Laminated abutment, a rotor provided with such an abutment, and an aircraft

Patent metadata

Field	Value
Publication number	US-9382803-B2
Application number	US-201213719817-A
Country	US
Kind code	B2
Filing date	Dec 19, 2012
Priority date	Dec 27, 2011
Publication date	Jul 5, 2016
Grant date	Jul 5, 2016

Abstract

A laminated abutment ( 10 ) comprising an inner strength member ( 11 ), an outer strength member ( 12 ), and an elastomeric member ( 15 ) comprising a stack of main layers ( 20, 30 ) that are flexible and of secondary layers ( 40 ) that are rigid. The stack comprises at least one first main layer ( 20 ) and at least one second main layer ( 30 ), each first main layer ( 20 ) presenting, in a lead-lag plane (PTRA), a first thickness (e 1 ) that varies between a minimum first thickness (e 1 min ) on the pitch-variation axis (AXPAS) and a maximum first thickness (e 1 max ) on the flapping axis (AXBAT), and each second main layer ( 30 ) presenting, in a lead-lag plane (PTRA), a second thickness (e 2 ) that varies between a minimum second thickness (e 2 min ) on the flapping axis (AXBAT) and a maximum second thickness (e 2 max ) on the pitch-variation axis (AXPAS).

First claim

What is claimed is:

1. A laminated abutment comprising an inner strength member and an outer strength member, the abutment further comprising an elastomeric member comprising a stack of main layers and of secondary layers, each main layer comprising a single flexible material and each secondary layer comprising a single rigid material, a strength member of the inner strength member and the outer strength member being able to perform rotary movements relative to the other strength member of the inner strength member and the outer strength member about a flapping axis, about a lead-lag axis, and about a pitch-variation axis the flapping axis and the pitch-variation axis having a geometrical center in common, the pitch-variation axis and the flapping axis co-operating to define a lead-lag plane, the pitch-variation axis and the lead-lag axis co-operating to define a flapping plane, and the lead-lag axis and the flapping axis co-operating to define a plane of pitch-angle variation, each secondary layer being bonded to each adjacent main layer; wherein the stack comprises at least one first main layer and at least one second main layer, each first main layer presenting, in the lead-lag plane, a first thickness that varies between a minimum first thickness on the pitch-variation axis and a maximum first thickness on the flapping axis, and each second main layer presenting, in the lead-lag plane, a second thickness that varies between a minimum second thickness on the flapping axis and a maximum second thickness on the pitch-variation axis, the thickness of each main layer being constant in the flapping plane and in the plane of pitch-angle variation.

2. The laminated abutment according to claim 1 , wherein the laminated abutment comprises a first sub-assembly of a respective first layer of the at least one first main layer that is arranged between the inner strength member and a second sub-assembly of a respective second layer of the at least one second main layer, the second sub-assembly being arranged between the first sub-assembly and the outer strength member, the first sub-assembly and the second sub-assembly including a common secondary layer.

3. The laminated abutment according to claim 1 , wherein the flexible material of the main layers includes an elastomer.

4. The laminated abutment according to claim 1 , wherein the rigid material of the secondary layers includes metal or reinforced plastics material.

5. The laminated abutment according to claim 1 , wherein the outer strength member is connected to a blade.

6. The laminated abutment according to claim 1 , wherein the inner strength member is fastened to the hub.

7. The laminated abutment according to claim 1 , wherein, in the lead-lag plane, each main layer and each secondary layer presents first symmetry about the pitch-variation axis.

8. The laminated abutment according to claim 7 , wherein, in the lead-lag plane, each main layer and each secondary layer presents second symmetry about the flapping axis.

9. The laminated abutment according to claim 1 , wherein each secondary layer presents a third thickness that is constant in the flapping plane, the lead-lag plane, and the plane of pitch-angle variation.

10. The laminated abutment according to claim 1 , wherein at least one secondary layer has a third thickness that varies, with a sub-portion comprising the secondary layer of varying third thickness and a main layer adjacent to the secondary layer of thickness that is constant.

