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Publication numberUS2861641 A
Publication typeGrant
Publication dateNov 25, 1958
Filing dateFeb 28, 1955
Priority dateFeb 28, 1955
Publication numberUS 2861641 A, US 2861641A, US-A-2861641, US2861641 A, US2861641A
InventorsBensen Igor B
Original AssigneeBensen Igor B
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Control mountings for helicopter rotors
US 2861641 A
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Description  (OCR text may contain errors)

Nov. 25, 1958 I. B. BENSEN 2,8

CONTROL MOUNTINGS FOR HELICOPTER ROTORS,

Filed Feb. 28, 1955 v 4 Sheets-Sheet l INVENTOR I I I602 5i 550 55 BY ATTORNEY Nov. 25, 1958 1. BENSEN CONTROL MOUNTINGS FOR HELICOPTER ROTORS Filed Feb. 28, 1955 4 Sheets-Sheet 2 INVENT OR 160/? 5. fils/vsf/v ATTORNEY WME I. B. BENSEN CONTROL MOUNTINGS FOR HELICOPTER ROTORS Filed Feb. 28, 1955 Nov. 25, 1958 4 Sheets-Sheet 3 INVENTOR 160/2 5. 55/1/55 ATTORNEY Nov. 25, 1958 .1. B.-B EN$EN CONTROL MOUNTING$ FOR HELICOPTER ROTORS Filed Feb. 28, 1955 4 Sheets-Sheet 4 ATTORNEY CONTROL MOUNTINGS FOR HELICOPTER ROTORS Igor B. Benson, Raleigh, N. C.

Application February 28, 1955, Serial No. 490,883

2 Claims. (Cl. 170-16027) This invention relates to helicopters and, more parglciularly, to combined rotor mount and control assem- The object of the invention is to provide an extremely simple, light and durable assembly for mounting a rotor on the top of a fuselage, whereby the axis of rotation of the rotor may be universally tilted, and whereby the pilot maintains direct and instinctively natural control over the tilting adjustments of the rotor. p

More particularly, it is intended now to provide a generally vertical rotor shaftpivotally mounted on the fuselage above the pilot seat of a helicopter, the rotor turning on-the shaft above the fuselage, and a control stick extending downwardly from the rotor shaft so that-when the control stick is swung forwardly and rearwardly, or from side to side, therotor shaft is correspondingly tilted about its'pivotal mounting, and the rotor follows the tilting of the rotor shaft. The instinctively natural reaction obtained by the control system-of this invention has to do with the native balancing reactions of a pilot, i. e., when he desires to travel to the right, for example, the natural motion of a control stick suspended froma point above the pilot is to the left. Similar reactions prevail for the up-and-down tiltings of the helicopter obtained in this instance by back and forward motions of-the control stick.

The illustrated embodiments of the invention are in association with a gyro glider, although it will be apparent that the invention may be adapted to powered helicopters, wherein the saving of weight, simplicity of construction, and ease of operation are of the essence. In contrast with the usual control systems utilizing blades individually pivoted on a'hub for adjustment about their feathering axes to vary the total and cyclic pitch, and comparatively elaborate linkage for controlling the blades, this invention provides a tiltable rotor shaft, and a rotor hub pivotally mounted on the rotor shaft so that the axis of rotation of the teetering rotor will follow the tilting motions of the rotor shaft. 7

In one embodiment of the invention, it is intended that the rotor shaft shall turn with the rotor, the rotor hub being rockably mounted on the rotor shaft, and the rotor shaft being rotatably mounted in a spherical bearing in the top of the fuselage so that the rotor shaft may be universally tilted from its normally vertical position.

In second, thirdan'd'fo-urth forms of the invention, the rotor hub is mounted through a teeter hinge over a straight thrust bearing on a non-rotating rotor shaft so that the rotor will bo th turn and teeter on the non-V rotating shaft. Provision is made for tilting the rotor shaft with respect to the fuselage on which it is mounted,

one form including a resilient bearing in the fuselage, another form consisting of gimbals, and still another form comprising a universal joint.

These and other objects will be apparent from the following specificationsanddrawings, in which:

Fig. 1 is a side elevation of a gyro glider embodying one form of the invention;

Fig. 2 is an enlarged view of the upper portion of the fuselage illustrating in vertical cross-section, the details of the Fig. l embodiment;

Fig. 3 is a view similar to Fig. 2 but illustrating a second form of the invention;

Fig. 4 is a view similar to Figs. 2 and 3 but illustrating a third form of the invention; and,

Fig. 5 is a fragmentary view similar to Figs. 2, 3 and 4, but illustrating a fourth form of the invention.

