US4028000A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Blade connection for helicopter rotor blades
Assignee: Airbus Defence and Space GmbH
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Filing: 1975-10-31
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Granted: 1977-06-07
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Expires: 1995-10-31
Abstract
Abstract Resilient drive means for a helicopter rotor blade. The rotor blade is pivotally supported on a stub shaft which is in turn supported on the rotor hub. First means are fixed to the rotor blade and second means fixed to the stub shaft with resilient and adjustable means positioned therebetween for controlling the angular relationship between the rotor blade and the stub shaft. In this embodiment, said first means comprise a shoulder which projects from the rotor blade and the second means comprise a rectangular hollow frame which is fixed to the stub shaft. The shoulder projects into the hollow frame. Threaded means acting through resilient means holds the first and second means in selected pivotal adjustment with respect to each other but the resilient component thereof permits sufficient slight lead lag movement therebetween as to effect damping of the lead lag mode of the rotorblade. The adjustment capability permits sufficient adjustment of the blade with respect to the hub to ensure desired balance between the several blades of a given rotor.
Inventors
- 👤 Emil Weiland
- 👤 Alois Schwarz
- 👤 Hubert Frommlet
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-31 21:09
CPC Classifications
B; B64; B64C; B64C27/00; B64C27/001; B64C27/51
Claims Analysis
Total Claims: 11
Claim 1
Independent Claim
83 words
In a blade connection for helicopter rotor blades, comprising a blade fastening pin and a damped connection between a blade mounting member and a rotor hub, the improvement comprising a shoulder secured on said blade mounting member, a carrier bracket secured on said rotor hub and supporting two oppositely oriented adjustable pressure screws adjustable toward and away from one another in direction of rotation around the axis of said blade fastening pin and elastomeric dampers inserted between said shoulder and said pressure screws.
Claim 2
Dependent Claim
83 words
In a blade connection for helicopter rotor blades, comprising a blade fastening pin and a damped connection between a blade mounting member and a rotor hub, the improvement comprising a shoulder secured on said blade mounting member, a carrier bracket secured on said rotor hub and supporting two oppositely oriented adjustable pressure screws adjustable toward and away from one another in direction of rotation around the axis of said blade fastening pin and elastomeric dampers inserted between said shoulder and said pressure screws.
Claim 3
Dependent Claim
26 words
The improved blade connection according to claim 1, wherein said carrier bracket is secured to said rotor hub by means of at least one releasable bolt.
Claim 4
Dependent Claim
27 words
The improved blade connection according to claim 2, wherein the axis of said bolt is arranged parallel with respect to the axis of said blade fastening pin.
Claim 5
Dependent Claim
32 words
The improved blade connection according to claim 1, wherein said elastomeric dampers consist of elastomer layers which are layered in said direction of rotation around the axis of said blade fastening pin.
Claim 6
Dependent Claim
18 words
The improved blade connection according to claim 4, wherein metal plates are fixed on the outer elastomer layers.
Claim 7
Dependent Claim
23 words
The improved blade connection according to claim 1, wherein said elastomeric dampers have side walls which face and engage surfaces on said shoulder.
Claim 8
Dependent Claim
31 words
The improved blade connection according to claim 6, wherein said side walls of said elastomeric dampers are built of elastomeric layers which are substantially parallel with said surfaces of said shoulder.
Claim 9
Dependent Claim
20 words
The improved blade connection according to claim 4, wherein said direction of rotation is the direction of lead lag motion.
Claim 10
Dependent Claim
187 words
A damped blade connection between a helicopter rotor blade and a rotatable hub comprising: blade mounting means on said blade; hub mounting means on said hub; blade fastening pin means for securing said blade and hub mounting means together and for relative movement about the axis of said blade fastening pin means; shoulder means mounted on said blade mounting means and extending in a direction transverse of the axis of said blade fastening pin means, said shoulder means having a pair of oppositely facing surfaces thereon facing in circumferential directions of said blade fastening pin means; carrier bracket means secured to said hub mounting means and including a pair of spaced support means thereon, said shoulder means being received in the spacing between said support means with each of said oppositely facing surfaces being opposed by one of said support means; elastomeric means positioned between said of said surfaces and one of said opposed surface means; and force applying means on each of said support means for engaging said elastomeric means and effecting a compression of said elastomeric means between said surfaces and said force applying means.
Claim 11
Dependent Claim
187 words
A damped blade connection between a helicopter rotor blade and a rotatable hub comprising: blade mounting means on said blade; hub mounting means on said hub; blade fastening pin means for securing said blade and hub mounting means together and for relative movement about the axis of said blade fastening pin means; shoulder means mounted on said blade mounting means and extending in a direction transverse of the axis of said blade fastening pin means, said shoulder means having a pair of oppositely facing surfaces thereon facing in circumferential directions of said blade fastening pin means; carrier bracket means secured to said hub mounting means and including a pair of spaced support means thereon, said shoulder means being received in the spacing between said support means with each of said oppositely facing surfaces being opposed by one of said support means; elastomeric means positioned between said of said surfaces and one of said opposed surface means; and force applying means on each of said support means for engaging said elastomeric means and effecting a compression of said elastomeric means between said surfaces and said force applying 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) | 1980-06-06 | 1980-12-06 | 1981-06-07 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1984-06-06 | 1984-12-06 | 1985-06-07 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1988-06-06 | 1988-12-06 | 1989-06-07 | $7700.00 | Window Closed / Lapsed |