JP2013203369A - 飛行体の高揚力装置 - Google Patents
飛行体の高揚力装置 Download PDFInfo
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- JP2013203369A JP2013203369A JP2012077712A JP2012077712A JP2013203369A JP 2013203369 A JP2013203369 A JP 2013203369A JP 2012077712 A JP2012077712 A JP 2012077712A JP 2012077712 A JP2012077712 A JP 2012077712A JP 2013203369 A JP2013203369 A JP 2013203369A
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- flap
- flap body
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- wing
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- 239000011800 void material Substances 0.000 abstract 2
- 230000004048 modification Effects 0.000 description 40
- 238000012986 modification Methods 0.000 description 40
- 230000000694 effects Effects 0.000 description 6
- 230000009467 reduction Effects 0.000 description 6
- 230000007246 mechanism Effects 0.000 description 4
- 230000007423 decrease Effects 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- 238000004904 shortening Methods 0.000 description 3
- 239000007787 solid Substances 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 238000009826 distribution Methods 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 238000005096 rolling process Methods 0.000 description 2
- 238000001228 spectrum Methods 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000012937 correction Methods 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000001771 impaired effect Effects 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000003860 storage Methods 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
- B64C9/16—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing
- B64C9/18—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing by single flaps
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
- B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
- B64C21/08—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like adjustable
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/44—Varying camber
- B64C3/50—Varying camber by leading or trailing edge flaps
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/02—Mounting or supporting thereof
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
- B64C2009/143—Adjustable control surfaces or members, e.g. rudders forming slots comprising independently adjustable elements for closing or opening the slot between the main wing and leading or trailing edge flaps
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C2230/00—Boundary layer controls
- B64C2230/14—Boundary layer controls achieving noise reductions
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/10—Drag reduction
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
- Toys (AREA)
- Body Structure For Vehicles (AREA)
Abstract
【解決手段】 高揚力装置3は、飛行体に揚力を生じさせる主翼2の後部に展開及び収容可能に設けられ、主翼2の翼長方向に沿って延在するフラップ本体11を備え、該フラップ本体11の延在方向の端部11aには、展開時における主翼2の後部とフラップ本体11の前部との間の空隙を拡張させる空隙拡張部20,30が設けられている。
【選択図】図3
Description
(主翼及び高揚力装置)
図1は、本発明の実施形態に係る飛行体の高揚力装置3の概要構成を示す斜視図である。図1に示すように飛行体は、前後方向に延びる機体1、左右一対の主翼2(図1では右側主翼のみを図示)、及び高揚力装置3を備えている。一対の主翼2は、機体1から左方向及び右方向それぞれに延びている。高揚力装置3は、主翼2の後縁部に設けられている。本実施形態に係る高揚力装置3は、スロッテッドフラップ型又はファウラーフラップ型であり、主翼2に収容されたり主翼2から展開したりする。なお、図1に示すように、飛行体1の主翼2にはこの他にも、ジェットエンジン4が懸架され、前縁部にはスラット5、後縁部には内側補助翼6,外側補助翼7などが設けられている。
(実施の形態1:前縁短縮型)
図3は、実施の形態1に係る高揚力装置3のフラップ本体11の構成を示す外観図であり、平面図と先端側からの側面図とを示している。図3に示すフラップ本体11は、全体的には、平面視にて左右方向(翼長方向)に長寸の長方形状を成している。その翼長方向の先端部11aには、その翼弦長を短縮することによって空隙拡張部20が形成されている。より具体的に説明すると、フラップ本体11の先端部11aの前縁部(以下、「先端前縁部」)21は、その他の部分の前縁部(以下、「本体前縁部」)12に比べて後方に位置している。且つ、先端部11aにおける翼弦方向寸法は、該先端部11aの近傍部分における翼弦方向寸法よりも小さく形成されている。そして、先端前縁部21の前方に形成されるスペース22が、上記の空隙拡張部20を構成している。
(実施の形態2:前縁上面カット型)
図7は、実施の形態2に係る高揚力装置3のフラップ本体11の構成を示す外観図であり、平面図と先端側からの側面図とを示している。図7に示すフラップ本体11は、実施の形態1と同様に、全体的には、平面視にて左右方向(翼長方向)に長寸の長方形状を成している。その翼長方向の先端部11aには、その上部を窪ませることによって空隙拡張部30が形成されている。
2 主翼
3 高揚力装置
11 フラップ本体
12 本体前縁部
20 空隙拡張部
21 先端前縁部
22 スペース
30 空隙拡張部
31 窪み
32 スペース
Claims (4)
- 飛行体の主翼の後部に展開及び収容可能に設けられ、前記主翼の翼長方向に沿って延在するフラップ本体を備え、
該フラップ本体の延在方向の端部には、展開時における前記主翼の後部と前記フラップ本体の前部との間の空隙を拡張させる空隙拡張部が設けられている、飛行体の高揚力装置。 - 前記フラップ本体の延在方向端部の前縁部は、他の部分の前縁部に比べて後方に位置し、且つ、前記延在方向端部の翼弦方向寸法は、当該延在方向端部の近傍部分における翼弦方向寸法よりも小さく形成されており、該フラップ本体の延在方向端部の前縁部の前方に形成される空隙が、前記空隙拡張部を構成する、請求項1に記載の飛行体の高揚力装置。
