| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 41 | Lead/lug motion damper for blade of helicopter rotor system | JP17747586 | 1986-07-28 | JPS6338098A | 1988-02-18 | DONARUDO ERU FUERISU; DEBUITSUDO JII MATOUSUKA |
| 42 | Rotor blade of helicopter | JP11296583 | 1983-06-24 | JPS5957098A | 1984-04-02 | RABATO UOORASU METSUGA; UIRIAMU DEIBUIDO NIIZUARI; PIITA ARAN REIESU; PATORITSUKU RAIAN TEISUDEIRU; SESHIRU EDOUADO KABUINGUTAN; UIRIAMU BURETSUKUFUIZEN |
| 43 | Rotor for helicopter with device having integral joint in root section of blade | JP20382982 | 1982-11-22 | JPS5893697A | 1983-06-03 | RUNE RUI RUIYU |
| 44 | JPS5632159B1 - | JP1529472 | 1972-02-15 | JPS5632159B1 | 1981-07-25 | |
| 45 | 回転翼航空機用のロータヘッドのロータブレード結合装置 | JP2015167074 | 2015-08-26 | JP2016052882A | 2016-04-14 | マルティン、シュトゥッキ; マリオ、カミナダ; パトリック、レジナルド、モーザー; リーケルト、レイブラント |
| 【課題】簡略化された構造的形態で機動的な制御を行うことができるようになっているロータブレード結合装置を提供する。 【解決手段】ロータヘッド中心ピース7と、ロータ平面(RE)内に位置するロータブレード3を受け入れるためにロータヘッド中心ピース7に取り付けられるロータブレードホルダ4と、隣り合うロータブレードホルダ4間の連結手段とを含む、回転翼航空機のロータヘッド1を形成するためにロータマスト9と結合するためのロータブレード結合装置2では、該ロータブレード結合装置2のために簡略化された構造的形態が達成され、且つ、ロータブレード結合装置2が機動的な制御を可能にする。これは、ロータブレード結合装置2が連結手段としてリング10を含み、リング10がそれぞれの連結位置でロータブレードホルダ4の全てと交差し、且つロータブレードホルダ4の全てを互いに連結するように配置される事によって達成される。 【選択図】図1 |
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| 46 | 制振機械的リンケージ | JP2015520196 | 2013-05-24 | JP2015522142A | 2015-08-03 | エドワード・ヴィ・ホワイト |
| 機械的リンケージは、第1および第2の端部部材と、一対の略平行なアーチ形ビームであって、端部部材を互いに接続するとともに、ビーム間に側方空間を画定するビームとを含む。複数の交互のフィンガが各ビームから側方空間内へと延伸し、また、制振部材が、側方空間内で、フィンガのそれぞれの隣り合う対間に取り付けられる。 | ||||||
| 47 | Vibration reducing device | JP2012066872 | 2012-03-23 | JP2013199945A | 2013-10-03 | YOSHIZAKI YUJI; SUZUKI HIDETOSHI; ITO HIROSHI |
| PROBLEM TO BE SOLVED: To make a vibration reducing device utilized when reducing vibration more compact in size.SOLUTION: A vibration reducing device is equipped with a dynamic mass 22, elastic bodies 23-1 to 23-2, 24-1 to 24-2, which apply elastic forces to the dynamic mass 22 so that the dynamic mass 22 vibrates in parallel to a damping direction 25, a control mass 26, an actuator 27 which expands and contracts in parallel in an expansion and contraction direction 34, and a moving direction conversion mechanism 28 which moves the control mass 26 to the dynamic mass 22 so that the control mass 26 moves in a damping direction 25 to the dynamic mass 22 by the expansion and contraction of the actuator 27. The actuator 27 is supported by the dynamic mass 22 so that the expansion and contraction direction 34 does not become parallel to the damping direction 25. By this, a vibration reducing device 19-i can be formed so that the dimension of the damping direction 25 becomes smaller compared with other vibration reducing devices in which the expansion and contraction direction 34 and the damping direction 25 are equal, the device can be made more compact in size. | ||||||
| 48 | Blade damper, and rotor fitted with the damper | JP2011039014 | 2011-02-24 | JP2011207470A | 2011-10-20 | LOUIS CHARLES; FERRANT MATTHIEU |
