Abstract: The present invention relates to a method of optimizing setting parameters for braiding a shielding sheath using spindles carrying coils of wires on a braiding machine, the sheath being braided onto a bundle of electrical conductors, and the invention also relates to such a bundle. According to the invention, the method consists in determining for each diameter in a series (s1) of consecutive electrical conductor bundle diameters, a single group (N) of spindles and a single group (M) of braiding wires so as to minimize the number of actions that need to be taken in order to adapt the machine to braiding a required diameter.

Abstract: The invention relates to a method of detecting obstacles on board an aircraft while in the vicinity (44) of a touchdown point (27, 42), the method comprising the following operations: selecting/determining a path (41) to be followed by the aircraft overflying the touchdown point; the aircraft overflying the touchdown point following the overflight path, and during the overflight recording signals/data delivered by an on-board rangefinder observing a portion of space extending below the aircraft; analyzing the rangefinder data to detect the presence of obstacles and to determine their positions in a terrestrial frame of reference, where appropriate to determine their dimensions; and recording the detected obstacle position data, and dimensions, if any, in a memory.

Abstract: 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.

Abstract: A method is provided for assisting the piloting of a rotorcraft in which vertical speed variation (DVZ) of the rotorcraft is determined as a function of a horizontal speed variation (DVH) of the aircraft and as a function of data representative of the power (W) absorbed for providing the rotorcraft with lift and forward advance, the ratio between variation speed vertical (DVZ) and the horizontal speed (VH) of the rotorcraft is calculated, and a piloting assistance symbol is presented on a display in a position (?) that is a function of the ratio.

Abstract: A twist element for a bearingless rotor is made mostly of composite fiber material and has a cross section with a substantially symmetric, flattened shape that has approximately the contour of a horizontal, central section of a double cone. In addition, a bearingless rotor having at least one such twist element, and a rotorcraft, particularly a helicopter, having at least one rotor with at least one such twist element are provided.

Abstract: A fiber-composite rotor blade, especially of a rotary-wing aircraft, with a predefined rotor blade profile that has a predefined outer contour of the profile, comprising a fiber-composite rotor blade structure having an upper and a lower cover skin and a profile core situated between them, and at least one highly extensible cable integrated into the fiber-composite rotor blade structure in the direction of the span of the rotor blade, whereby said cable can be connected to a functional device that can be attached onto or into the fiber-composite rotor blade structure. The cable is a highly extensible power and/or signal transmission cable, comprising at least one cable strand with at least one first cable core made of an electrically insulating, elastic plastic material, and at least one first cable wire that is wound around the first cable core at a predefined pitch angle, like a spiral and free of crossovers.

Abstract: The present invention relates to a method and to a device (D) enabling a health check to be performed on at least a first turbine engine (M1) of a rotorcraft, the rotorcraft being provided with first and second turbine engines (M1 and M2) controlled respectively by first and second control means (MC1 and MC2). The device is remarkable in that it comprises check means (C) provided with main means (C1), the main means (C1) controlling the first and second control means (MC1 and MC2) so that the surveillance parameters of the first and second turbine engines (M1 and M2) respectively reach the real first and second final values (V1f and V2f) as determined in accordance with the method of the invention.

Abstract: The present invention relates to a method of analyzing variations in an indicator (i) of the behavior of a mechanism, the method comprising the following operations: (OP1, OP2) extracting noise (w) and any discontinuities (b, s) from the indicator (i) in order to obtain a trend (c); (OP8) comparing variations in the trend (c) with one or more reference values; and (OP10) indicating a fault of the mechanism as a function of the result of the comparison(s) (OP8).

Abstract: The invention relates to a rotorcraft cockpit having a left seat and a right seat placed side-by-side, a console extending between the seats, two side sticks, one situated to the right of the right seat and the other situated to the left of the left seat, enabling the pilot to control roll and pitch; a flight control system comprising sensors associated with the side sticks and a computer connected to the sensors serves to convert the orders applied by the pilot to the side sticks into signals for controlling actuators in order to vary roll and pitch; a piloting relationship integrated in the computer stabilizes the response of the rotorcraft in roll and in pitch when a side stick is actuated, and maintains the attitudes in roll and pitch at reference values when neither side stick is actuated.

Abstract: A rotor, comprising at least one rotor blade connectable to a rotor head, which rotor blade possesses a blade neck having a virtual flapping hinge in the form of a flexurally soft, flexurally elastic blade-neck portion, there being provided, in a blade-connector region of the blade neck, two auxiliary flapping hinges, spaced apart from one another in the radial longitudinal direction of the rotor blade with reference to a rotor radius, between which the virtual flapping hinge is substantially disposed and between which the blade neck is deformable in flexurally elastic and curved fashion in the context of a flapwise motion. A rotorcraft, in particular a helicopter, in particular a tiltrotor helicopter, having at least one such rotor.

