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31. 发明专利

GB2183583A Gyroplanes or autogyros; rotor control 未知
公开(公告)号：GB2183583A
公开(公告)日：1987-06-10
申请号：GB8529913
申请日：1985-12-04
申请人： PROPERTY ASSOCIATES LIMITED
发明人： WATTS JAMES ARTHUR
IPC分类号： B64C27/41 , B64C27/02 , B64C27/52
摘要： An autogyro has rotor blades carried by a rotor head mounted via a bore (12) on a support member (10) rotatable about a pitch axis (18) and independently rotatable about a roll axis (22) for control of the autogyro in pitch and roll respectively. The pitch and roll axes intersect one another in order to overcome the problem of rotation about one axis affecting the radius of rotation about the other axis. Means are provided to prevent rotation of the rotor head and support member about an axis orthogonal to both the pitch and roll axes, and comprise a spindle (24) parallel to axis (18) and supported to pivot about axis 18 by links (28). Head plates (14) on the autogyro body carry the spindle (16) defining the axis (18), and the pilot's control movements are applied to the end (40) of support member (10) via linkages not shown.

32. 发明专利

GB8529913D0 AIRCRAFT 未知
公开(公告)号：GB8529913D0
公开(公告)日：1986-01-15
申请号：GB8529913
申请日：1985-12-04
申请人： PROPERTY ASSOCIATES LTD
IPC分类号： B64C27/41 , B64C27/02

33. 发明专利

BE902685A JOINT HOMOCINETIQUE A COUPLE ELEVE. 未知
公开(公告)号：BE902685A
公开(公告)日：1985-10-16
申请号：BE215210
申请日：1985-06-18
申请人： UNITED TECHNOLOGIES CORP
发明人： BYRNES F E , FERRIS D L , HIBYAN E S , NOEHREN W L , OGLE P C , OLSEN E G
IPC分类号： B64C27/35 , B64C27/41 , F16F1/393 , F16D , B64C
摘要： Un palier en élastomère comprenant une cage interne, une cage externe et une alternance de couches d'élastomère et d'armatures de séparation interposées entre les cages est caractérisé en ce que le palier (10) est sensiblement sphérique, il peut tourner autour d'un axe longitudinal (20), il comprend deux extrémités axiales (22, 24) , il est tronqué à l'une au moins de ses extrémités (22, 24) pour permettre le fixation d'un organe rotatif à la cage interne (12) et les couches d'élastoère ont une section droite transversale non circulaire dans un plan normal à l'axe, en donnant lieu ainsi à la formation de lobes axiaux 25. Application au système rotor pour hélicoptère.

34. 发明专利

DK276485D0 未知
公开(公告)号：DK276485D0
公开(公告)日：1985-06-19
申请号：DK276485
申请日：1985-06-19
申请人： UNITED TECHNOLOGIES CORP
发明人： BYRNES FRANCIS E , FERRIS DONALD L , HIBYAN EDWARD S , NOEHREN WILLIAM L , OGLE PETER C , OLSEN ERIC G
IPC分类号： B64C27/35 , B64C27/41 , F16F1/393 , F16C , F16D

35. 发明专利

GB1269327A HELICOPTER ROTOR 未知
公开(公告)号：GB1269327A
公开(公告)日：1972-04-06
申请号：GB805570
申请日：1970-02-19
申请人： DORNIER GMBH
IPC分类号： B64C27/41 , D06M11/82
摘要： 1,269,327. Helicopters. DORNIER G.m.b.H. 19 Feb., 1970 [26 Feb., 1969], No. 8055/70. Heading B7W. A helicopter rotor and mast assembly has rotor blades 5 attached to the cup 3 and a hollow mast 1 fixed to the ball 2 of a ball-andcup joint, and a bendable rod 8 supporting the cup 3 and non-rotatably mounted at a location 11 away from the cup. The mast 1 transmits power to the blades 5 through a synchronous joint 6 at any position of the cup 3 relative to the ball 2, and the blades 5 are attached to the cup by connections 4. Bearings 7 are provided between the cup 3 and bendable rod 8 and the latter is braced by a sleeve 9 and bearing 12. This sleeve 9, 12 slides within the mast 1 and is controlled by linkages 10 so that the rigidity of the ball and cup joint 2, 3 may be varied in accordance with flying conditions. In order that the phase angle in the plane of the rotor disc between cyclic control deflection and control moment should remain the same at all degrees of rigidity when a change in flapping, resistance is imposed part of a swash-plate attached to the fuselage may be rotated. Alternatively, by increasing rotor speed it is possible to maintain the phase angle constant when the control rigidity is changed.

