Abstract: Preprocessor for the detection of point sources in an infrared (IR) "scenario" or field, essentially consisting of an input interface; a transversal filter; an adaptable threshold device, consisting in turn of a two-port internal memory and of an arithmetic processing unit; a resource assembly and an output interface. The system can be used in surveillance in the IR band, more particularly, in the field of detection of signal emission on ships, planes, helicopters, transportation means, armored cars, airports and anywhere it is necessary to detect artificial or natural heat sources from as far away as possible. In comparison with the prior art, the preprocessor differs from the point of view of the filtering system, adjusting the filter itself to the real form of the IR signal which is punctiform and depends on the electro-optic characteristics of the sensor.

Abstract: A damper, especially for a structural element of an aircraft and especially a propeller driven aircraft in which the propeller generates vibration in the structural element with a fundamental frequency and a frequency which is a harmonic of the fundamental frequency. The damper has a cantilever bar which can be flexed and a cup-shaped pendulum element affixed to the bar and tunable so that the mass of the pendulum defines a first eigenfrequency of vibration of the damper corresponding to the fundamental and the moment of inertia about an axis perpendicular to the axis of the bar is tuned to a second eigenfrequency corresponding to the fundamental.

Abstract: A manufacturing process for high performance single mode channel optical guides of the LiNbO.sub.3 using five successive steps: photo-etched optical path definition, deposition of the dielectric layer, lift-off definition of the channels, proton exchange and thermal cycling. The method can be used to produce multi-function devices to be interfaced with optical fibers to obtain sensors, telecommunications devices and devices for processing wide-band microwave signals the proton exchange is affected in benzoic acid diluted with lithium benzoate and eliminates the time instability of the electro-optical structure due to the presence of an insulating layer above the optical guide.

Abstract: Detector of suspended cables specially suited for avionic applications formed mainly by a scanning system (S) provided with a noise generator (1) and scan concentrator (3); by a Lidar system (L) and an extractor system (E). The latter is composed of a background filter (7) and a chain extractor (8). This detector, if included in the on board instrumentation of light aircrafts and helicopters, is in condition of supplying the pilot with a warning signal if suspended cables are detected in the flight path during low altitude flights. The instrument gives the cable position and allows the selection of the right corrective move.The invention finds its most convenient application in the flight safety field while that of the avionic optical radars is the specific technical field of this device.

Abstract: A cryogenic gyroscope for detecting the angular velocity of a rigid system without reference to an external inertial system comprises a closed rigid casing made of a sueprconducting material and kept below its critical superconducting temperature, for example, by immersion in a bath of liquid helium. A rotation-detector device is situated within the superconductor casing. This device, which is rigidly supported by the wall of the casing, includes at least one component of ferromagnetic material, constituted by a plurality of ferromagnetic strips intercalated with layers of electrically-insulating material.

Abstract: In a jet-propelled aircraft of the type in which the propulsion jets are directed onto a wing so as to achieve an ejector effect, two vertical tail-fin surfaces are provided and extend downwardly beneath the center of gravity of the aircraft to return the aircraft to a correct attitude when it tends to move sideways relative to the direction of flight.

Abstract: A composite structure is prepared in a mold using an elastic diaphragm which allows the application of a uniformly distributed pressure during a curing cycle. The elastic diaphragm seals a resin impregnated lay-up throughout the curing cycle during which the lay-up is heated and compressed, and ensures a constant resin-to-reinforcement ratio by preventing the escape of resin from the lay-up as the viscosity of the resin is lowered during the initial stages of the curing cycle. In instances where entrapped air or volatile removal from the lay-up is necessary, a separate step including the application of a vacuum and/or heat to the lay-up can be performed prior to the final curing cycle.

Abstract: An array of mirrors of the SSM ('Second Surface Mirror") type is fixed to the outer surface of a panel of a spacecraft, for example an artificial satellite, for the purpose of heat control. The fixing of the mirrors to the panel is achieved by gluing in a series of operations which ensure the correct positioning of the mirrors, the effectiveness of the adhesion, and electrical conductivity through the array of mirrors. In the application of the mirrors, use is made of a fixed structure for supporting the panel, a transferring tool on which the mirrors are temporarily retained in contact with separate support areas by a vacuum, and a loading tool arranged to receive the mirrors from the transferring tool and apply them to the panel.

Abstract: A docking system for space modules includes a docking device having respective male and female coupling members carried by the two space modules. The coupling members are arranged to allow, after they have been brought into their coupled condition, relative rotation of the two modules about the axis of the docking device. The system further includes a plurality of connecting devices arranged to lock the two space modules in a precise relative position after the male and female members of the docking device have been brought into their coupled condition. Each of the said connecting devices comprises a coupling seat located in one of the two modules and a coupling shank carried by the other module and axially movable between a withdrawn inoperative position and an extended coupling position. This coupling shank has a head which is expandible within the said coupling seat to effect the connection between the two modules.

Abstract: An expandable spacecraft is provided which includes at least one main generally cylindrical body member. This body member comprises a generally waffle-type structure which includes a plurality of flanges extending generally radially from the body member. An auxiliary housing is provided which is adapted to increase the volume of the body member. The auxiliary housing is connected to the main body member and is slidably and telescopically received therein. The main body portion and auxiliary housing member can be provided in a compact state with a predetermined volume or can be expanded by extending the housing outwardly from the main body member to increase the volume of the assembly to a desired degree.

Abstract: In an extensible arm having a reticular lattice structure with a polygonal cross-section, particularly for space modules or vehicles, each longitudinal side of the lattice structure includes first and second kinematic pantograph chains each constituted by a plurality of rods articulated together so as to define a series of aligned X-shaped elements. The rods of the second kinematic chain are shorter than the rods of the first kinematic chain, and the articulations between the X-shaped elements of the second kinematic chain located on one side of the latter coincide with the articulations between the X-shaped elements of the first kinematic chain located on the same side.

