US4111386A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Helicopter rotor and transmission mounting and vibration isolation system
Assignee: RTX Corp
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Filing: 1976-12-09
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Granted: 1978-09-05
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Expires: 1996-12-09
Abstract
Abstract A helicopter rotor and transmission mounting and vibration isolation system in which the transmission is supported from the fuselage by a plurality of elastomeric mounts which are selectively positioned and focused to establish a system roll axis and a system pitch axis on opposite sides of the elastomeric mounts and which mount members are of selected stiffness to establish selected roll stiffness and selected pitch stiffness of the system, to establish the natural frequencies of the system sufficiently below the blade passage frequency to minimize the response of the fuselage to forces and moments imparted by the helicopter rotor and to provide selected torque restraint and lift restraint for the system.
Inventors
- 👤 Irwin Jeffrey Kenigsberg
- 👤 Larry Bruce Eastman
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-02 21:36
CPC Classifications
B; B64; B64C; B64C27/00; B64C27/001; B64C2027/002; Y; Y10; Y10S; Y10S416/00; Y10S416/50
Claims Analysis
Total Claims: 11
Claim 1
Independent Claim
318 words
A helicopter having: (A) a main lift rotor, (B) a transmission supporting and driving the rotor for rotation about an axis of rotation, (C) a fuselage, and (D) a rotor and transmission support and vibration isolation system supporting the transmission from the fuselage and including: (1) a plurality of elastomeric mount members each of selected compression stiffness and each having a selectively oriented axis and being connected to the fuselage and supporting the transmission therefrom and comprising: (a) alternate layers of elastomer and metal laminates stacked in compression between the fuselage and the transmission with an elastomer layer in contact with the fuselage and the transmission to thereby reduce the transmission of acoustic vibration therebetween to reduce internal noise in the helicopter and with the laminates positioned concentrically about the mount member axis so that said laminates are oriented normal to said axis, and with each mount member defining a focal line coincident with its axis so that the roll and pitch shear lines for each elastomer laminate are normal to the mount focal line and with each mount member focal line intersecting a corresponding focal line of other mount members so as to define a mount system roll axis extending longitudinally of the fuselage and displaced vertically on one side of said mount members and a mount system pitch axis extending transversely of the fuselage and displaced vertically on the other side of said mount members from said roll axis, and so that said axes are off-set from said mount members a selected distance to establish vibration isolation through said mount members between said fuselage and said transmission about both said pitch and said roll axes and so that with said system pitch and roll axes so positioned said mount members along provide substantial system yaw restraint which is accomplished by compression loading of the elastomer laminates of the mount members in response to transmission yaw motion.
Claim 2
Dependent Claim
318 words
A helicopter having: (A) a main lift rotor, (B) a transmission supporting and driving the rotor for rotation about an axis of rotation, (C) a fuselage, and (D) a rotor and transmission support and vibration isolation system supporting the transmission from the fuselage and including: (1) a plurality of elastomeric mount members each of selected compression stiffness and each having a selectively oriented axis and being connected to the fuselage and supporting the transmission therefrom and comprising: (a) alternate layers of elastomer and metal laminates stacked in compression between the fuselage and the transmission with an elastomer layer in contact with the fuselage and the transmission to thereby reduce the transmission of acoustic vibration therebetween to reduce internal noise in the helicopter and with the laminates positioned concentrically about the mount member axis so that said laminates are oriented normal to said axis, and with each mount member defining a focal line coincident with its axis so that the roll and pitch shear lines for each elastomer laminate are normal to the mount focal line and with each mount member focal line intersecting a corresponding focal line of other mount members so as to define a mount system roll axis extending longitudinally of the fuselage and displaced vertically on one side of said mount members and a mount system pitch axis extending transversely of the fuselage and displaced vertically on the other side of said mount members from said roll axis, and so that said axes are off-set from said mount members a selected distance to establish vibration isolation through said mount members between said fuselage and said transmission about both said pitch and said roll axes and so that with said system pitch and roll axes so positioned said mount members along provide substantial system yaw restraint which is accomplished by compression loading of the elastomer laminates of the mount members in response to transmission yaw motion.
Claim 3
Dependent Claim
50 words
A helicopter according to claim 1 wherein said mount elastomer laminates are of selected shear and compressive stiffness to establish transmission natural frequencies sufficiently below the rotor blade passage frequency so as to isolate the fuselage from blade passage frequency forces and to also establish the magnitude of torque restraint.
Claim 4
Dependent Claim
29 words
A helicopter according to claim 1 wherein said roll axis is above the mount members and the pitch axes is below the mount members to provide transmission yaw restraint.
Claim 5
Dependent Claim
34 words
A helicopter according to claim 3 and including at least one in-plane vibration absorber operatively associated with the rotor so that rotor motion about said pitch axis is substantially in-plane to maximize absorber efficiency.
Claim 6
Dependent Claim
24 words
A helicopter according to claim 1 wherein said mount members are preloaded sufficiently to keep them in compression loading during all modes of operation.
Claim 7
Dependent Claim
24 words
A helicopter according to claim 1 wherein said mount members are selectively constructed, positioned, and oriented to produce differential stiffness therein in orthogonal directions.
Claim 8
Dependent Claim
64 words
A helicopter according to claim 6 wherein said plurality of mount members comprise four mount members with two such mount members being forward mount members located forward of the rotor axis of rotation and on opposite lateral sides thereof and with the two remaining mount members being after mount members located aft of said rotor axis of rotation and on opposite lateral sides thereof.
Claim 9
Dependent Claim
119 words
A helicopter according to claim 7 wherein said after mount members are oriented so that the after mount member focal lines intersect on said roll axis, so that the forward mount member focal lines intersect on said roll axis, and so that the focal lines of the two mounts on one lateral side of the transmission intersect on the pitch axis, and so that the focal lines of the two mounts on the opposite lateral side of the transmission intersect on said pitch axis to thereby establish said roll and pitch axes offset above and below said transmission, respectively, for transmission yaw restraint which is accomplished by placing the mount member elastomer in compression with the mounts so oriented.
Claim 10
Dependent Claim
17 words
A helicopter according to claim 1 and including positive stop means operatively associated with said mount members.
Claim 11
Dependent Claim
29 words
A helicopter according to claim 1 wherein said roll axis is below the transmission base and the pitch axis is above the transmission base to provide transmission yaw restraint.
References Cited (Backward Citations)
US2648509A
Cited
US2722391A
Cited
GB1380710A
Cited
US3920202A
Cited
US3932060A
Cited
US3858831A
Cited
US4014484A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1981-09-04 | 1982-03-06 | 1982-09-05 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1985-09-04 | 1986-03-06 | 1986-09-05 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1989-09-04 | 1990-03-06 | 1990-09-05 | $7700.00 | Window Closed / Lapsed |