Abstract: A bundle includes wire segments forming a branch fitted with an angled coupling including: a base having the ends of the wire segments fastened thereto; an angled rigid casing surrounding the wire segments and having a first end providing for bearing against the base; and a member for fastening the casing to the base with a mutual variable orientation; the branch is protected by a shielding sheath secured to a second end of the casing; the bundle includes an abutment member secured to the portion of the wire segments extending inside the angled casing and co-operating with the angled casing to prevent the portion of the wire segments from leaving the casing; the portion of the wire segments is twisted in such a manner that the mutual orientation between the base and the casing can be modified without introducing harmful mechanical stresses in these wire segment portions.

Abstract: A hingeless rotor, in particular for a rotorcraft, comprising: a rotor head, a rotor mast having a rotor axis, a torque-transmission element nonrotatably joined to the rotor mast, at least one rotor blade, and a rotor-head-side rotor-blade connector having a centrifugal-force-discharging blade connector loop, which loop encircles the rotor axis or the rotor mast and is nonrotatably joined to the torque-transmission element.

Abstract: A fairing C is arranged on a rotor 9 of a rotorcraft having a cap 5 secured to the end 10 of the head of the rotor 9. The fairing C further comprises at least one air deflector member D provided with a ring 6 and spacers 4, the spacers 4 enabling the ring 6 to be secured to the cap 5.

Abstract: The invention relates to tooling for preparing a large-section harness comprising at least one cable. The tooling includes an output module (19) for receiving the terminal end of the cable. The output module (19) comprises three tools mounted on an output body (20) that is movable on a tray (1) so that each of the tools can be presented in alternation in register with the terminal end of the cable, the tools comprising a first tool (22) for marking cutting and stripping lengths for the cable, a second tool (28) for marking the position and the orientation of the terminal connection member (29), and a third tool (30) for checking that the terminal connection member (29) is in the proper position and orientation after it has been crimped to the terminal end of the cable.

Abstract: Active connection element for connecting at least two structural components with a first end with a first connection area assigned to the first structural component and a second end with a second connection area assigned to the second structural component, a load-diminishing intermediate section through which intermediate section the flux of force between the first and second connection areas extends when the connection element is loaded, in which at least one controllable extension actuator having at least a piezo stack is arranged parallel to the intermediate section. When operated, the piezo stack extends the connection element at least in the area of the intermediate section in a controlled manner in order to actively suppress or insulate vibrations between the structural components. A prestressing device having a prestressing element exercises a compressive prestressing onto the piezo stack.

Abstract: A hydraulic system includes a reservoir for a hydraulic fluid, a pump, a high-pressure line network, a low-pressure line network and operating cylinders each of which can be connected to the high-pressure line network or to the low-pressure line network via control units, each operating cylinder is associated with a local compensation volume element.

Abstract: Device assisting with interception by an aircraft of a flight path segment located in a horizontal plane and a system of assistance with interception and follow-up of such a segment. The device includes means of determining a ground speed vector and means of displaying to present, on a screen, a means of indication (10) of the ground speed corresponding to a first rectilinear section (11) in the horizontal plane, connected to a symbol (7) whose angular orientation corresponds to the direction of said ground speed vector and whose length is variable, a means of interception approach indication (12) corresponding to a second rectilinear section (13) in the horizontal plane of variable width and provided for as an extension of first rectilinear section (11) and a means of indication (14) of the interception turn corresponding to at least one circular arc (15) in the horizontal plane, provided to extend second rectilinear section (13).

Abstract: Device assisting with interception by an aircraft of a flight path segment located in a horizontal plane and a system of assistance with interception and follow-up of such a segment. The device includes means of determining a ground speed vector and means of displaying to present, on a screen, a means of indication (10) of the ground speed corresponding to a first rectilinear section (10) in the horizontal plane, connected to a symbol (7) whose angular orientation corresponds to the direction of said ground speed vector and whose length is variable, a means of interception approach indication (12) corresponding to a second recipient section (3) in the horizontal plane of variable width and provided for as an extension of first rectilinear section (11) and a means of indication (14) of the interception turn corresponding to at least one circle arc (15) in the horizontal plane, provided to extend second rectilinear section (13).

Abstract: A hydraulic linear actuating drive includes a cylinder, a movable servo piston that can be pressure-loaded and that runs inside the cylinder, at least one piston rod attached to the servo piston, and at least one piston gasket having at least two sealing elements at a distance from each other. An intermediate sealing space is defined between the at least two sealing elements, an inner wall of the cylinder and an outer edge of the servo piston. The hydraulic linear actuating drive has at least one leakage channel that can move together with the servo piston. A first end of the channel opens into the intermediate sealing space and into a leakage fluid inlet opening located there, while the other, second end of the channel opens into a leakage fluid outlet opening arranged outside of the cylinder.

Abstract: The invention relates to a rotor comprising a rotor shaft, a rotation torque transmission element which is mounted thereon and at least one element of the plate-shaped rotor head whose axis of rotation extends therethrough. Said rotor is provided with two groups of different arms. The first group consists of the flexible rotor blade connection arms which remove centrifugal forces and to which a respective blade can be fixed. The second group consists of flexible connection rotor arms which are devoid of centrifugal force to which the elements of the plate-shape rotor head can be rotationally fixed by means of the rotation torque transmission element.