36. 发明专利

GB819214A Rotary wing aircraft 未知
公开(公告)号：GB819214A
公开(公告)日：1959-09-02
申请号：GB3477256
申请日：1956-11-14
申请人： EDWARD BURKE WILFORD , HAROLD EDMINSTON LEMONT
IPC分类号： B64C27/41
摘要： 819,214. Rotary wing aircraft. WILFORD, E. B., and LEMONT, H. E. Nov. 14, 1956 [Nov. 17, 1955], No. 34772/56. Class 4. A rotary wing aircraft rotor system comprises a drive shaft, a hub universally mounted thereon and connected thereto by flexible means so as to bias the hub towards a normal position of equilibrium, a plurality of blades journalled radially in the hub, and means to take up spanwise forces between the blades. In Fig. 1, the rotor shaft 24 is driven through a gear 122 and has an extension 22 ending in a spherical part 20 forming with a bearing member 16, a universal joint for the hub 11. A multiarmed flexible spider 26 is secured to the hub at 30, and a similar spider 32 is secured to the drive shaft at 32. These spiders are connected at the ends of their fingers as at 40, and transmit uniform rotation to the hub while allowing tilting thereof and biasing the hub to a central position. The hub is formed with four cylindrical arms 12 each journalling through roller bearings 52, a cylinder 50 having a flanged end 51 clamped by a ring 56 to a flange 45 on a blade root 44. A tapered pin 58 passing through the cylinder 50 and blade root 44 serves as an anchor for a tension and torsion strap 74, each strap also being attached to a member 78, Fig. 2, relieving the hub of centrifugal forces. A collar 64 is splined to the inner end of each cylinder 50, and bears an arm 66 connected by a rod 108 to the inner ring of a conventional swash ring 94, Fig. 1. Each arm 66 is adjustable to vary the " lead" of the pitch control mechanism. Stops 80 on the hub abut the upper surface of member 78, and a resilient ring 82 surrounds the drive shaft 24 within member 78, to restrain the hub tilt beyond a predetermined point. The spherical member 20 contains an oil reservoir lubricating the bearing 16 through ducts 118. The two spiders 26 and 32 may be replaced by a bellows extending between the fastenings 30 and 34, and the bearing 16 may be replaced by ball bearings. U.S.A. Specification 2,648,387 is referred to.

37. 发明专利

GB704802A A rotor head and swash plate means combination for self- sustaining aircraft 未知
公开(公告)号：GB704802A
公开(公告)日：1954-03-03
申请号：GB2400151
申请日：1951-10-15
申请人： DOMAN HELICOPTERS INC
IPC分类号： B64C27/41
摘要： 704,802. Rotary wing aircraft. DOMAN HELICOPTERS, Inc. Oct. 15, 1951 [Nov. 18, 1950], No. 24001/51. Class 4 In a helicopter having an inclinable rotor hub, the rotating element of the swash-plate that controls blade pitch is connected to the rotor hub by means of an axially flexible tube and provision is made by means of interengaging surfaces on the rotor hub and an element of the swash-plate mechanism respectively to restrain tilting movement of the rotor hub. A fixed mast M, 19 carries a universal joint 11, 12, 13 which supports a shell 14 having bearings 15 for mounting a hub 16 on which the blades 10 are pivotally mounted in bear- ings 18 for pitch change. A drive shaft 21 passes through the mast M and carries a stub shaft 23 inclinable with respect to the shaft 21 by means of a universal joint central with the joint 11, 12, 13. The stub 23 is mounted in the shell 14 by bearings 24 and carries a gear 27 interconnected by planetary pinions 29 to a gear ring 28 on the shell 14 for driving the rotor hub at a speed lower than that of the drive shaft. The mast M carries bearings 40 upon which is mounted for axial and rotary movement a drive tube 35 provided with a universal mounting 36, 37, 38 for the rotating element 39 of a swash-plate, connected by links 34 to blade pitch control horns 33. The non-rotary element of the swash-plate is controlled by rods 48 and a collective pitch control mechanism 41, 42, 43 is provided. The rotor hub carries a flange and the driving tube 35 carries a flanged plate which are interconnected by an axially flexible tube 51. The tube is formed with a depending skirt having a sealed and slidable connection with an end plate 54 secured to the mast M. This plate is intended to collect oil supplied to the rotor head through oilways 80, 81 by a pump 77 driven by gears 78, 79. The hub carries a depending flange 57 and the plate is formed with an annular projection 58 which are brought into inter-locking engagement by extreme movement of the collective pitch control mechanism in order to lock the rotor head and the blades in a horizontal plane. In an alternative embodiment, Fig. 2 (not shown), the universal element of the swash-plate is non-rotary and the upper surface of the drive tube 35 carries a thrust race which is adapted to bear against the flange 57 to lock the rotor head in a horizontal position. Specification 639,572 is referred to.

