Patent US788756A successfully refreshed from Google Patents.
Patent US4527951A successfully refreshed from Google Patents.
US4527951A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Pendulum for damping or eliminating low excitation frequencies
Assignee: Airbus Defence and Space GmbH
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Filing: 1983-07-11
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Granted: 1985-07-09
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Expires: 2003-07-11
Abstract
Abstract Low excitation frequencies of a structural component, for example of a heopter rotor blade or the like, are damped or eliminated by a pendulum device connected to the component, the excitation frequency or frequencies of which are to be damped or eliminated. In a helicopter rotor blade the pendulum device is preferably connected to the blade neck near the rotor head. The pendulum device has a plurality of pendulum bodies coupled to each other for forming a multiple pendulum in which these pendulum bodies are so tuned relative to each other that the multiple pendulum has several eigenfrequencies.
Inventors
- 👤 Ferdinand Trier
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-29 06:53
CPC Classifications
B; B64; B64C; B64C27/00; B64C27/001; F; F16; F16F; F16F15/00; F16F15/10; F16F15/14; F16F15/1407; B64C2027/005; Y; Y10; Y10S; Y10S416/00; Y10S416/50
Claims Analysis
Total Claims: 9
Claim 1
Independent Claim
100 words
A pendulum apparatus for damping or eliminating low excitation frequencies of a helicopter rotor blade, comprising at least one multiple pendulum device (5) including at least two individual pendulum bodies (8, 14), first means (11) operatively coupling said at least two individual pendulum bodies (8, 14) to each other to form said multiple pendulum device, said individual pendulum bodies (8, 14) being tuned to each other so that the respective multiple pendulum device has several eigenfrequencies, and second means for operatively connecting said multiple pendulum device (5) to said helicopter rotor blade for damping or eliminating said low excitation frequencies.
Claim 2
Dependent Claim
100 words
A pendulum apparatus for damping or eliminating low excitation frequencies of a helicopter rotor blade, comprising at least one multiple pendulum device (5) including at least two individual pendulum bodies (8, 14), first means (11) operatively coupling said at least two individual pendulum bodies (8, 14) to each other to form said multiple pendulum device, said individual pendulum bodies (8, 14) being tuned to each other so that the respective multiple pendulum device has several eigenfrequencies, and second means for operatively connecting said multiple pendulum device (5) to said helicopter rotor blade for damping or eliminating said low excitation frequencies.
Claim 3
Dependent Claim
79 words
The apparatus of claim 1, wherein said at least two individual pendulum bodies of said multiple pendulum device comprise a hollow pendulum body forming a housing having a bearing surface forming said first coupling means, and a roller body means arranged in said housing for rolling back and forth in an oscillation direction on said bearing surface forming said first coupling means, said roller body means being able to additionally oscillate in a rolling manner about its rest position.
Claim 4
Dependent Claim
11 words
The apparatus of claim 2, wherein said bearing surface is curved.
Claim 5
Dependent Claim
27 words
The apparatus of claim 3, wherein said roller body means comprise a sphere and wherein said curved bearing surface is a shell part of a hollow sphere.
Claim 6
Dependent Claim
27 words
The apparatus of claim 3, wherein said roller body means comprise a cylinder, and wherein said curved bearing surface is a shell part of a hollow cylinder.
Claim 7
Dependent Claim
42 words
The apparatus of claim 1, comprising two multiple pendulum device (5) and wherein said second connecting means comprise a shaft, bearing means operatively mounting said shaft to said helicopter rotor blade, said two multiple pendulum devices being rigidly secured to said shaft.
Claim 8
Dependent Claim
41 words
The apparatus of claim 6, wherein said helicopter rotor blade has a longitudinal axis, said connecting shaft extending crosswise relative to said longitudinal axis, whereby said two multiple pendulum devices are rotatable with said coupling shaft relative to said longitudinal axis.
Claim 9
Dependent Claim
22 words
The apparatus of claim 5, wherein said cylinder roller has conical ends resting against the inner side surface of said bearing housing.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1988-07-08 | 1989-01-07 | 1989-07-09 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1992-07-08 | 1993-01-07 | 1993-07-09 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1996-07-08 | 1997-01-07 | 1997-07-09 | $7700.00 | Window Closed / Lapsed |