- 前記フラップ本体の延在方向端部の前縁部は、他の部分の前縁部に比べて上部が窪ませてあり、該窪みが前記空隙拡張部を構成する、請求項1に記載の飛行体の高揚力装置。
- 前記フラップ本体の前記延在方向端部の近傍部分の翼弦方向寸法をLとした場合に、前記フラップ本体の主面に対向して平面視したときの前記空隙拡張部は、その翼長方向寸法が寸法Lの100%以下、且つ、その翼弦方向寸法が寸法Lの30%以下である、請求項1乃至3の何れかに記載の飛行体の高揚力装置。
Priority Applications (8)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2012077712A JP5956803B2 (ja) | 2012-03-29 | 2012-03-29 | 飛行体の高揚力装置 |
PCT/JP2013/002174 WO2013145774A1 (ja) | 2012-03-29 | 2013-03-29 | 飛行体の高揚力装置 |
CA2867045A CA2867045C (en) | 2012-03-29 | 2013-03-29 | High-lift device of air vehicle |
EP13768891.7A EP2832638B1 (en) | 2012-03-29 | 2013-03-29 | High-lift device for flight vehicle |
CA2983719A CA2983719C (en) | 2012-03-29 | 2013-03-29 | High-lift device of air vehicle |
US14/389,257 US9714079B2 (en) | 2012-03-29 | 2013-03-29 | High-lift device of air vehicle |
BR112014024151-1A BR112014024151B1 (pt) | 2012-03-29 | 2013-03-29 | Dispositivo de alta sustentação para veículo aéreo |
US15/629,407 US9789955B1 (en) | 2012-03-29 | 2017-06-21 | High-lift device of air vehicle |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2012077712A JP5956803B2 (ja) | 2012-03-29 | 2012-03-29 | 飛行体の高揚力装置 |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2013203369A true JP2013203369A (ja) | 2013-10-07 |
JP5956803B2 JP5956803B2 (ja) | 2016-07-27 |
Family
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Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2012077712A Active JP5956803B2 (ja) | 2012-03-29 | 2012-03-29 | 飛行体の高揚力装置 |
Country Status (6)
Country | Link |
---|---|
US (2) | US9714079B2 (ja) |
EP (1) | EP2832638B1 (ja) |
JP (1) | JP5956803B2 (ja) |
BR (1) | BR112014024151B1 (ja) |
CA (2) | CA2983719C (ja) |
WO (1) | WO2013145774A1 (ja) |
Families Citing this family (9)
Publication number | Priority date | Publication date | Assignee | Title |
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JP2016078584A (ja) | 2014-10-15 | 2016-05-16 | 三菱航空機株式会社 | 航空機 |
US10532805B2 (en) * | 2016-09-20 | 2020-01-14 | Gulfstream Aerospace Corporation | Airfoil for an aircraft having reduced noise generation |
CN110072773B (zh) | 2016-12-12 | 2022-10-21 | 庞巴迪公司 | 飞机缝翼 |
DE102018121395B4 (de) * | 2018-09-03 | 2021-06-17 | Airbus Defence and Space GmbH | Endrippenanordnung für eine Auftriebshilfevorrichtung eines Luftfahrzeugs mit Lärmminderung |
CA3082663A1 (en) | 2019-06-10 | 2020-12-10 | Bombardier Inc. | Wing assembly with slats and aircraft |
US11897597B2 (en) * | 2020-07-20 | 2024-02-13 | The Boeing Company | Flap pressure shape biasing |
CN112644687B (zh) * | 2020-12-31 | 2024-05-17 | 中国商用飞机有限责任公司 | 飞机后缘襟翼 |
CN112678150B (zh) * | 2020-12-31 | 2024-04-26 | 中国商用飞机有限责任公司 | 飞机后缘襟翼 |
CN114750930B (zh) * | 2022-05-07 | 2023-05-16 | 中国航空工业集团公司沈阳飞机设计研究所 | 一种翼面开缝扰流板式航向控制舵面 |
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2012
- 2012-03-29 JP JP2012077712A patent/JP5956803B2/ja active Active
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2013
- 2013-03-29 WO PCT/JP2013/002174 patent/WO2013145774A1/ja active Application Filing
- 2013-03-29 EP EP13768891.7A patent/EP2832638B1/en active Active
- 2013-03-29 US US14/389,257 patent/US9714079B2/en active Active
- 2013-03-29 CA CA2983719A patent/CA2983719C/en active Active
- 2013-03-29 CA CA2867045A patent/CA2867045C/en active Active
- 2013-03-29 BR BR112014024151-1A patent/BR112014024151B1/pt active IP Right Grant
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2017
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Publication number | Publication date |
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BR112014024151B1 (pt) | 2021-11-16 |
US20170291688A1 (en) | 2017-10-12 |
US9789955B1 (en) | 2017-10-17 |
CA2867045A1 (en) | 2013-10-03 |
CA2983719C (en) | 2020-04-28 |
BR112014024151A2 (ja) | 2017-06-20 |
EP2832638B1 (en) | 2018-03-07 |
CA2867045C (en) | 2018-06-05 |
EP2832638A1 (en) | 2015-02-04 |
EP2832638A4 (en) | 2015-11-18 |
CA2983719A1 (en) | 2013-10-03 |
JP5956803B2 (ja) | 2016-07-27 |
US9714079B2 (en) | 2017-07-25 |
US20150053825A1 (en) | 2015-02-26 |
WO2013145774A1 (ja) | 2013-10-03 |
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