Referring now to the drawings in which like reference numerals denote similar elements, the gyro-glider illustrated in Fig. 1 comprises a fuselage 2 of open-box-like configuration having a landing gear 4, and a cable hitch 6'by which it is towed. Pins 7 stabilize flight and counteract tendencies toward'side thrusts resulting from resilient function in the hub. The pilot sits in a seat 8, and lift results from rotation of'a rotor R comprising rotor blades 10 fastened by plates 12 at their inner ends to a rotor hub 14 by bolts 15. Pillow blocks 16 fastened as indicated at 17 at the center of hub 14 are connected by a teeter pin 18 to the upper end of a rotor shaft 20 which is supported generally vertically between the converging ends of the members 22, 22a at the upper end of the fuselage. It will be understood that while in the present embodiment there are three such members converging inwardly and upwardly. from the respective corners of the fuselage, that various other fuselage structures and configurations may be used. This invention is concerned primarily with the mounting of rotor shaft 20 in fuselage 2, the mounting of rotor hub 1-4 on the rotor shaft, and their relationship to the control stick 30 detailed hereinafter.

Referring now to Fig. 2, there is shown an annular plate-shaped rotor head bearing block 24 secured, as at 25, to the inner ends of fuselage members 22, the rotor head bearing block supportingin its inner periphery an outer race of a spherical bearing 26. An inner hearing race 27 affixed around rotor shaft 20rollingly supports a plurality of barrel-shaped rollers 28 so that, thus rotatably mounted, rotor shaft 20 is free to tilt, within certain prescribed limits, from the vertical. It will be understood that conventional bearing retainers and installation structures are used with the bearing parts.

Control stick 30, whichextends downwardly in front of the pilot station, is fixed, as at 32, to a control stick bearing housing 34 having, near its center, a pair of outer ball races 36, 38 lying opposite inner ball races 40, 4?. on shaft 20. Bearing balls 43 rolling between the inner and outer races provide for free rotation of shaft 20 within the control stick bearing housing. A nut 44 and Washer 45 hold the assembly on the lower end of shaft 20, and a spacer 46 separates the bearing assembliesfrom one another. Thus, when control stick 30 is swung in one direction or another, rotor shaft 20 is correspondingly tilted from its normal generally vertical position.

An anti-rotation and travel-limit coupling is provided between the rotor head bearing block 24 and control stick bearing block 34, this being a-guide strip 47 se cured as at 48 to control stick bearing block 34 and provided, near its other end, with a slot 50 through which projects a pin bolt 52 rigidly projecting from rotor head bearing block 24. By this means, control stick 30 is prevented from turning with rotor shaft 20, and limits the motion of the rotor shaft 20 in its spherical bearing 26 by abutting engagement of pin bolt 52 with the ends of slot 50. The teeter motion of rotor R is limited by stops 54 secured as at 56 to the hub bolts 17 so that teeteringof the rotor assembly beyond desired limits 9 a is prevented by engagement of stops .54 with the top of rotor head assembly block 24.

When control stick 30 is, for instance, pulled back, rotor shaft 20 tilts in spherical bearing 26 so that its upper end tilts forwardly. As the rotor R teeters about teeter pin 18, its axis of rotation soon follows and coincides with the axis of rotor shaft 20 so that a forward drive and upward lift of the craft is imparted by rotor R.

Tilting of the control stick to the right or left results in differential pitch control of the opposite blades 12, 12 in that the angle of attack of the blade momentarily disposed towards the front of the craft is increased, whereas the attack angle of the blade momentarily at the rear is correspondingly decreased.

In the embodiments illustrated in Figs. 3, 4 and 5, the structure and mounting of rotor R on teeter pin 18 is the same as in Figs. 1 and 2. However, rotor shaft a is affixed, as at 58 on a straight thrust bearing 59 having a housing 60, containing a cylinder 61 having outer bearing races 62, 64 therein. A sleeve 66 is formed with inner bearing races 68, 70 sothat bearing ball sets 70, 72 rotatably support rotor shaft 20a. 7

Referring now to Fig. 3, sleeve 66 of the thrust bearing assembly is affixed around a post 76a. Around post 76a are afiixed a spacer 78 and the inner metal annulus 80 of a resilient mount 82 which supports the rotor assembly on fuselage 2. An annular disc 84 of resilient material, such as rubber, fits tightly around inner annulus 80 and is confined within an outer metal annulus secured at 88 to the inner ends of fuselage members 22, 22a. Below inner annulus 80, control stick 30a is welded at 90 to a mounting sleeve 92 held on post 76a by a nut 94 threaded on the lower end of the post. Teeter motion stops 54a secured at 56 by bolt 17 engage the top of outer annulus 86 so as to limit the teeter motion.