| PROBLEM TO BE SOLVED: To provide a damper implementable safely and suitable for preventing the generation of drive system resonance, in particular.SOLUTION: The damper (10) includes an inner end strength member (20) and an outer end strength member (30) that are tubular and coaxial, and includes a return member (40) arranged between the inner end strength member (20) and the outer end strength member (30). The return member (40) includes an intermediate strength member (43) coaxial with the inner and outer end strength members (20, 30), and the return member (40) has first and second return means (41, 42). The first return means (41) is arranged between the outer end strength member (30) and the intermediate strength member (43), and the second return means (42) is arranged between the inner end strength member (20) and the intermediate strength member (43). | ||||||
| 49 | Helicopter, its rotor, and its control method | JP2008013568 | 2008-01-24 | JP2009173152A | 2009-08-06 | NAKAO MASAHIRO |
| <P>PROBLEM TO BE SOLVED: To provide a helicopter capable of flying at high speed, a rotor of the helicopter, and a control method of the helicopter. <P>SOLUTION: The rotor of the helicopter includes blades 3, a rotor hub 21 for supporting the blades 3, and a lead lag angle control mechanism 6 which changes the lead lag angle of the blade 3 in synchronism with the rotation of the rotor hub 21. The lead lag angle control mechanism 6 changes the lead lag angle of the blades 3 so that the peripheral speed of the blade tips of the blades 3 becomes slow at the advanced side and fast at the retreated side. <P>COPYRIGHT: (C)2009,JPO&INPIT | ||||||
| 50 | Rotary wing of rotorcraft having blade in hinge coupling in flap and lug condition | JP2006256256 | 2006-09-21 | JP2007084064A | 2007-04-05 | BEROUL FREDERIC |
| PROBLEM TO BE SOLVED: To provide a lug damper means for damping vibrations of hinge coupled blades of the rotary wing of rotorcraft. SOLUTION: The rotary wing 11 of the rotorcraft is composed of a hub 31 and at least two blades 14-17 coupled by hinges with the hub at the peripheries of the pitch axes 14a-17a, flap axes, and lug axes. The blades are attached to pitch levers 26-29, while the rotary wing includes pitch control rods connected with the pitch levers by first ball joints 65 and a common lug damper system 30 arranged centering on the rotary shaft 12 of the rotary wing sufficiently and connected with the blades. The damper system is mounted on transverse projections of the blades by second ball joints 31-34 in proximity sufficiently to the first ball joints for connecting the pitch rods to the pitch levers in order to preventing the system itself from being influenced comparatively by the flap vibrations of the hinge coupled blades. COPYRIGHT: (C)2007,JPO&INPIT | ||||||
| 51 | Damping mechanism | JP29790197 | 1997-10-14 | JP3841530B2 | 2006-11-01 | ティエリー シエグ; パトリス ルバラール |
| 52 | Articulated helicopter | JP14750696 | 1996-06-10 | JPH0999900A | 1997-04-15 | SANTEIINO PANKOTSUTEI |
| PROBLEM TO BE SOLVED: To keep the oscillation in all directions of each blade to other than the relatively limited value when the angular speed of a rotor becomes lower than a designated value by limiting the operation on the side to each hub of each blade within a designated value in the engagement position. SOLUTION: A limiting device 44 for limiting the oscillation in the lateral direction to a hub 2 of a blade 4 when the hub 2 is rotated relatively at a low speed or stopped is disposed between each of bridges 9 and a fork 11. A centrifugal pin device 45a comprises a seat part 49 provided in a fixed position to the hub 2, and a pin part or a pin assembly 50 provided in such a manner as to move among the engagement position to the hub 2, the middle position and the release position. In each position of the engagement position, the middle position and the release position, the pin assembly engages with the seat part 49, and partially engages therewith, and the engagement with the seat part 49 is released. | ||||||
