JP2016527128A - ブレード取り付けのためのシステム及び方法 - Google Patents
ブレード取り付けのためのシステム及び方法 Download PDFInfo
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- JP2016527128A JP2016527128A JP2016523727A JP2016523727A JP2016527128A JP 2016527128 A JP2016527128 A JP 2016527128A JP 2016523727 A JP2016523727 A JP 2016523727A JP 2016523727 A JP2016523727 A JP 2016523727A JP 2016527128 A JP2016527128 A JP 2016527128A
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- Prior art keywords
- lug
- fitting
- aircraft system
- blade
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- 238000000034 method Methods 0.000 title claims abstract description 19
- 239000002131 composite material Substances 0.000 claims abstract description 30
- 230000036316 preload Effects 0.000 claims description 2
- 238000006243 chemical reaction Methods 0.000 description 6
- 229910052751 metal Inorganic materials 0.000 description 3
- 239000002184 metal Substances 0.000 description 3
- 230000007704 transition Effects 0.000 description 3
- 230000008878 coupling Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
- 238000009792 diffusion process Methods 0.000 description 2
- 230000006870 function Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 239000010935 stainless steel Substances 0.000 description 2
- 238000005728 strengthening Methods 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 239000004593 Epoxy Substances 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 239000011347 resin Substances 0.000 description 1
- 229920005989 resin Polymers 0.000 description 1
- 238000005476 soldering Methods 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
- 238000005482 strain hardening Methods 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/473—Constructional features
- B64C27/48—Root attachment to rotor head
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/473—Constructional features
- B64C2027/4733—Rotor blades substantially made from particular materials
- B64C2027/4736—Rotor blades substantially made from particular materials from composite materials
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49826—Assembling or joining
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T403/00—Joints and connections
- Y10T403/70—Interfitted members
- Y10T403/7075—Interfitted members including discrete retainer
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
本発明は、契約番号、PhaseIV:W911W6‐07‐D‐0002‐0020 awarded by the U.S.Armyの下で、政府の支援を受けてなされた。政府は、本発明について特定の権利を有する。
条項1
複合材内の接合部を強化するための装置であって、前記装置は、
ラグフィッティング開口部を含んだフィッティングコア、前記ラグフィッティング開口部内に結合されたラグブッシング、及び前記フィッティングコアを実質的に取り囲む外側フィッティングを含む、装置。
条項2
前記外側フィッティングは、ウェブ部分を含む、条項1に記載の装置。
条項3
前記ウェブ部分は、複数のウェブ支持体を含む、条項1又は2に記載の装置。
条項4
前記ラグブッシングは、第1の荷重伝達経路を提供するように構成される、条項1から3のいずれか一つに記載の装置。
条項5
前記外側フィッティングは、第2の荷重伝達経路を提供するように構成される、条項1から4のいずれか一つに記載の装置。
Claims (15)
- ブレードコネクタを備えたローターハブ、及び
ラグフィッティングアセンブリを含む複合材ブレードを備え、前記ラグフィッティングアセンブリは、
ラグフィッティング開口部を含むフィッティングコア、
前記ラグフィッティング開口部内に結合されたラグブッシング、及び
前記フィッティングコアを実質的に取り囲む外側フィッティングを備える、航空機システム。 - 前記外側フィッティングは、ウェブ部分を含む、請求項1に記載の航空機システム。
- 前記ウェブ部分は、複数のウェブ支持体を含む、請求項2に記載の航空機システム。
- 前記複数のウェブ支持体は、複数の空洞を形成する、請求項3に記載の航空機システム。
- 前記ウェブ部分は、切断された楕円を形成する、請求項2に記載の航空機システム。
- 前記ラグブッシングは、第1の荷重伝達経路を提供するように構成される、請求項1から5のいずれか一項に記載の航空機システム。
- 前記外側フィッティングは、第2の荷重伝達経路を提供するように構成される、請求項1から6のいずれか一項に記載の航空機システム。
- 前記ローターハブを前記複合材ブレードに結合させるように構成されたラグアタッチメントを更に備える、請求項1から7のいずれか一項に記載の航空機システム。
- 前記ラグアタッチメントは、プリロードクランピングブッシング、ピンタイプの接合部、ブッシング、ラグボルト、ラグボルトアセンブリ、心棒、及びコッタピンのうちの少なくとも1つである、請求項8に記載の航空機システム。
- 前記複合材ブレードは、ルート端部を含む、請求項1から9のいずれか一項に記載の航空機システム。
- 前記ラグフィッティングアセンブリは、前記ルート端部内に結合される、請求項10に記載の航空機システム。
- 前記外側フィッティングの少なくとも一部分が、少なくとも2インチの翼弦長を有する、請求項1に記載の航空機システム。
- 複合材構造体内のベアリング応力を低減させるための方法であって、前記方法は、
複合材構造体を提供すること、
前記複合材構造体に結合されたフィッティングコアを提供すること、及び
前記フィッティングコアを実質的に取り囲み、ウェブ部分を含む外側フィッティングを提供することを含む、方法。 - 前記フィッティングコア内に結合されたラグブッシングを提供することを更に含む、請求項13に記載の方法。
- 外側フィッティングを提供することは、前記ウェブ部分の幅対厚さの比率を調整することによって、前記ウェブ部分内に所定量のベアリング応力が分散されるように、外側フィッティングを提供することを更に含む、請求項14に記載の方法。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/926,295 | 2013-06-25 | ||
US13/926,295 US9682773B2 (en) | 2013-06-25 | 2013-06-25 | Systems and methods for blade attachment |
PCT/US2014/032375 WO2014209456A1 (en) | 2013-06-25 | 2014-03-31 | Systems and methods for blade attachment |
Publications (3)
Publication Number | Publication Date |
---|---|
JP2016527128A true JP2016527128A (ja) | 2016-09-08 |
JP2016527128A5 JP2016527128A5 (ja) | 2017-05-18 |
JP6301461B2 JP6301461B2 (ja) | 2018-03-28 |