In operating the Fig. 3 embodiment, rotor R teeters about pin 18, and shaft 20a is rotatably mounted by thrust bearing 59 on post 76a, the entire assembly being universally tiltable by manipulating control stick 30a. The resilient disc 84 provides elastic centering forces tending to return post 76a to its normally vertical position. Disc 84 also absorbs vertical vibration and prevents rotation of control stick 30a about the rotor axis.

The embodiment illustrated in Fig. 4 is comparable to that of Fig. 3 except in that post 76b is supported for universal tilting movement by gimbals 96, which include a pivot pin 93 extending across an inner ring and through post 76b, and transverse pivot pins 102 pivotally supporting inner ring 100 in an outer ring 104, the outer ring being fastened at 104 to fuselage members 22, 22a. Control stick 30a is secured at 90 to a sleeve 92 held on the reduced lower end 93 of post 76b by nut 94 threaded around the lower end of the post.

As in the previous embodiments, teeter motion stops v 54b are secured at 56 by bolt 17 to hub 14 so that, upon predetermined teetering of rotor R, outer gimbals ring 104 is engaged by stop 54b to prevent excessive teetering motion.

In the Fig. 5 embodiment, the supporting post for thrust bearing 59 is formed with upper and lower portions 76c, 760 connected by a universal joint 106 so that rotor R may be universally tilted. Aflixed around upper portion 76c above the universal joint is a sleeve '92" to which control stick 30a is welded, as at 92. The reduced lower end 108 of lower post portion- 760" is supported in an apertured base plate 106 in which the inner ends of fuselage frame members 22", 22a" are afiixed at 112. Tilt limit stops, not shown, are mounted on base plate 110 toengage upper post portion 76c on four sides thereof upon predetermined tilting of the assembly above the universal joint 1106, thereby stopping upper post portion 76c and the elements supported thereon from flopping over when rotor R isinactive, but permitting sufficient universal tilting of upper post portion 760 to effect the desired controls. A teeter stop 540 secured at 56 by bolt 17 to hub 14 engages an abutment collar 114 welded at 116 around bearing housing 60 to prevent excessive teetering of rotor R.

The invention has been found to be particularly useful in a gyro-glider of such elementary form that it can be assembled by beginners who, self-taught, learn to fly it by being towed behind an automobile or by practicing in the prop-wash of an airplane, or simply kiting in a strong wind.

The invention is equally applicable to powered helicopters and all other types of rotary ring aircraft.

The invention described above is not limited to the illustrated details, but is intended to cover all substitutions, modifications and equivalents within the scope of the following claims.

I claim:

1. In a rotating wing aircraft, a fuselage, a rotor com prising a hub and blades afiixed to and radiating therefrom, a normally generally vertical rotor shaft, bearing means rotably supporting said hub on'said shaft whereby the rotative plane of said blade may tilt with respect to the axis of said shaft, universal pivot means supporting said shaft in said fuselage whereby said shaft may be tilted with respect to said fuselage, said universal pivot means comprising a resiliently deformable supporting member connected at spaced portions thereof to said shaft and fuselage, respectively, said member providing elastic centering forces tending to maintain said shaft vertical and providing a resilient support for said shaft in said fuselage, and control means for tilting said shaft, said member comprising a generally flat annular disc having inner and outer peripheries, the connection at spaced portions thereof to said shaft and fuselage comprising means affixing the inner periphery of the disc around the shaft and means affixing the fuselage to the outer periphery of the disc, substantially the entire weight of the aircraft being supported by said disc.

2. In a rotating wing aircraft, a fuselage including a plurality of frame members converging at the upper end of the frame, a ring rigidly affixed to the converging ends of said frame members, a substantially flat annular disc of resiliently deformable material having an outer periphery compressed within said ring, said disc being disposed substantially horizontally and the diametrical extent of the material forming the upper and lower sides thereof being substantially greater than the axial thickness thereof, a normally vertical shaft extending axially within the inner periphery of the disc, means substantially rigidly afiixing the inner periphery of the disc around said shaft, a bearing rotatably mounted on said shaft above said disc, a rotor comprising a hub and blades radiating therefrom, a teeter connection between said hub and said bearing, and a control stick rigidly affixed on said shaft below said disc, the resilient deformability of said ring providing for universal tilting movements of said shaft by said control stick and also providing elastic centering forces tending to maintain said shaft in vertical disposition.