| 53 | The tubular elastomer damper | JP51512994 | 1993-10-18 | JPH08505923A | 1996-06-25 | カレン、ローレンス・アイ、ザ・サード; バイルンス、フランシス・イー |
| (57)【要約】 管状エラストマーダンパー（１１）はハウジング（１３）の内部に配置され且つエラストマー部材（１４）によって包囲された中心シャフト（１２）を有している。 エラストマーに沿った各点で半径と長さとの積が等しい値になるようにエラストマーの長さを内側接着面（１５）から外側接着面（１６）まで漸減させることによって、または、シャフト（２６）に近い側に高疲労歪み及び低減衰能力を有する第一エラストマー層（２８）を用い、ハウジング（２７）に近い側に低歪み及び高減衰能力を有する第二エラストマー層（２９）を用い、それらの間に中程度の歪み及び中程度の減衰能力を有する中間エラストマー層（３０）を用いてエラストマー部材の内側半径から外側半径まで均一な歪みが得られるように形成することによって、中心シャフトとハウジングとの間に配置されたエラストマー全体に均一な歪みを与えるようにする。 管状エラストマーダンパーの内側半径部から外側半径部まで均一な歪みを与えることによって、局在する高い歪みに起因する、減衰特性に不利益な温度上昇を防止する。 任意に、設計パラメータ内の動作を確実にし、管状エラストマーダンパーの寿命を延長するために、熱散逸用の軸方向冷却通路をエラストマー部材内部に設ける。 | ||||||
| 54 | Softball plane bearingless rotary wing and the yoke | JP11296583 | 1983-06-24 | JPH0741879B2 | 1995-05-10 | ウイリアム・デイヴイド・ニ−ズアリ; ウイリアム・ブレツクフイゼン; セシル・エドウアド・カヴイングタン; パトリツク・ライアン・テイスデイル; ピ−タ・アラン・レイエス; ラバト・ウオ−ラス・メツガ |
| 55 | JPH0479880B2 - | JP23121683 | 1983-12-06 | JPH0479880B2 | 1992-12-17 | EMIRIO PARIAANI |
| 56 | Nonarticulated hub structure for rotary wing aeroplane | JP11391990 | 1990-04-27 | JPH0411599A | 1992-01-16 | YAMAMOTO KEIZO; ICHIHASHI TAKAHIRO; HANAYAMA KANEHIRO; BANDO SHUNICHI; KAKINUMA ASAO; WAKATSUKI TADASHI |
| PURPOSE: To reduce the outside diameter dimension by arranging a lead lug damper between two beam-shaped parts which constitute the deflection part of a deflection member and accommodating a spherical bearing for connecting a pitch housing formed integrally with a rotary blade, with a hub, into the lead lug damper. CONSTITUTION: A deflection girder member 4 extending in the radial direction is shaped integrally with a hub body 2, and a flexible part 29 is installed on the outside in the radial direction of a leaf spring shaped part 3 at the inner edge part in the radial direction. The flexible part 29 consists of beam-shaped parts 8a and 8b which are arranged, keeping intervals in the revolution direction, and the edge part is formed integrally, and a deflection part 9 is formed outside. The leaf spring member 3 and the flexible part 29 are pin-joined, and a joint part 5 is joined compactly by combining a plurality of lug elements. An elastic metallic damper 7 is arranged between the beam-shaped parts 8a and 8b, and a spherical bearing 17 is built in the damper 7, and the pivot shaft 14 of a housing supporting member 13 is inserted, and the housing 10 formed integrally with a rotary blade 12 is fixed on the supporting member 13. COPYRIGHT: (C)1992,JPO&Japio | ||||||
| 57 | Rotary visco-elastic device for damping drag and recovering elasticity of rotor blade of rotorcraft, and rotor head having it | JP28324690 | 1990-10-20 | JPH03213497A | 1991-09-18 | KUROODO BIETOUNADE; ROBEERU JIYAN SHIYUJI |
