US4252503A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Rotor blade especially for rotary wing aircraft
Assignee: Airbus Helicopters Deutschland GmbH
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Filing: 1979-02-26
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Granted: 1981-02-24
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Expires: 1999-02-26
Abstract
Abstract A rotor blade has a neck section which connects the blade proper to a rotoread at the blade root. The neck section is flexible against bending in the lead-lag direction and in the flapping direction. A carrier member is located alongside or inside the neck section but spaced from the neck section. The carrier member is resistant against bending at least in the lead-lag direction or in the flapping direction. The carrier member is rigidly connected at its one end to the blade proper. A layer of a damping material is operatively interposed between the carrier member and the neck section, preferably at the blade root end of the neck section, whereby blade vibrations preferably in the lead-lag direction are damped and substantially prevented from entering into the rotor head.
Inventors
- 👤 Peter M. Wackerle
- 👤 Otmar Friedberger
- 👤 Emil Weiland
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-04 21:18
CPC Classifications
B; B64; B64C; B64C27/00; B64C27/001; B64C27/32; B64C27/46; B64C27/51
Claims Analysis
Total Claims: 10
Claim 1
Independent Claim
171 words
A hingeless rotor blade, especially for rotary wing aircraft, comprising blade means, a blade root and a blade neck section (2 or 5) operatively connecting said blade means and said blade root, said blade neck section (2 or 5) being flexible relative to bending loads in the lead-lag direction and in the flapping direction, carrier means (3 or 6) resistant against bending in at least one direction, means rigidly connecting said carrier means (2 or 6) to said blade means, and damping means (4 or 8) directly and operatively interposed between said blade neck section (2 or 5) and said carrier means (3 or 6), whereby said carrier means are operatively connected in parallel to said blade neck section and operate as lever means when the blade neck section is subject to a bending load for transmitting a force into said damping means in accordance with the mechanical advantage of said lever means for substantially damping blade vibrations in accordance with said mechanical advantage and in said at least one direction.
Claim 2
Dependent Claim
171 words
A hingeless rotor blade, especially for rotary wing aircraft, comprising blade means, a blade root and a blade neck section (2 or 5) operatively connecting said blade means and said blade root, said blade neck section (2 or 5) being flexible relative to bending loads in the lead-lag direction and in the flapping direction, carrier means (3 or 6) resistant against bending in at least one direction, means rigidly connecting said carrier means (2 or 6) to said blade means, and damping means (4 or 8) directly and operatively interposed between said blade neck section (2 or 5) and said carrier means (3 or 6), whereby said carrier means are operatively connected in parallel to said blade neck section and operate as lever means when the blade neck section is subject to a bending load for transmitting a force into said damping means in accordance with the mechanical advantage of said lever means for substantially damping blade vibrations in accordance with said mechanical advantage and in said at least one direction.
Claim 3
Dependent Claim
22 words
The rotor blade of claim 1, wherein said carrier means comprise plate means arranged on the pressure side of said blade means.
Claim 4
Dependent Claim
22 words
The rotor blade of claim 1, wherein said carrier means comprise plate means arranged on the suction side of said blade means.
Claim 5
Dependent Claim
31 words
The rotor blade of claim 1, wherein said carrier means comprise a blade core extension forming an integral part of said blade means and extending longitudinally through said blade neck section.
Claim 6
Dependent Claim
27 words
The rotor blade of claim 4, wherein said damping means are operatively interposed between said blade neck section and said blade core extension at said blade root.
Claim 7
Dependent Claim
24 words
The rotor blade of claim 1, wherein said carrier means comprise plate means arranged along at least one side of said blade neck section.
Claim 8
Dependent Claim
25 words
The rotor blade of claim 6, wherein said damping means are operatively interposed between said plate means and said neck section at said blade root.
Claim 9
Dependent Claim
38 words
The rotor blade of claim 1, wherein said carrier means comprise two plates and wherein said blade neck section is sandwiched between said two plates substantially without direct contact between said blade neck section and said carrier plates.
Claim 10
Dependent Claim
71 words
The rotor blade of claim 1, wherein said carrier means comprise a core (6) stiff against bending and forming an extension of said blade means, and wherein said blade neck section comprises a hollow flexible sleeve (5), said stiff bar extending longitudinally through said hollow sleeve, said stiff core (6) acting as a lever arm relative to said hollow, flexible sleeve (5) for causing a shearing deformation of said damping means.
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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) | 1984-02-24 | 1984-08-25 | 1985-02-24 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1988-02-24 | 1988-08-25 | 1989-02-24 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1992-02-24 | 1992-08-25 | 1993-02-24 | $7700.00 | Window Closed / Lapsed |