Abstract: A jet propelled aircraft of the kind in which propulsion jets are directed over the top surface of the wing so as to cause additional lift as a result of the supercirculation induced on the wing and the deflection of the jets downwards, due to the Coanda effect, immediately downstream of the wing is provided with two longitudinal surfaces projecting from said top surface so as to form a single surface ejector system. The wing of the aircraft has a fixed front part which occupies a minor portion of the wing chord, and a movable rear portion which is articulated to the fixed portion about a substantially transverse axis and can be inclined downwards relative to the fixed part. The portion of the wing between the two longitudinal surfaces may be provided on its trailing edge with a movable attitude control surface of the aircraft.

Abstract: A drill bit for drilling holes in laminates consisting of a matrix of plastic material incorporating graphite or glass fibers as used particularly in the aviation industry. The bit comprises cutting elements each of which presents a first straight sharp edge of very low conicity and positive rake and a second sharp edge having a convex curvature (FIG. 1).

Abstract: Measuring apparatus for providing a reading representing a magnetic field component or the electric field component of incident radio frequency electromagnetic radiation comprises a set of magnetic field sensors and a set of electric field sensors interchangeably connectable to a measuring device which has an indicator instrument and an optical output to which can be connected a repeater device by means of an optical fibre cable which thus does not exert a perturbing influence on the field being measured. The sensors are omnidirectional balanced devices in which the detector elements are constituted by suitably shaped metallic film deposits on dielectric substrates, and can be interchanged by a simple plug-in connection which also holds the sensor physically in position on the measuring device.

Abstract: A pair of like electrical/electronic equipment racks are uniquely arranged in an avionics bay located in the belly (lower lobe) of a wide-bodied aircraft, with the fronts of the racks facing a central access aisle that extends lengthwise of the fuselage between the racks, and with the rear of each rackfacing one of two outboard aisles that extend parallel to the central aisle along the sides of the bay. At the forward end of the bay, a transversely extending passageway interconnects the central aisle with the two outboard aisles and enables the ground crew to access both the front and rear of each rack by entering the bay through a ground access hatch disposed in the lower most central portion of the fuselage and opening into the bay at the central aisle. Emergency in-flight access to the bay from the upper lobe, by in-flight personnel, is also available through a hatch disposed in a deck lying above and slightly aft of the avionics bay.

Abstract: Core noise, a low frequency noise component believed to be partly caused by the combustion processes within the engine, and turbine noise, a higher frequency noise component caused by the interaction of high velocity gases with the engine's turbine, are attenuated by noise absorbing structures that are disposed within the engine's nozzle and that in part define the physical geometry of the nozzle duct. The nozzle is formed of an outer sleeve and an inner generally bulb-shaped plug which are coaxially arranged to define an annular nozzle duct that channels the flow of gases rearwardly from the outlet of the engine's turbine. The plug has a hollow interior that is partitioned into a plurality of cavities that communicate with the nozzle duct via perforations provided in an outer wall of the plug.

Abstract: An escape slide container is mounted for selective, upward movement with a track-mounted, overhead sliding door in an aircraft fuselage. Slide deployment mechanism for releasing the container from the door and for attaching it to the floor of the aircraft allows the door to move upwardly independently of the container, leaving the container attached to the floor. An over-center linkage supports the container above the floor while upward movement of the door trips the over-center linkage to propel the container outwardly through the door opening to deploy the escape slide under the urging of gravity. Apparatus for arming and disarming the slide for deployment operates in conjunction with door opening and closing apparatus that simultaneously effects movement of a door carrier to unplug the aircraft door from the opening in the fuselage and initiates upward traverse of the door along a plurality of tracks from which the door is supported at three points.

Abstract: An escape slide container is mounted for selective, upward movement with a track-mounted, overhead sliding door in an aircraft fuselage. Slide deployment mechanism for releasing the container from the door and for attaching it to the floor of the aircraft allows the door to move upwardly independently of the container, leaving the container attached to the floor. An over-center linkage supports the container above the floor while upward movement of the door trips the over-center linkage to propel the container outwardly through the door opening to deploy the escape slide under the urging of gravity.

Abstract: A pair of like electrical/electronic equipment racks are uniquely arranged in an avionics bay located in the belly (lower lobe) of a wide-bodied aircraft, with the fronts of the racks facing a central access aisle that extends lengthwise of the fuselage between the racks, and with the rear of each rack facing one of two outboard aisles that extend parallel to the central aisle along the sides of the bay. At the forward end of the bay, a transversely extending passageway interconnects the central aisle with the two outboard aisles and enables the ground crew to access both the front and rear of each rack by entering the bay through a ground access hatch disposed in the lower most central portion of the fuselage and opening into the bay at the central aisle. Emergency in-flight access to the bay from the upper lobe, by in-flight personnel, is also available through a hatch disposed in a deck lying above and slightly aft of the avionics bay.

Abstract: Combination primary and fan air thrust reversal control systems for long duct fan jet engines are disclosed. In one form, the system spoils and expands primary air and, then, allows the spoiled, expanded air to exit from the fan air duct exhaust nozzle while directing fan air in a thrust reversal direction out cascade vanes circumferentially located in the aft portion of the engine nacelle. In other forms, the system directs unequal pressure fan air and primary air through separate thrust reversal ducting and out cascade vanes circumferentially located in the engine nacelle. In equal pressure fan air and primary air systems, the air may be mixed in ducting prior to being emitted from common cascade vanes, or may be maintained separate prior to emission. In still other forms, the primary air is pre-exhausted through separate nozzles located in the primary duct wall, and a portion is then exhausted through the nacelle cascade vanes.