Family
ID=50829254
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2016523727A Active JP6301461B2 (ja) | 2013-06-25 | 2014-03-31 | ブレード取り付けのためのシステム及び方法 |
Country Status (4)
Country | Link |
---|---|
US (1) | US9682773B2 (ja) |
EP (1) | EP3013688B1 (ja) |
JP (1) | JP6301461B2 (ja) |
WO (1) | WO2014209456A1 (ja) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10570949B2 (en) * | 2016-03-17 | 2020-02-25 | The Boeing Company | Damage tolerant and fail-safe (DTFS) high strength preloaded pin assembly |
US10480566B2 (en) * | 2016-03-17 | 2019-11-19 | The Boeing Company | Damage tolerant and fail-safe (DTFS) high strength preloaded pin assembly |
US11718391B2 (en) * | 2021-03-23 | 2023-08-08 | Avx Aircraft Company | Rotary aircraft hybrid rotor mast |
Citations (11)
Publication number | Priority date | Publication date | Assignee | Title |
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US4305699A (en) * | 1979-02-15 | 1981-12-15 | Centro Ricerche Fiat S.P.A. | Blade for a wind motor |
EP0604299A1 (fr) * | 1992-12-23 | 1994-06-29 | Eurocopter France | Dispositif de liaison pale-moyeu à attache feuilletée, pale de rotor munie d'une telle attache,et rotor équipé de telles pales |
JPH0820395A (ja) * | 1994-07-05 | 1996-01-23 | Japan Aviation Electron Ind Ltd | 無人ヘリコプタのヘッド構造 |
US6056838A (en) * | 1995-10-30 | 2000-05-02 | Eurocopter | Method for manufacturing a variable-pitch composite blade for a helicopter rotor |
WO2008087443A1 (en) * | 2007-01-20 | 2008-07-24 | Ge Aviation Systems Group Limited | Blades |
US20100278655A1 (en) * | 2009-04-29 | 2010-11-04 | Eurocopter Deutschland Gmbh | Rotor blade made of a fibre-reinforced composite material and production method for it |
US20120087797A1 (en) * | 2010-10-11 | 2012-04-12 | Eurocopter Deutschland Gmbh | Rotor blade with control tube |
US20120177497A1 (en) * | 2009-09-24 | 2012-07-12 | Shanghai Nine Eagles Electronic Technology Co. | Propeller Connecting Piece for Electric Model Airplane |
US20120195762A1 (en) * | 2011-01-31 | 2012-08-02 | Eurocopter | Blade and method of fabricating said blade |
US20130142658A1 (en) * | 2011-12-01 | 2013-06-06 | Eurocopter | Rotor blade |
US8500407B1 (en) * | 2010-03-28 | 2013-08-06 | The Boeing Company | Composite blade root-end drill-through lug and attachment method |
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2013
- 2013-06-25 US US13/926,295 patent/US9682773B2/en active Active
-
2014
- 2014-03-31 WO PCT/US2014/032375 patent/WO2014209456A1/en active Application Filing
- 2014-03-31 JP JP2016523727A patent/JP6301461B2/ja active Active
- 2014-03-31 EP EP14726806.4A patent/EP3013688B1/en active Active
Patent Citations (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4305699A (en) * | 1979-02-15 | 1981-12-15 | Centro Ricerche Fiat S.P.A. | Blade for a wind motor |
EP0604299A1 (fr) * | 1992-12-23 | 1994-06-29 | Eurocopter France | Dispositif de liaison pale-moyeu à attache feuilletée, pale de rotor munie d'une telle attache,et rotor équipé de telles pales |
JPH0820395A (ja) * | 1994-07-05 | 1996-01-23 | Japan Aviation Electron Ind Ltd | 無人ヘリコプタのヘッド構造 |
US6056838A (en) * | 1995-10-30 | 2000-05-02 | Eurocopter | Method for manufacturing a variable-pitch composite blade for a helicopter rotor |
WO2008087443A1 (en) * | 2007-01-20 | 2008-07-24 | Ge Aviation Systems Group Limited | Blades |
US20100278655A1 (en) * | 2009-04-29 | 2010-11-04 | Eurocopter Deutschland Gmbh | Rotor blade made of a fibre-reinforced composite material and production method for it |
US20120177497A1 (en) * | 2009-09-24 | 2012-07-12 | Shanghai Nine Eagles Electronic Technology Co. | Propeller Connecting Piece for Electric Model Airplane |
US8500407B1 (en) * | 2010-03-28 | 2013-08-06 | The Boeing Company | Composite blade root-end drill-through lug and attachment method |
US20120087797A1 (en) * | 2010-10-11 | 2012-04-12 | Eurocopter Deutschland Gmbh | Rotor blade with control tube |
US20120195762A1 (en) * | 2011-01-31 | 2012-08-02 | Eurocopter | Blade and method of fabricating said blade |
US20130142658A1 (en) * | 2011-12-01 | 2013-06-06 | Eurocopter | Rotor blade |
Also Published As
Publication number | Publication date |
---|---|
US20140377073A1 (en) | 2014-12-25 |
JP6301461B2 (ja) | 2018-03-28 |
WO2014209456A1 (en) | 2014-12-31 |
EP3013688A1 (en) | 2016-05-04 |
US9682773B2 (en) | 2017-06-20 |
EP3013688B1 (en) | 2019-01-09 |
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