Patent US4458862A successfully refreshed from Google Patents.
US4458862A
Expired / Lapsed
US
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Antiresonant suspension device for helicopter
Assignee: Airbus Group SAS
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Filing: 1983-02-28
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Granted: 1984-07-10
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Expires: 2003-02-28
Abstract
Abstract The invention relates to aeronautics in general, and in particular to a suspension device for helicopter, comprising a flexible mounting plate at the center of which is fixed the bottom of the main gear box whose top is supported by hinged oblique bars. The mounting plate offers radial arms hinged to the base of the bars and to the fuselage of the helicopter. These arms bear flapping weights creating forces of inertia with reactions at the attachment points of direction opposite the elastic reactions of deformation of the mounting plate. A device of this type enables the vibrations on board helicopters to be reduced.
Inventors
- 👤 Rene L. Mouille
- 👤 Gerard C. L. Genoux
- 👤 Pierre E. Hege
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-31 09:44
CPC Classifications
B; B64; B64C; B64C27/00; B64C27/001; F; F16; F16F; F16F7/00; F16F7/10; F16F7/1022; B64C2027/002; B64C2027/005; Y; Y10; Y10S; Y10S416/00; Y10S416/50
Claims Analysis
Total Claims: 13
Claim 1
Independent Claim
207 words
An anti-resonant suspension system for supporting the rotor and gear box of a helicopter on the fuselage thereof comprising a mounting plate having a central part on which is secured the bottom of the gear box and a plurality of radially extending flexible arms disposed coplanar uniformly about the central axis of said gear box, said arms being rigid within their plane and flexible in a direction perpendicular thereto, each of said arms being joined at its end to said fuselage, a plurality of oblique connecting bars corresponding in number to the number of said arms, said bars being joined at one end to the upper end of said gear box and at its other end to a respective one of said arms at a point along said arm adjacent to but spaced latterally from the joint between said arms and said fuselage, said respective joints permitting flexing of each of said arms along their length by deformation in a direction perpendicular to the plane of said arms, each of said arms having a lever integral with its outer end and extending freely therefrom in the plane of said arm, said lever having a flapping weight secured to the free end thereof substantially coplanar with said arm.
Claim 2
Dependent Claim
207 words
An anti-resonant suspension system for supporting the rotor and gear box of a helicopter on the fuselage thereof comprising a mounting plate having a central part on which is secured the bottom of the gear box and a plurality of radially extending flexible arms disposed coplanar uniformly about the central axis of said gear box, said arms being rigid within their plane and flexible in a direction perpendicular thereto, each of said arms being joined at its end to said fuselage, a plurality of oblique connecting bars corresponding in number to the number of said arms, said bars being joined at one end to the upper end of said gear box and at its other end to a respective one of said arms at a point along said arm adjacent to but spaced latterally from the joint between said arms and said fuselage, said respective joints permitting flexing of each of said arms along their length by deformation in a direction perpendicular to the plane of said arms, each of said arms having a lever integral with its outer end and extending freely therefrom in the plane of said arm, said lever having a flapping weight secured to the free end thereof substantially coplanar with said arm.
Claim 3
Dependent Claim
42 words
The device of claim 1, wherein the joint by which each flexible arm is connected to the fuselage is a bearing joint whose axis is contained in the plane of the mounting plate and perpendicular to the longitudinal direction of said arm.
Claim 4
Dependent Claim
28 words
The device of claim 2, wherein the joint by which each flexible arm is connected to the lower end of the corresponding connecting bar is a ball joint.
Claim 5
Dependent Claim
22 words
The device of claim 1, wherein the joint by which each flexible arm is connected to the fuselage is a ball joint.
Claim 6
Dependent Claim
28 words
The device of claim 4, wherein the joint by which each flexible arm is connected to the lower end of the corresponding connecting bar is a bearing joint.
Claim 7
Dependent Claim
25 words
The device of claim 1, wherein the flexible arms have a width which decreases from the central part of the mounting plate towards their end.
Claim 8
Dependent Claim
18 words
The device of claim 1, wherein the flexible arms comprise an inner opening extending along their longitudinal axis.
Claim 9
Dependent Claim
52 words
The device of claim 7, wherein the lever bearing the flapping weight of each flexible arm is constituted by an extension of said arm directed towards the inside, the flapping mass being located in the opening of the flexible arm, between the joint on the fuselage and the centre of the plate.
Claim 10
Dependent Claim
47 words
The device of claim 1, wherein the lever bearing the flapping weight of each flexible arm is constituted by an extension of said arm directed towards the outside, the flapping weight being located beyond the joint on the fuselage with respect to the centre of the plate.
Claim 11
Dependent Claim
32 words
The device of claim 1, wherein the joint connecting each flexible arm to the fuselage is located between the flapping weight and the joint connecting said arm to the corresponding connecting bar.
Claim 12
Dependent Claim
32 words
The device of claim 1, wherein the joint connecting each flexible arm to the corresponding connecting bar is located between the flapping weight and the joint connecting said arm to the fuselage.
Claim 13
Dependent Claim
19 words
The device of claim 1, wherein the lever bearing each flapping weight is connected to the corresponding flexible arm.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1987-07-10 | 1988-01-09 | 1988-07-10 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1991-07-10 | 1992-01-09 | 1992-07-10 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1995-07-10 | 1996-01-09 | 1996-07-10 | $7700.00 | Window Closed / Lapsed |