouded
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Toys (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
- Air-Flow Control Members (AREA)
- Air-Conditioning For Vehicles (AREA)
- Blow-Moulding Or Thermoforming Of Plastics Or The Like (AREA)
- General Factory Administration (AREA)
- Ink Jet Recording Methods And Recording Media Thereof (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Transmission Devices (AREA)
- Fittings On The Vehicle Exterior For Carrying Loads, And Devices For Holding Or Mounting Articles (AREA)
Abstract
Description
AR=B2/S
(B=スパン、S=突出プラットフォーム面積)
であり、これは、最大効率が空力弾性の制約と釣り合わなければならず、翼構造が過酷な天候または離着陸中に誘起される他の応力に耐えなければならない場合の細長い翼を形成する。したがって、それらのUAVは、航続時間、範囲、燃料効率、あるいは積載容量に関してより良好な性能を与えるために、改良された機体形状を必要とする。
環状機体の重力の中心がその圧力中心からより容易に分離され、したがって、ピッチ安定性においてより良好な静止および動的余裕を与える。
従来の平面状前進傾斜翼に過剰の張力またはフラッター負荷を与える空気弾性力は、翼体の弾力性のある環状構造によって効率的に補強されおよび減衰される。
前進傾斜の要素は機体に比較的高い迎え角に対して失速し難い耐性を与え、これは着陸、離陸、または他の機動を行うとき重要である。
前進傾斜の要素はいくつかの状況において、抗力対揚力比を改善する。
AR=2B2/S
ここで、Bは翼体のスパン(翼体の最大外径で定義される)であり、Sは翼体の突出したプラットフォーム面積である。
AR=2B2/S
から誘導され、AR=16である。
Sr=t2/Cmr
は0.5〜5に変化することができ、スロットによって作られる縦の高さHsrは環状体の高さHの0.3〜0.8倍で変化することができる。各方向舵要素は適切な翼形を組み込んで平滑な空気力学的流れをその個別表面に沿って確保し、正確な翼形形状は環状翼体の他の部分に適用されるものと類似しており、必要であれば、方向舵翼弦の減少に伴うレイノルド数の変化を調整する。
・ダクトが適切な間仕切りによって2つ以上の個別ダクトに分割される実施形態。
・外部翼体自体が2つ以上の個別ダクトを形成する実施形態。
・外部翼体が翼体軸の周りを360度未満の角度で回転対として翼形を形成する実施形態。この場合、閉じる替わりに、ダクトはその長さに沿って走るスロットで部分的に開かれる。角度を180度より大きく、好ましくは360度近くにすることによって、翼体は回転のあらゆる角度で空気力学的揚力を提供するように略環状を維持する。
Claims (22)
- 翼体軸を形成するとともに該翼体軸に沿って観察した場合に略環状の環状体とされ、該環状体の内部が両端で開口するダクトを形成する翼体と、
1対以上の推進装置を備え、各対が前記翼体に搭載されるとともに前記翼体軸を含む面の第1の側に配置される第1推進装置と、前記翼体に搭載されるとともに前記翼体軸を含む面の第2の側に配置された前記第1推進装置とは独立に運転可能な第2推進装置とを有する推進システムと、を有する航空機体。 - 前記第1推進装置の推力の方向が、前記第2推進装置の推力の方向とは独立に調整可能な請求項1に記載の機体。
- 前記第1推進装置の推力の方向が、前記推進装置を回転することによって前記第2推進装置の推力の方向とは独立に調整可能な請求項2に記載の機体。
- 各推進装置が推力発生機と推力発生機からの推進ガスを受け取るように配置された複数のダクトとを備え、前記第1推進装置の推力の方向は、前記ダクト中の推進ガスの流れを調整することによって前記第2推進装置の推力とは独立に調整可能な請求項2に記載の機体。
- 各ダクトが翼体内に含まれる請求項4に記載の機体。
- 各推進装置の推力ベクトルが、推力ベクトルが同一方向である第1構成と推力ベクトルが逆方向である第2構成との間で調整可能な請求項1から5のいずれか一項に記載の機体。
- 前記翼体の少なくとも一部が翼体軸に対して傾斜する請求項1から6のいずれか一項に記載の機体。
- 前記翼体が第1観察角度から観察した場合に前進傾斜とされ、第1観察角度に直角の第2観察位置から観察した場合に後退傾斜とされる請求項7に記載の機体。
- 前記外部翼体が立面図で観察した場合に前進傾斜とされ、平面図で観察した場合に後退傾斜とされる請求項8に記載の機体。
- 前記第1推進装置が前記翼体軸を含む垂直面の第1の側に位置し、前記第2推進装置が前記翼体軸を含む垂直面の第2の側に位置する請求項1から9のいずれか一項に記載の機体。
- 前記推進装置にそれぞれの制御信号を発信することによって前記推進装置を独立に運転するように構成された制御装置をさらに含む請求項1から10のいずれか一項に記載の機体。
- 翼体軸を形成するとともに該翼体軸に沿って観察した場合に略環状の環状体とされ、該環状体の内部が両端で開口するダクトを形成する翼体を有し、該翼体が第1観察角度から観察した場合に前進傾斜とされ、第1観察角度に直角の第2観察角度から観察した場合に後退傾斜とされる航空機体。
- 前記翼体が平面図で観察した場合に前進傾斜とされ、立面図で観察した場合に後退傾斜とされる請求項12に記載の機体。
- 前記翼体が2つ以上のノーズを備えた前縁部と、2つ以上のテールを備えた後縁部とを有する請求項12または13に記載の機体。
- 前記ノーズが前記テールに対して回転オフセットを有する請求項14に記載の機体。
- 前記翼体の前記前縁部およびまたは前記後縁部の少なくとも一部分が略螺旋曲線に従う請求項12から15のいずれか一項に記載の機体。
- 翼体軸を形成するとともに該翼体軸に沿って観察した場合に略環状の環状体とされ、該環状体の内部が両端で開口しているダクトを形成する翼体を有し、該翼体がその左側に少なくとも1つの方向舵を保持し、その右側に少なくとも1つの方向舵を保持する機体。
- 前記翼体がその左側に2つ以上の方向舵を保持し、その右側に2つ以上の方向舵を保持する請求項17に記載の機体。
