Abstract: An emitter for emitting electromagnetic pulses includes a generator for generating an electromagnetic pulse, an optical fiber that transmits the eletromagnetic pulse, and an optical cavity. The optical cavity is placed in the path of the incident electromagnetic pulse transmitted by the optical fiber and has an input provided with a first partially reflecting mirror and an output provided with a second partially reflecting mirror. The first partially reflecting mirror is placed between first and second fiber lengths of the optical fiber and the second partially reflecting mirror is placed between the second and a third fiber length of the optical fiber. The length of the second fiber and a transmission/reflection ratio of the first and second mirrors are adjusted such that a train of electromagnetic pulses, having variable geometry characteristics, is emitted.

Abstract: The door (10) of an aircraft incorporates a housing (14) able to receive a slide, in a folded up state. The housing (14) is delimited between a cover (16) facing outwards from the door (10) and intermediate bulkhead (18). The cover (16) is jettisonable outside the aircraft or able to swivel by its lower edge on a threshold of the door, by the use of setting de-setting means. In one embodiment, the housing occupies the greater part of the door surface.

Abstract: Rotatable gripping device for the transport or machining of an arbitrarily shaped part. A rotatable gripping device designed to be fitted on a universal table for the transport or machining of a part comprises a ball joint support (16), a ball joint (18) and a suction cup (44) supported by the ball joint. The vacuum in the suction cup (44) is created by the duct (50) connected through a flexible tube (54) directly to the ball joint (18)—suction cup (44) assembly, on the outside of the support (16). The resulting total angular movement of the suction cup (44) is thus at least 90° (+ or −45 °).

Abstract: A method for determining a minimum control speed for an aircraft includes measuring, during at least one flight of the aircraft, the values of predefined parameters, recording these values in a memory, and determining, on the basis of these measurements and of at least one predefined certification value received from memory, a certification value (Cnfcertif) for the yaw moment (Cnf) created by the shutting down of one engine of the aircraft. The certification value (Cnfcertif) is used to determine the minimum control speed. On the basis of measured values of the sideslip (&bgr;), the lateral force (Cy), and a certification value (Cycertif), a certification value (&bgr;certif) is determined, and, on the basis of the measured value of the sideslip (&bgr;), the lateral force (Cy), the yaw moment (Cnf), and the certification values (Cycertif) and (&bgr;certif), the certification value (Cnfcertif) is determined.

Abstract: Device for pressure tapping, integrated into the fuselage of an aircraft, comprising an integrated plate (10), without discontinuity, with a pressure tapping part in the center (16). The plate (10) enters a supplementary opening (22) formed in a fuselage panel (20). The plate (10) and the panel part (20) surrounding the opening (22) are fixed on a supporting element (18) linked to the framework of the aircraft (34, 36). In the case where rivet, screw or bolt type fixations are used, they are placed at the edge of the plate (10). This arrangement facilitates assembly and improves the precision of the measurement, by suppressing any discontinuity in the measurement zone.

Abstract: According to the invention, the suspension pylon (3) comprises a fairing for reducing the local loss in lift (8) and its maximum-width section (7) is located at the front of the concave and set-back rear part (4R) of the pressure face (4) of the wing structure (1). The fairing for reducing the local loss in lift (8): is housed, at least over most of its height, in the concavity of the rear part (4R) of the pressure face (4) of the wing structure (1), and widens laterally toward the rear; and comprises a projecting rear part (12) that tapers toward the rear and ends in an aerodynamic trailing edge (16) the length of which is very long by comparison with the maximum width of the fairing.