References Cited in the file of this patent UNITED STATES PATENTS 2,224,357 Pecker Dec. 10, 1940 2,264,942 Larsen Dec. 2, 1941 2,429,502 Young Oct. 21, 1947 2,510,006 Young May 30, 1950 2,631,679 Hiller Mar. 17, 1953 2,658,575 Stone Nov. 10, 1953 2,677,431 Prince May 4, 1954 2,689,011 Zakhartchenko Sept. 14, 1954 2,702,601 Nagler Feb. 22, 1955 FOREIGN PATENTS 459,070 Canada Aug. 23, 1949

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US2224357 *Aug 4, 1938Dec 10, 1940Joseph S PeckerRemote control steering apparatus for flying machines
US2264942 *May 5, 1939Dec 2, 1941Autogiro Co Of AmericaRotative winged aircraft
US2429502 *Aug 21, 1943Oct 21, 1947Arthur M YoungCaptive helicopter-kite means
US2510006 *Apr 5, 1946May 30, 1950Bell Aircraft CorpRotating wing aircraft
US2631679 *Jun 25, 1951Mar 17, 1953Hiller HelicoptersRotor head for rotary wing aircraft
US2658575 *Jul 17, 1946Nov 10, 1953Peter T StoneHelicopter rotor
US2677431 *Oct 21, 1950May 4, 1954Gen ElectricUniversal rotor mounting
US2689011 *Feb 9, 1948Sep 14, 1954Mcdonnell Aircraft CorpHelicopter rotor construction
US2702601 *Apr 26, 1952Feb 22, 1955Nagler Helicopter Company IncJet driven helicopter rotor system
CA459070A *Aug 23, 1949Autogiro Co Of AmericaAircraft equipped with a sustaining rotor
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US3080001 *Oct 7, 1959Mar 5, 1963Lockheed Aircraft CorpHelicopter
US3174708 *Aug 28, 1961Mar 23, 1965Miles Melvin ORotary wing aircraft control system
US3207226 *Sep 10, 1964Sep 21, 1965Frank W CaldwellRotor driving mechanism
US3233679 *Nov 19, 1963Feb 8, 1966Rotorcraft S A Proprietary LtdRotating wing aircraft
US4148594 *Jun 10, 1977Apr 10, 1979Ssp Agricultural Equipment, Inc.Fan blade for wind machines
US4566856 *Sep 27, 1984Jan 28, 1986United Technologies CorporationHelicopter gimbal rotor
US4569629 *Sep 27, 1984Feb 11, 1986United Technologies CorporationHelicopter gimbal rotor
US4580945 *Sep 27, 1984Apr 8, 1986United Technologies CorporationHelicopter gimbal rotor
US4913376 *Oct 21, 1988Apr 3, 1990Black Franklin EVTLH autogyro
US5098033 *Jan 11, 1990Mar 24, 1992Rotary Air Force Inc.Gyroplane with tilting mast
US5996934 *Nov 24, 1997Dec 7, 1999Murph; Ellis G.Tethered autogyro
US6598827Oct 7, 2002Jul 29, 2003Tom KusicTelescopic vertical take-off aircraft
US7037072Mar 3, 2004May 2, 2006Carson Franklin DRotor head for a rotary-wing aircraft
US7438260Nov 26, 2004Oct 21, 2008Tom KusicVertical take-off aircraft—C
US8042762Oct 28, 2009Oct 25, 2011Tom KusicVertical take-off tilt rotor aircraft
US8196854Apr 21, 2011Jun 12, 2012Tom KusicTilt rotor aircraft with tilting tail rotor—TT
DE3729231A1 *Sep 2, 1987Mar 16, 1989Hans MuellerVTOL (vertical take-off and landing) aircraft
EP0289671A1 *May 5, 1987Nov 9, 1988Property Associates LimitedAircraft
Classifications
U.S. Classification416/148, 244/17.25
International ClassificationB64C27/00, B64C27/41, B64C27/52, B64C27/32
Cooperative ClassificationB64C27/52, B64C27/41
European ClassificationB64C27/52, B64C27/41