Sandwich-structure flat actuator and application to structural torsion

• US 7,726,603 B2
• Filed: 11/16/2006
• Issued: 06/01/2010
• Est. Priority Date: 11/22/2005
• Status: Active Grant

• Current Assignee: Office National D'Etudes et de Recherches Aerospatiales
• Original Assignee: Office National D'Etudes et de Recherches Aerospatiales
• Inventors: Buchaniek, Leon, Mercier Des Rochettes, Hugues, Joly, Didier
• Primary Examiner(s): Mansen; Michael R
• Assistant Examiner(s): O'Hara; Brian M
• Application Number:
  US11/600,223
• Publication Number:
  US 20070205332A1
• Time in Patent Office: 1,293 Days
• Field of Search: 244/78.1, 244/87, 244/99.8, 244/200, 310/328, 310/333
• US Class Current: 244/99.8
• CPC Class Codes: B64C 2027/7283 of the piezoelectric type
• CPC Class Codes: B64C 27/001 Vibration damping devices
• CPC Class Codes: H10N 30/208 using shear or torsion displacement, e.g. d15 type devices
• CPC Class Codes: Y02T 50/30 Wing lift efficiency

Abstract

The present invention relates to a sandwich-structure flat active actuator that is symmetrical relative to the mid-plane comprising at least one piezoelectric flat layer having an active direction superpose and fixedly attached to at least one passive flat layer of fabric with rigid warp and weft oriented in two directions forming a mesh; the two directions of each layer of fabric are the same. The active direction of each piezoelectric layer is oriented along one and the same diagonal of the mesh of the layers of fabric. The invention is also aimed at a device consisting of two actuators mounted head-to-tail. The invention applies to the active torsion of structures such as, for example, a helicopter blade.

Claims

1. A flat, sandwich-structure actuator having a length in a direction X, a width in a direction Y and a thickness in a direction Z, said actuator comprising:

at least three flat layers superposed in a sandwich-structure symmetrical relative to the mid plane of the actuator promoting a flat shearing deformation of said sandwich-structure, comprising;

at least one layer of a fabric whose warp and weft comprise rigid fibers respectively disposed parallel to said directions X and Y, forming a mesh of juxtaposed parallelograms, each layer of fabric having its warp and weft oriented in the same directions X, and Y, and

at least one piezoelectric active flat layer capable of lengthening or retracting in an active direction, the active direction of each piezoelectric flat layer being oriented along one and the same diagonal of said parallelograms of said mesh,

the faces of said piezoelectric active flat layer in contact with a layer of fabric being fixedly attached to said layer of fabric on whole the surface of said piezoelectric active flat layer, and

first and second attachment zones designed for transmission of said flat shearing deformation of said sandwich-structure, said first and second attachment zones being of elongated shape and parallel to one of said directions X and Y and being respectively disposed on the opposite outer faces of said sandwich structure along opposite ends of this latter.

2. The actuator as claimed in claim 1, wherein the active layer is situated between two layers of fabric.

3. The actuator as claimed in claim 1, wherein the sandwich structure comprises one layer of fabric situated between two active layers.

4. A flat actuator device, wherein two actuators are provided as claimed in claim 1, mounted head-to-head, two facing attachment zones of the actuators being fixedly attached and two active directions, respectively corresponding to the two actuators, not being parallel, two other facing actuator attachment zones, left free, have a displacement in a first direction of a plane whose amplitude is equal to a sum of amplitudes of the two actuators.

5. The use of the device as claimed in claim 4 in combination with the structure of an open airfoil, wherein the two facing attachment zones left free are fixedly attached respectively to a pressure surface and a suction surface, the device thus closing this structure in the vicinity of a trailing edge of the airfoil.

6. The use as claimed in claim 5, wherein the two fixedly attached facing attachment zones and the trailing edge are situated, along a chord, on either side of the two facing attachment zones left free.

7. The use as claimed in claim 6, wherein the two fixedly attached facing attachment zones and the trailing edge are situated, along the chord, on a same side of the two facing attachment zones left free, the two fixedly attached facing attachment zones forming the trailing edge of the airfoil.