11. The laminated abutment according to claim 1 , wherein each secondary layer arranged between the inner strength member and the outer strength member is arranged between a respective first main layer of the at least one first main layer and a respective second layer of the at least one second main layer.

12. The laminated abutment according to claim 1 , wherein the lead-lag axis is offset from the geometrical center.

13. The laminated abutment according to claim 1 , wherein the first thickness varies continuously between the minimum first thickness and the maximum thickness, the second thickness varying continuously between the minimum second thickness and the maximum second thickness on the pitch-variation axis.

14. The laminated abutment of claim 1 , wherein the maximum first thickness exceeds the minimum first thickness, and wherein the maximum second thickness exceeds the minimum second thickness.

15. A rotor provided with a hub and with a plurality of blades, each blade being connected to the hub by a laminated abutment in accordance with claim 1 .

16. An aircraft, including a rotor according to claim 15 .

17. A laminated abutment comprising:
an inner strength member;
an outer strength member disposed about the inner strength member; and
an elastomeric member having a first flexible layer, a second flexible layer, and a rigid layer disposed between and bonded to the first flexible layer and the second flexible layer, the first flexible layer and the second flexible layer having a same material composition, the elastomeric layer having a lead-lag plane, a pitch-angle plane orthogonal to the lead-lag plane, a flapping motion plane orthogonal to the lead-lag plane and to the pitch-angle plane, a pitch axis extending within the lead-lag plane, and a flapping axis extending orthogonal to the pitch axis within the lead-lag plane, wherein in the lead-lag plane the first flexible layer has a first varying thickness with a first flexible layer maximum thickness on the flapping axis and a first flexible layer minimum thickness on the pitch axis, in the lead-lag plane the second flexible layer has a second varying thickness with a second flexible layer maximum thickness on the pitch axis and a second flexible layer minimum thickness on the flapping axis, and in the flapping motion plane and the pitch-angle plane the first flexible layer has a first generally constant thickness and the second layer has a second generally constant thickness.

18. A rotorcraft comprising:
a fuselage;
a rotor hub projected from and rotatably coupled to the fuselage, the rotor hub having an axis of rotation;
a rotor blade extending from the rotor hub and having a blade root, a blade tip, a pitch axis extending from the blade root to the blade tip; and
an abutment having a first member coupled to the rotor hub, a second member coupled to the blade root, and an elastomeric member disposed between the first member and the second member, the elastomeric member having a first flexible layer, a second flexible layer, and a rigid layer disposed between and bonded to the first flexible layer and the second flexible layer, the first flexible layer and the second flexible layer having a same material composition, the abutment having a lead-lag axis extending generally parallel to the axis of rotation, a flapping axis extending perpendicular to the pitch axis and the lead-lag axis, a lead-lag plane defined by the flapping axis and the pitch axis, a flapping motion plane defined by the lead-lag axis and the pitch axis, and a pitch-angle plane defined by the lead-lag axis and the flapping axis, wherein in the lead-lag plane the first flexible layer has a first varying thickness with a first flexible layer maximum thickness on the flapping axis and a first flexible layer minimum thickness on the pitch axis, in the lead-lag plane the second flexible layer has a second varying thickness with a second flexible layer maximum thickness on the pitch axis and a second flexible layer minimum thickness on the flapping axis, and in the flapping motion plane and the pitch-angle plane the firs

Assignees

• Airbus Helicopters

Inventors

• Ferrant Matthieu
• Legrand Mathieu

Classifications

• F16F1/387

  comprising means for modifying the rigidity in particular directions {(spherical or conical sleeves F16F1/393)} · CPC title

• F01D5/147 Primary

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title

• B64C27/48

  Root attachment to rotor head · CPC title

• B64C27/35 Primary

  having elastomeric joints · CPC title

• F16F1/393

  with spherical or conical sleeves · CPC title