- 前記翼体が方向舵の各隣接対の間にスロットを備えて形成される請求項18に記載の機体。
- 前記翼体が、突出したプラットフォーム面積Sと翼体軸に垂直な最大外径Bとを有し、B2/S比が0.5より大きい請求項1から19のいずれか一項に記載の機体。
- 離着陸運転中に安定性を与えるための3つ以上の下部構造要素をさらに備えた請求項1から20のいずれか一項に記載の機体。
- 前記外部翼体内に少なくとも部分的に収容されたエネルギー源をさらに備えた請求項1から21のいずれか一項に記載の機体。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GBGB0707512.0A GB0707512D0 (en) | 2007-04-18 | 2007-04-18 | Annular airborne vehicle |
GB0707512.0 | 2007-04-18 | ||
PCT/GB2008/001329 WO2008129244A2 (en) | 2007-04-18 | 2008-04-16 | Annular airborne vehicle |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2010524765A true JP2010524765A (ja) | 2010-07-22 |
JP5205447B2 JP5205447B2 (ja) | 2013-06-05 |
Family
ID=38135027
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2010503578A Expired - Fee Related JP5205447B2 (ja) | 2007-04-18 | 2008-04-16 | 環状航空機体 |
Country Status (10)
Country | Link |
---|---|
US (3) | US8262016B2 (ja) |
EP (3) | EP2137069B1 (ja) |
JP (1) | JP5205447B2 (ja) |
CN (1) | CN101765540B (ja) |
AT (3) | ATE556931T1 (ja) |
DE (1) | DE602008003110D1 (ja) |
EA (1) | EA014867B1 (ja) |
ES (1) | ES2359455T3 (ja) |
GB (1) | GB0707512D0 (ja) |
WO (1) | WO2008129244A2 (ja) |
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- 2008-04-16 DE DE602008003110T patent/DE602008003110D1/de active Active
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- 2008-04-16 US US12/594,719 patent/US8262016B2/en not_active Expired - Fee Related
- 2008-04-16 ES ES08736991T patent/ES2359455T3/es active Active
- 2008-04-16 CN CN2008800127255A patent/CN101765540B/zh not_active Expired - Fee Related
- 2008-04-16 AT AT10187803T patent/ATE556931T1/de active
- 2008-04-16 EP EP10187803A patent/EP2308754B1/en not_active Not-in-force
- 2008-04-16 AT AT10188051T patent/ATE556930T1/de active
- 2008-04-16 JP JP2010503578A patent/JP5205447B2/ja not_active Expired - Fee Related
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JPWO2019215839A1 (ja) * | 2018-05-09 | 2021-03-11 | 株式会社自律制御システム研究所 | 移動体、及びこれを用いる方法 |
JP6989832B2 (ja) | 2018-05-09 | 2022-01-12 | 株式会社Acsl | 移動体、及びこれを用いる方法 |
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US20120305714A1 (en) | 2012-12-06 |
US8328131B2 (en) | 2012-12-11 |
US8408489B2 (en) | 2013-04-02 |
EP2308754B1 (en) | 2012-05-09 |
WO2008129244A3 (en) | 2008-12-11 |
GB0707512D0 (en) | 2007-05-30 |
EP2137069A2 (en) | 2009-12-30 |
US8262016B2 (en) | 2012-09-11 |
ATE485218T1 (de) | 2010-11-15 |
ATE556930T1 (de) | 2012-05-15 |
EA014867B1 (ru) | 2011-02-28 |
EP2277775A1 (en) | 2011-01-26 |
WO2008129244A2 (en) | 2008-10-30 |
US20100044496A1 (en) | 2010-02-25 |
EP2137069B1 (en) | 2010-10-20 |
JP5205447B2 (ja) | 2013-06-05 |
ATE556931T1 (de) | 2012-05-15 |
EP2308754A1 (en) | 2011-04-13 |
EP2277775B1 (en) | 2012-05-09 |
CN101765540B (zh) | 2013-03-27 |
ES2359455T3 (es) | 2011-05-23 |
EA200901189A1 (ru) | 2010-02-26 |
US20120256043A1 (en) | 2012-10-11 |
DE602008003110D1 (de) | 2010-12-02 |
CN101765540A (zh) | 2010-06-30 |
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