Airbus Helicopters

Dassault Systemes

Eurocopter

Laurent Bianchi

Dawood Parker

John Enderby

Sebastien Bernier

Mark Bowes

Jacques Joseph Gaffiero

Nicolas Isidore

Bernard Michel

Damien Reveillon

Pierre Denis Voirin

Francois Marchand

Alain Charreyre

Rémy Cuenca

Mathieu Galan

Julien Jaume

Florian Gregoire

Sébastien Bernier

Pierre Voirin

François Marchand

A probe for non-intrusively detecting imperfections in a test object made from metallic, non-conductive, and/or composite materials. The probe may include a capacitive measuring apparatus that includes at least two coplanar electrodes, an adjustment device to adjust a spatial separation between the electrodes, and a separation device. The separation device may maintain a substantially constant distance between the at least two coplanar electrodes and the test object during test measurements.

Probe for non-intrusively detecting imperfections in a test object

A method for non-intrusively detecting imperfections in a test object made from metallic, non-conductive, and/or composite materials. The method uses a database with predetermined reference values and a probe that comprises a capacitive measuring apparatus with at least two coplanar electrodes. The method includes the operations of placing the at least two coplanar electrodes into a first position that is at a predetermined distance from the test object, performing a capacitive measurement to determine an effective dielectric constant, retrieving a reference value of the predetermined reference values from the database based on the test object and the predetermined distance, and detecting imperfections in the test object based on a comparison of the effective dielectric constant with the reference value.

Method for non-intrusively detecting imperfections in a test object

A blade of a rotor for a rotary-wing aircraft is equipped with an outer covering extending along the span of the blade. This outer covering is provided with an extrados skin and with an intrados skin defining a cavity. The blade also includes a structure that extends into the cavity and connects the blade to a hub of the rotor. The cavity is filled with a filling material that includes at least one partition parallel to a chord of the blade and at least two independent blocks of filling material filling the cavity, thereby allowing the reduction of the torsional rigidity along the span of the blade.

Blade with reduced torsional rigidity, and rotor equipped with such a blade

A computer-implemented method designs a three-dimensional modeled object. The method: provides, in a three-dimensional scene, said three-dimensional modeled object comprising a curve (C) defined by a set of vertices (V, V, V) and a set of edges (E, E) connecting said vertices. Next the method places a point (P) on the curve; stores an initial position of the point on the curve, relative to a first vertex (V); stores an initial position of the point within the three-dimensional scene; and modifies the curve by deleting the first vertex. The method further places the point onto the modified curve (C') at a modified position (P&#x2032;) situated at a minimal distance from the stored initial position of the point within the three-dimensional scene.

Computer implemented method for designing a three-dimensional modeled object comprising a curve and a point place on the curve

A blade () provided with a fitting () for fastening to a hub and with an airfoil element () having a spar () extending spanwise from an attachment zone () towards a distal zone (), said attachment zone () surrounding a centrifugal force transmission bushing () that is connected to said fitting () by a through pin (). The blade comprises a twisting force transmission member () provided with a first half-shell () and with a second half-shell () that together surround said attachment zone (), each half-shell () having a perforated first portion (&#x2033;) giving visual access to said bushing () when said airfoil element is removed from the fitting, and a second portion (&#x2033;) co-operating with a torsion box () surrounding said distal zone (), said transmission member () being secured to said fitting in rotation about a torsion axis (AX) of the blade ().

Blade and method of fabricating said blade

A blade () having a fitting () for fastening to a hub and an aerodynamic element () having a main spar () surrounding a bushing () for transmitting centrifugal forces and connected to said fitting (). The blade includes a transmission member () for transmitting torsional forces and co-operating with a torsion box. The fitting () includes an annular recess () defining a first recess () and a second recess () that are separated by a top separator () and a bottom separator () locally obstructing the annular recess (), the blade () including a first ring () and a second ring () reversibly arranged respectively in the first recess () and in the second recess (), each ring () being fastened to the top separator () and to the bottom separator (), a ring () including a fastener pin () passing through said bushing () and said fitting () in co-operation with the other ring ().

Rotor blade

A rotor blade () provided with an outer covering () and with at least one load take-up spar () associated with at least one pin-receiving bushing (). Each spar () is a compartmentalized spar comprising centrifugal force take-up means () incorporated within a twisting stress take-up casing (), said centrifugal force take-up means () comprising at least two boxes (), each having said pin-receiving bushing () of the spar () passing therethrough, each box () including a closed retention belt () extending in the spanwise direction of the blade, the retention belt () of one box () surrounding the retention belt () of another box (), each retention belt () being provided with unidirectional fibers () wound around said pin-receiving bushing (), said casing () being provided with inclined fibers () presenting an angle relative to said unidirectional fibers ().

Rotor blade and an aircraft

A rotor blade () with adaptive twisting, the blade being provided with an outer covering () extending along a pitch variation axis (AY) from a first end zone () to a second end zone (), the outer covering () defining an internal cavity (). The blade includes a strip () extending inside said cavity () along said pitch variation axis (AY), said strip () comprising a composite material that is anisotropic so as to be suitable for twisting under the effect of centrifugal forces (F) directed parallel to said pitch variation axis (AY) when the blade () is in rotation, said strip () being fastened to said outer covering () via first and second fastener means () in order to be capable of twisting said outer covering ().

Blade with adaptive twisting, and a rotor provided with such a blade

A rotorcraft blade is provided having at least one spar and an outer covering. At the root of the blade, the spar is subdivided into at least one bottom tape and at least one top tape. The blade further includes a hollow cuff whose outer wall includes the outer covering secured to the bottom and top tapes.

Growing community of inventors

Marseilles, France

Laurent Bianchi