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1. 发明专利

JPH10100996A ROTOR BLADE ROTATION STOPPING MECHANISM FOR UNMANNED HELICOPTER 失效
公开(公告)号：JPH10100996A
公开(公告)日：1998-04-21
申请号：JP25485696
申请日：1996-09-26
申请人： JAPAN AVIATION ELECTRON
发明人： WATANABE YOSHIHIKO
IPC分类号： B64C27/48 , B64C27/635 , B64C27/82 , B64C39/02
摘要： PROBLEM TO BE SOLVED: To prevent the hanging-down of a rotor blade when the rotation of a rotor shaft is stopped. SOLUTION: A ball 21 is deviated from a hub grip 12 mounted with a mounting screw (a lead lug shaft) 13 for a rotor blade 11 to the rotor blade 11 with a spring 22 and engaged with a recess 26 formed in the rotor blade 11 to limit the axial rotation of the mounting screw 13 for the rotor blade 11 to a preset range.

2. 发明专利

JP6971840B2 回転翼及びそれを用いた無人航空機有权
公开(公告)号：JP6971840B2
公开(公告)日：2021-11-24
申请号：JP2017252434
申请日：2017-12-27
申请人：株式会社イノアックコーポレーション
发明人：大藪淳
IPC分类号： B64C27/08 , B64C27/473 , B64C27/635 , B64C39/02 , B29C70/16 , B29C70/22 , B29C70/42 , B29K101/10 , B29K105/08 , B29L9/00 , B64C11/22

3. 发明专利

DE69525155T2 未知
公开(公告)号：DE69525155T2
公开(公告)日：2002-08-01
申请号：DE69525155
申请日：1995-04-24
申请人： LORD CORP
发明人： MCGUIRE P
IPC分类号： B64C27/635 , B64C27/51 , F16F9/10 , F16F13/14 , F16F13/24 , F16F15/02 , F16F15/023 , F16F15/08 , F16F9/14 , B64C27/00 , F16F9/34 , F16F13/10 , F16F13/16

4. 发明专利

DE1241272B 未知
公开(公告)号：DE1241272B
公开(公告)日：1967-05-24
申请号：DEB0075015
申请日：1964-01-16
申请人： BOELKOW GMBH
发明人： PFLEIDERER DIPL-ING KURT
IPC分类号： B23Q5/26 , B23Q39/04 , B64C27/54 , B64C27/635 , B64C27/64 , G04D1/00 , G04D3/00
摘要： 1,090,915. Rotary wing aircraft. BOLKOW G.m.b.H. Jan. 18, 1965 [Jan. 16, 1964], No. 2136/65. Heading B7W. [Also in Division G3] A helicopter rotor blade is mounted for leadlag pivoting and is given an impulse, producing a movement about the lead-lag hinge, at a predetermined angular position to ensure that the pivoting motion is correctly phased. In Fig. 1, the rotor blade 31, pivoted at 60 is connected to the piston 28 of a hydraulic servomotor to which fluid is supplied from a pump 7 and reservoir 6, through a rotary valve having a non-rotating part 5 and a part 5a rotating with the rotor and the rest of the hydraulic system. For 5 degrees in each revolution, the valve is in the position shown allowing fluid to move to the right a shuttle valve 19 and the piston 28. For another 5 degree period, the valve is in a position in which it reverses the connections to the lines 11, 13, and the shuttle valve 19 and piston 28 are moved to the left. These two periods are 180 degrees apart, and at other times the valve part 5 closes the conduits 11, 13 allowing the shuttle valve 19 to centralize and connecting the two ends of the cylinder 2 by a passage 22, which contains a fluid pressure operated valve 25. The rotor blade thus pivots freely on the hinge 60. The lead-lag pivoting may be started and stopped gradually by moving the part 5 of the rotary valve axially to vary the alignment of the passages such as 8 with the conduits such as 11, 10 thus to vary the pressure in the servomotor and to vary the pressure on the valve 25. which when closed, damps the pivoting of the blade. The hydraulic servomotor may be replaced by an electric or pneumatic servomotor.

5. 发明专利

GB947683A Pivot drive for producing the lead lag movement of the rotor blade of rotary wing aircraft 未知
公开(公告)号：GB947683A
公开(公告)日：1964-01-29
申请号：GB3205462
申请日：1962-08-21
申请人： LUDWIG BOLKOW
发明人： MULLER MARTIN , DERSCHMIDT HANS , SCHWARZ ALOIS
IPC分类号： B64C27/635
摘要： 947,683. Rotary wing aircraft. L. BOLKOW, [trading as BOLKOW-ENTWICKLUNGEN KOM.-GES. Aug. 21, 1962, No. 32054/62. Headings B7G and B7W. The lead-lag angle of a rotary wing aircraft rotor blade is controlled by an hydraulic transmission. In the Figure, the rotor head comprises a disc 22c, and two parallel spiders 22a, 22b, supporting five blades 25 on drag pivots 24. Each blade is cyclically pivoted about its drag axis by a telemotor system comprising a slave cylinder 29 and a master cylinder 36 connected between disc 22c and the rotary element 42 of a swash plate. Where there is an even number of blades, opposed slave cylinders are hydraulically connected to each other and to a master cylinder, one for each pair of slave cylinders. The rotary member of the swash plate may consist solely of arms, one for each master cylinder, each pivoted to the rotor shaft at one end and having at the other end a roller received in a groove in a non- rotary inclinable ring. The master cylinder can then be secured to the rotor shaft, and communicate with the slave cylinders through bores in the shaft and flexible pipes. The slave cylinders contain longitudinal grooves on their inner walls, or other restricted by-pass ducts, the flow through which tends to cause the piston path to be symmetrically located longitudinally of the cylinder (see Figs. 5-12 (not shown).