38. 发明专利

GB643876A Improvements in rotative-winged aircraft 未知
公开(公告)号：GB643876A
公开(公告)日：1950-09-27
申请号：GB2189647
申请日：1947-08-08
申请人： AUTOGIRO CO OF AMERICA
IPC分类号： B64C27/41
摘要： 643,876. Helicopters. AUTOGIRO CO. OF AMERICA. Aug. 8, 1947, No. 21896. Convention date, May 14, 1942. [Class 4] A rotative winged aircraft incorporating a flapping rotor with offset flapping pivots is provided with a freely floating universally tiltable hub so interconnected with floating cyclic pitch-varying mechanism that with reference to the axis of a non-floating member, which may be controllably inclinable with respect to the mechanical axis of the rotor, the inclination of the hub axis and of the control axis of the cyclic pitch mechanism, defined as an axis normal to the plane containing the extremities of the blade pitch control arms, are proportional and of opposite senses in the same azimuth. The rotor driveshaft 6 is mounted in bearings 5, 8 on a fixed structure 3, 4, 7 and is rotated by an enginedriven shaft 14 and gears 12, 13 through a dog-type over-running clutch comprising toothed plates 15, 16 urged into contact by a spring 17. To provide for autorotation of the rotor the plates 15, 16 may be separated by a manually-controlled lever 18. The rotor hub 11 is supported on the upper end of the rotor shaft 6 by a universal joint 9 and each blade 19 is connected to the hub by a link 23 provided with flapping and drag pivots 24, 26 and mounted in a sleeve 25 journalled in the hub at 27 and formed with a pitch-control arm 33, Fig. 2. Each link 23 is extended by an arm 28 co-operating with a ring segment 29, Fig. 2, sandwiched between a pair of friction discs 30 backed by rubber rings 31 and secured within a housing free to tilt and rotate about a supporting ball member 32 secured to the upper end of the shaft 6. This arrangement permits unrestrained simultaneous drag movements of all the blades in the same sense whilst restraining relative drag movements. The hub 11 is provided with stub fittings 40, each radially in line with the extremity 36 of each pitch control arm 33 and attached respectively to the members 40 and 36 are control rods 39, 34, the lower ends of which are connected by a lever 35 pivoted at 38 to an extension 42 of a freely revolving ring 43. The ring is mounted on a swashplate 44 and rotated with the rotor shaft 6 by a scissors linkage 47, 48 attached thereto. The swashplate 44 is mounted on a ball member 46 free to slide on the fixed tube 7 and vertical movement of the member 46, under the action of a linkage 64, 67, effects collective blade pitch control. Cyclical pitch control is provided by a member 58 universally mounted at 61 and engaging an arm 54 depending from the swashplate 44. If, due to an external disturbance in the rotor disc, the pitch of the blade 19 as viewed in Fig. 2 is decreased, the resulting downward movement of the extremity of the arm 33 will, through the linkage 34, 35, 39 tilt the rotor hub 11 downwardly and rearwardly which will increase the pitch of the next advancing blade to restore the equilibrium of the rotor. Specification 410,532 is referred to.

39. 发明专利

FR957079A 未知
公开(公告)号：FR957079A
公开(公告)日：1950-02-14
申请号：FR957079D
IPC分类号： B64C27/41

40. 发明专利

FR948219A 未知
公开(公告)号：FR948219A
公开(公告)日：1949-07-26
申请号：FR948219D
申请日：1947-06-19
申请人： DOMAN FRASIER HELICOPTERS
IPC分类号： B64C27/41

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