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: The invention aims to integrate the activation of the opening/closing phases around a single electric motor, including the treatment of the external window that may be present. An airplane electric door according to the invention has a locking system provided with means for locking a safety catch and a system (200) for coordinating door movements having a single actuating electric motor (2), a cylindrical support (501) having a vertical rotation axis (Z?Z), said support (501) being intended to be rotated by the motor (2), and a fixed guide (91).

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 aim of the invention is to optimise 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. For this purpose, 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 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: The aim of the invention is to optimise 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. For this purpose, 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 relates to an emergency opening device for an aircraft door provided with an opening mechanism (10, 11, 17), said device comprising (i) a mobile maneuvering member (21-23, 35) urged by elastic compression means (20) and provided with an end piece (35) connecting to the opening mechanism of the door, and an opposing resetting end segment; and (ii) a member (26) for retaining the resetting segment (23) of the maneuvering member, comprising jaws (26a, 26b) that can move between a closed position in which the resetting segment is locked, in a maneuvering member position in which the elastic means (20) are compressed, and an open position in which the resetting segment is released, thereby allowing the movement of the maneuvering member under the resultant force from the expansion of the elastic means (20).

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: 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: An aircraft (11) includes a system for observing part of the external environment of the aircraft. The environment observation system includes a camera, known as a panoramic camera (21, 22, 23), including a stationary camera associated with a lens that can focus a panoramic field of view simultaneously in both azimuth, about an axis of the panoramic camera, and elevation in a plane containing the axis. The panoramic camera is connected to at least one display screen disposed inside the aircraft (11) and is positioned such that part of the external environment of the aircraft (11) is located in its field of view.

Abstract: An active device (10) for viewing a scene, includes a light source (12) suitable for emitting electromagnetic radiation towards the scene to be viewed. The device (10) also includes a detector (14), and is configured to activate the detector so as to measure at least a portion of the electromagnetic radiation emitted by the light source and returned by the scene viewed. The electromagnetic radiation emitted by the light source (12) is infrared radiation at least partially included within a spectral band, referred to as the “viewing band”, the wavelengths of which are between 8 micrometers and 15 micrometers, and the detector (14) is designed to measure infrared radiation within the viewing band. Such an active viewing device (10) is particularly suited to viewing in foggy or rainy weather. A viewing method is also described.

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: A panel (1) includes a plurality of retainers (7) along its lateral sides, these being intended to engage, in the closure position of the panel, with corresponding retainers located on the frame structure of this panel. The panel includes at least one beam (3), a longitudinal end portion of which has a slot (15) emerging in the end face of the beam and located at a suitable position for mounting a retainer (6) directly on this beam. The retainer includes a retaining part (7) and a mounting part (8) formed by a base, the mounting part forming one body with the retaining part. The mounting part and the slot (15) are shaped such that the mounting part engages tightly in the slot and the mounting part is fastened to the beam by fastening members, particularly nuts and bolts, which are positioned approximately perpendicular to the principal direction of the beam.

Abstract: A locking system for an aircraft door includes: at least one locking member mounted on the door or doorframe, located along at least one of the edges of the door or doorframe, and adapted to move between a closed position, in which it bears against a corresponding bearing region of the doorframe or door, an “inward opening” intermediate position, which it occupies during the opening sequence of the door, in which it bears respectively against the doorframe or door to move the door toward the interior of the aircraft cabin, and an open position, in which it is completely disengaged from the corresponding bearing region, thus permitting the outward movement of the door relative to the doorframe without an upward or downward vertical movement; elements for actuating each locking member between the closed and open positions; and elements for locking each locking member in the closed position.

Abstract: In a process for the production of an aircraft stop by molding a composite material of resin and carbon fibers, a stack of pieces made of composite material, in which a metal piece will have been inserted, is draped by superposing layers of carbon fibers that are preimpregnated with resin, whereby the fibers are oriented so as to ensure maximum cohesion of the unit around the metal piece (4).

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.