6. 发明专利

JP2019116254A 回転翼及びそれを用いた無人航空機审中-公开
公开(公告)号：JP2019116254A
公开(公告)日：2019-07-18
申请号：JP2017252434
申请日：2017-12-27
申请人：株式会社イノアックコーポレーション
发明人：大藪淳
IPC分类号： B64C1/00 , B64C39/02 , B64C27/473 , B64C27/635 , B64C27/08 , B29C70/22 , B29C70/16 , B29C70/42 , B29K101/10 , B29K105/08 , B29L9/00 , B64C11/22
摘要：【課題】ロータの回転のブレを抑制可能な回転翼及びそれを用いた無人航空機の提供を目的とする。【解決手段】本発明に係る回転翼10は、炭素繊維に熱硬化性樹脂が含浸してなる表皮20と、発泡体を含み且つ表皮20の内側に配置されるコア部27と、を有している。表皮20は、2軸以上の炭素繊維織物22に熱硬化性樹脂が含浸してなり、回転翼10の外表面を形成する外側表皮層21を有している。コア部27は、発泡体に熱硬化性樹脂が含浸してなる。【選択図】図3

7. 发明专利

JPH10503573A 失效
公开(公告)号：JPH10503573A
公开(公告)日：1998-03-31
申请号：JP52898895
申请日：1995-04-24
IPC分类号： B64C27/635 , B64C27/51 , F16F9/10 , F16F13/14 , F16F13/24 , F16F15/02 , F16F15/023 , F16F15/08

8. 发明专利

BR102019026287A2 pá aerodinâmica, aeronave rotativa, e, ponta de um corpo de pá de uma pá aerodinâmica 未知
公开(公告)号：BR102019026287A2
公开(公告)日：2020-12-29
申请号：BR102019026287
申请日：2019-12-11
申请人： HAMILTON SUNDSTRAND CORP
发明人： TIMOTHY MAVER
IPC分类号： B64C27/04 , B64C27/32 , B64C27/635
摘要： pá aerodinâmica, aeronave rotativa, e, ponta de um corpo de pá de uma pá aerodinâmica uma pá aerodinâmica é fornecida e inclui um corpo da pá e um módulo de luz. o corpo da pá inclui uma extremidade interna e uma ponta externa da extremidade interna. o corpo da pá é conectável a um cubo na extremidade interna, de modo que as rotações do cubo conduzam rotações da ponta em torno de um eixo rotacional. o módulo de luz é disposto na ponta e configurado para ativar em resposta às rotações da ponta sobre o eixo rotacional para emitir luz visível no exterior do corpo da pá.

9. 发明专利

CA2969992C ROTOR ET AERONEF POURVU D'UN TEL ROTOR 未知
公开(公告)号：CA2969992C
公开(公告)日：2018-08-21
申请号：CA2969992
申请日：2017-06-06
申请人： AIRBUS HELICOPTERS
发明人： HONNORAT OLIVIER , JALAGUIER JEAN-PIERRE
IPC分类号： B64C27/51 , B64C27/37 , B64C27/39 , B64C27/635
摘要： La présente invention concerne un rotor (5) comprenant un moyeu (10) et une pluralité d'ensembles sustentateurs (15). Chaque ensemble sustentateur (15) est relié à deux ensembles sustentateurs adjacents respectivement par un premier amortisseur (301) et un deuxième amortisseur (302). Le premier amortisseur (301) est articulé un ensemble sustentateur (15) autour d'un premier axe (AX1), et le deuxième amortisseur (302) est articulé audit ensemble sustentateur (15) autour d'un deuxième axe (AX2). Un premier plan (P1) contient un axe de traînée (AXTRA) de l'ensemble sustentateur et orthogonal à l'axe de pas (AXPAS) de l'ensemble sustentateur (15). Le premier axe (AX1) est situé dans un volume (V1) compris entre le premier plan (P1) et un axe de rotation (AXROT) du rotor, le deuxième axe (AX2) étant positionné en dehors dudit volume (V1).

10. 发明专利

CA2658032A1 DISPOSITIF D'AMORTISSEMENT ET SYSTEME DE ROTOR D'AERODYNE L'INCORPORANT 未知
公开(公告)号：CA2658032A1
公开(公告)日：2009-09-06
申请号：CA2658032
申请日：2009-03-05
申请人： HUTCHINSON
发明人： RICHER DE FORGES HERVE , CIOLCZYK JEAN-PIERRE
IPC分类号： B64C27/51 , B64C11/04 , B64C11/12 , B64C27/37 , B64C27/635 , F16F5/00 , F16F9/34
摘要： La présente invention concerne un dispositif d'amortissement en particulier destiné à former un amortisseur de mode de traînée pour pale d'hélicoptère, et un système de rotor d'aérodyne incorporant ce dispositif. Ce dispositif d'amortissement (101) comporte : - un bâti (102) externe destiné à être couplé à un premier élément tournant et un élément radialement interne (105) monté coaxialement au bâti et destiné à être couplé à un second élément tournant, - au moins un amortisseur élastomère (107) de section transversale annulaire monté solidaire du bâti et de l'élément interne, et - une chambre de travail (108) délimitée par le bâti et par l'amortisseur et communiquant avec une chambre de compensation (109) délimitée par un organe souple hautement déformable (113) monté coaxialement à l'élément interne. Selon l'invention, la chambre de travail est formée en une première extrémité (104) du dispositif et communique avec la chambre de compensation par une structure poreuse (110) surmontant une ouverture d'extrémité de l'organe souple, lequel est monté dans l'élément interne.

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