| PURPOSE: To reduce drag of a rotor head by constituting a member for supporting a plurality of rotor blades connected to a hub to be rotated around a rotor shaft so as to freely damping drag and recovering elasticity by interposing a visco-elastic material formed of a thin tubular layer between inner and outer rigid core members capable of relatively moving. CONSTITUTION: A helicopter is provided with a plurality of rotor blades including leg parts connected to a hub 1 to be rotated around a rotor axis A through fork-shaped connectors 14 and laminated spherical joints 5. Moreover, it is provided with respective rotor blades and devices 28 for damping and absorbing drag and recovering elasticity, and each device 28 is constituted of a drag damping and elasticity recovering member 29 and a rigid rod 30. In this case, the drag damping and elasticity recovering member 29 is constituted by interposing a visco-elastic material 33 formed of a thin tubular layer having the high resistance against deformation between inner and outer rigid core members 31, 32 capable of being relatively moved. One end of the ridge rod 30 is connected to a lever 34 projectingly provided on the outer core member 32, and the inner core member 31 is connected to a supporting body 50a on the hub 1. COPYRIGHT: (C)1991,JPO | ||||||
| 58 | Rotary-wing aircraft rotor head having resilient-return interblade ties with built-in damping arrangement | JP11187189 | 1989-04-28 | JPH0253698A | 1990-02-22 | BURIYUNO GINBARU |
| PURPOSE: To remove the excessive coupling to a rotor head by holding an essential toggle joint on a means for connecting a blade to a hub in the radially outside beyond the intersection forming the single center of the joint connecting of a connecting member to the hub. CONSTITUTION: A blade-to-blade connecting device having a plurality of resilient- return tie rod 29 with built-in damping arrangement mounted in a ring form is provided around a hub 1. An essential toggle joint 41 is situated about on the feathering axial line X-X, and held by a means 13 for connecting a blade to the hub 1 in the radially outside beyond the intersection C where the flapping axial line, the drag axial line and the feathering axial line cross to form the single center of the joint connection of a connecting member 13 to the hub 1. According to this, the excessive coupling to a rotor head can be removed. COPYRIGHT: (C)1990,JPO | ||||||
| 59 | JPH01162900U - | JP5453489 | 1989-05-15 | JPH01162900U | 1989-11-13 | |
| 60 | Pitch changing and lead lag attenuating device for helicopter | JP28374287 | 1987-11-10 | JPH01127493A | 1989-05-19 | SATO TETSURO |
| PURPOSE: To prevent relative displacement between a sleeve and a pivot so as to reduce a lead lag by connecting an elastomeric damper, a flex beam, a torque arm, a pitch sleeve, an elastomeric pivot, a damper, and an arm with each other. CONSTITUTION: In assembly of a pitch changing and lead lag attenuating device 6, a through hole 2a is bored in a flex beam 2, a bushing 13 is mounted inside the through hole 2a, and an assembly constructed of an elastomeric pivot 7 and a torque arm 12 connected together by means of a nut 10 is inserted into the inside of the bushing 13. After an elastomeric damper 9 is inserted from the upper/lower side of the arm 12 so as to be connected to the pivot 7 via the beam 2 and a nut 8 and a pitch sleeve 3 is inserted into the beam 2, the sleeve 3 and the arm 12 are connected together via a nut 11. If a lead lag is generated in a rotor blade 4 and a relative position between the beam 2 and the sleeve 3 is changed because a clearance between the end face of the beam 2 and a pitch change link 5 is changed from 1 to 1', a relative displacement between the sleeve 3 and the pivot 7 can be prevented. COPYRIGHT: (C)1989,JPO | ||||||
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