Abstract: The invention concerns an aircraft door having a lever (3) for emergency opening from outside, disposed in a lever window. The lever (3) for emergency opening from outside includes: a main arm (7) having a first aerodynamic surface (9); a profiled cowling (8) with a second aerodynamic surface (10); a driving stop (18) capable of rotating the profiled cowling (8) from its concealing position to its separated position when the main arm (7) passes from its retracted position to its deployed position.

Abstract: The invention proposes a simple system, with small space requirement, without hinge arms or sealing skirt, while providing secure and effective opening. To achieve this, the invention provides a door opening by a lateral guidance defining an integrated doubling-back kinematics, towards the interior then the exterior of the fuselage. An opening system of an emergency door (1) is positioned in an aircraft fuselage (2), the door and the fuselage comprising respective frameworks (11, 21) extending opposite each other.

Abstract: The aim of the invention is to provide an architecture of a laser imager having high spatial resolution, compatible with an application installed on board a vehicle, in particular on board an aircraft. For this purpose, the invention proposes the generation of a piece of wide-field laser ranging information by a suitable remote optical system. An example of a piece of equipment (1) according to the invention installed on board an aircraft moving in an environment that is likely to contain obstacles (4), in particular an aircraft on the ground, includes a laser range finder (11) coupled to an optical fibre (F1) emitting laser pulses (I), which is itself coupled to an optical system providing an interface with the environment (12) via an optical cross-connect (13) coupled to a covered optical fibre bundle, in the form of laser illuminations (Fi).

Abstract: An aircraft emergency exit door (10) with opening mechanisms integrated by a grouping of the mechanisms into a door beam (3) located on a given side of a window (16) of standard dimensions. In the beam, an inner handle (1) is mounted on a main shaft (102) connected with a locking shaft (8A) on which there is mounted, against return springs (83), a door blocking/locking mechanism (8) comprising a lock (81). A mechanism for conditionally opening the door (100) includes a vent flap (110), a pivot connection (12) for coupling the flap (110) to the inner handle (1), and a blocking shaft (120) that has, at each end, a pressure lever (121) equipped with supports for blocking (122) and unblocking (123) the flap (110). Return springs (32) mounted against the conditional opening mechanism (100) are calibrated to allow the opening of the flap (110) by exerting reduced pressure in residual pressure variation conditions, and to prevent it from opening in overpressure conditions.

Abstract: The monitoring and security of at least one enclosure, allowing a constant and complete view of the enclosure, and a modulated assessment of the state of security of same. The invention proposes to transmit images of the enclosure wirelessly to a mobile medium for helping the flight crew assess the situation and the measures to take in case of a sensitive security situation.

Abstract: The invention aims to make aircraft doors easier to open by preventing ice formation or, at the very least, favoring rapid breaking of the ice on the door edges connected to the skin of the fuselage. To that end, it is provided to supply energy along the door when specific conditions are met. According to one embodiment, an anti-icing/de-icing system for an aircraft door (1) according to the invention includes an excitation energy source and devices (81 to 83) for dissipating such energy extending parallel to a side surface (11) of the aircraft door (1), along a sealing gasket (4) support (5) secured to the door (1) across from a fuselage (2) side surface (21) framing (20) the door (1). The sealing gasket (4) of the door (1) is compressed against bearing (6) from a side surface (25) of the fuselage (2) when the door (1) is closed.

Abstract: An aircraft electric door including a locking system for actuating a safety catch for locking the door, a system for moving the door between open and closed positions, and a single electric motor for actuating both the locking system and the system for moving the door.

Abstract: The objective of the invention is to replace the rope bar of the door evacuation slide with individual connections. According to a preferred embodiment, the mechanism for arming/disarming an aircraft door evacuation slide (1, 15, 16) includes two releasable connectors (21) disposed to either side of the base of the door and each includes two half connectors (21s, 21i), a so-called upper half connector (21s, 41, 4a, 42) rigidly connected to the door (1) and having an attachment device (33) for attachment to the slide, and a so-called lower half connector (21i) fixed to the cabin floor (6). Each upper half connector (21s) includes a movable inner part controlled by a ring (43) and housed in the corresponding lower half-connector (21i). The mechanism can also include an electric motor coupled to two rods (31), each rod (31) being capable of rotating the control ring (43) of each upper half connector (21s) between two angular positions: an armed position and a disarmed position.

Abstract: An aircraft (11) includes an enclosure and a system for surveilling areas of interest inside the enclosure. The enclosure includes a transverse aisle (13) and a longitudinal aisle (15) that intersect at an intersection zone (19), a first access door (14) being located at one end of the transverse aisle (13) and a second access door (22) being located at one end of the longitudinal aisle. In addition, the surveillance system includes a panoramic camera (17) with a panoramic field of view, the camera being positioned at the intersection zone (19) such that an area of interest associated with the first access door (14) and an area of interest associated with the second access door is located within the field of view of the panoramic camera.

Abstract: The invention relates to a guard for the upper part of a door (2) of an aircraft, consisting of: a composite comprising a composite and/or stainless steel strip (14) which forms the core of the guard (1) and which renders same flexible and resistant, a silicon which is optionally reinforced with fibres and a polyester.

Abstract: The present invention provides a device for controlling the movement of a vehicle closure element, the device comprising, interposed between a vehicle structure and a closure element, firstly a driver element that can be activated on command, constituted by a pyrotechnic actuator, and secondly mechanical connection means suitable for allowing a driving connection between the pyrotechnic actuator and the closure element when the pyrotechnic actuator is activated, while also allowing the closure element to move freely relative to the pyrotechnic actuator when the closure element is moved over a stroke greater than that enabling said driving connection.

Abstract: This device comprises at least one sensor of a CCD camera of very short spectral band lying between 0.4 &mgr;m and 1.1 &mgr;m, fitted with an infrared filter eliminating the spectral band lying between around 0.4 &mgr;m and 0.8 &mgr;m, this sensor being associated with a computer catering in particular for image processing, at least one display screen and a control board. It is thus possible, with the aid of a single type of sensor, to detect hot spots, flames, smoke and the shifting of objects, and to provide a visualization of the inside of the enclosure.