Abstract: Tool assembly for riveting parts, comprising: a first and a second frame (2, 5) capable of being mounted on a shaped structure "C" or on separate robot arms (60, 61); a pair of sheet-holding devices (3, 6) each mounted on one of the frames and at least one of each is provided with a device (11) for displacing it relative to the corresponding chassis with a force corresponding to the clamping provided for holding the parts to be riveted during drilling; at least one drill (20, 21) mounted on a frame, a device (41) for placing a rivet (40) in a hole drilled by the drill, this device being carried by a frame; a percussion riveting hammer (51) carried by a frame and an associated counter-piece (54) carried by the other frame, integral with a reaction dolly (52). The elements carried by each frame are all capable of being displaced between an active position and a rest position.

Abstract: The method according to the invention consists, in a first step, in studying the acoustic response of a piece P by recording, with acoustic sensors (1, 2, 3, 4), signals emitted by a calibrated acoustic emitter (5), from a succession of predetermined mark points defining a grid on the surface of the piece, while the latter is unstressed. In a second step, the piece is stressed and the acoustic signals coming from acoustic events created by this stressing of the piece are recorded. Processing of the propagation times and of the amplitudes of the acoustic waves thus recorded during these two steps allows identification of the position and size of structural defects in the material constituting the piece P.

Abstract: A surface impedance measurement device comprises a transmitting antenna producing a magnetic field in the area surrounding a material to be tested and a receiving antenna receiving the magnetic field. An electric voltage wobbled in frequency is applied to the transmitting antenna, and a circuit measures the voltage at the terminals of the second antenna. For the antennae to be applied on the same side of the material to be tested and of which the surface impedance is to be measured, the antennae are superposed by the intermediary of a dielectric wedge in a compact probe. The impedance measurements are then independent of the dimensions and geometry of the material.

Abstract: Device for maintaining a load attached to an aircraft immobilized in relation to the said aircraft, comprising bearing members carried by the aircraft and movable relative to the aircraft, means provided for moving the bearing members into contact with the said load, and a jack separate from the said means and having a movable assembly which is capable of exerting a force on the bearing members in order to clamp them firmly against the load.

Abstract: An ejector seat device for aircraft includes a support structure which is adapted to be mounted in an aircraft and which can be ejected in an emergency, a seat connected to the support structure, a harness system which is capable of keeping a person in the seat and which comprises a recall device to immobilize the person in a suitable position at the moment of ejection, at least one pyrotechnical catapult capable of ejecting the support structure and the seat, together with a person sitting on the seat, out of the aircraft, a device for at least weakening the aircraft canopy by shock wave, a control handle, and an initiator connector to the handle for transforming a pull on the handle into a pyrotechnical signal. The pyrotechnical signal from the handle is transmitted in the form of a shock wave to the harness recall device and to the catapult.

Abstract: A removable box is provided for electrical or electronic equipment. A plug connection has elements respectively provided on the box and within an associated housing. Guide pieces are located on the box and housing which engage with one another to guide a sliding motion of the box generated by rotation of an endless screw within a housing rack. Rotation of the screw is blocked when the plug elements are engaged and rotation allowed when the elements are disengaged via a locking mechanism.

Abstract: As a method and device for representing the horizon on board an aircraft, there is displayed on the cathode tube of a collimator an image comprising a circle of small size inside which there are, on the one hand, a horizon line inclined to the horizontal by an angle equal to but opposite the rolling angle of the aircraft, the horizon line being remote from the center of the circle by a distance which is a function of the pitching angle in the upward direction when the aircraft is diving and in the downward direction when the aircraft is pulling the nose up, and which delimits to zones of different brightness and, on the other hand, a point representing a pole situated on the median line of the horizon line at a distance from the latter corresponding to a pitching angle of 90.degree.. A "head up" type control system is essentially provided.

Abstract: A prosthetic cardiac valve with a plurality of flaps supported by a base through a rotational guide and retaining mechanism between an open position and a closed position.The valve is characterized in that:the guide and retaining mechaism define a virtual axis of rotation disposed at a distance from the axis of the valve which is greater than 75% of the radius of the base measured along the axis of symmetry of a flap,each virtual axis, situated outside the corresponding flap, is offcentered with respect to the center of gravity of the flap, andin the open position, the corners of each flap come to bear on the internal wall of the base in zones which are situated at a distance from the corresponding virtual axis of rotation which is greater than 25% of the radius of the base.

Abstract: Device for ejecting a load slung under an aircraft, designed to impart to this load, at the moment of its release, kinematic values controlled as a function of the instantaneous flight parameters of the aircraft at this moment.A plurality of separate modules (1, 2A, 2B, 4, 10) makes it possible, on the one hand, to execute a longitudinal translational movement (d) of the load (3) to detach it from the members (5) attaching it to the aircraft and, on the other hand, to carry out an accurate adjustment of the angular ejection speed. One of the modules is an energy source (1), such as a bottle of compressed nitrogen. Two other modules are respectively a front fluid jack (2A) and a rear fluid jack (2B), both with a retractable telescopic piston which, when the pressurized gas is supplied to it by the source (1), exerts an ejection force on the load (3).The invention is used for the release of loads carried by aircraft.

Abstract: A panel structure useful in constructing cowlings for aircraft engines includes a honeycomb core composed of glass fibers impregnated with phenol resin, an inner covering attached to an inner surface of the honeycomb core which is made of carbon fibers impregnated with phenol resin and which is porous, and an outer covering attached to an outer surface of the honeycomb core which is made of carbon fibers impregnated with phenol resin and which is leaktight. The outer covering is formed by heating the carbon fibers and phenol resin to cause polymerization while subjecting the outer covering first to vacuum and then to high pressure.

Abstract: This invention concerns an antenna switchable between the VHF and UHF frequency bands. This antenna incorporates a capacitive element, disposed at a specified distance from a reflecting surface mounted on the body of the vehicle. For VHF, tuning is obtained by a fixed self-inductance in parallel and a variable self-inductance in series with the capacitive element. The latter comprises various sections which can be short-circuited by switches. For UHF, the variable self-inductance is totally short-circuited and the fixed self-inductance is disconnected by a switch; then, plates form, with the reflecting surface and the capacitative element, a "manchette" antenna. This switchable antenna can in particular be mounted on an airplane.

Abstract: An air arrester device that can be connected into the fuel line of an airplane to interrupt the passage of a bubble of air moving through the fuel line, the device including a vertically oriented elongated container which includes an inlet duct connected to its lower end and an outlet duct which extends downwardly through its upper end and into the interior of the container, the outlet duct including at least one intake port located at about half way along the length of the container to enable fuel in the container to flow into the outlet duct and upwardly out of the container. Under negative G conditions an air bubble which has passed into the container via the inlet duct will be located below the intake ports while under normal conditions it will be located above the intake ports.

Abstract: The invention relates to a method and to a structural element for protecting an aircraft against the building-up, when flying, of electrostatic charges on the external metallic surface of the aircraft normally coated with a finishing dielectric paint.The structural element of the aircraft is subjected to a treatment consisting in applying on the external metallic surface of the aircraft, prior to the depositing of the finishing paint, a resistive electrostatic protection layer having a surface resistivity of between 1 and 100 M.OMEGA. per square and being connected to the reference electric potential (i.e., ground or mass) of the frame or body of the aircraft.The the protective layer is provided, for example, by applying at least a paint layer forming, once dry, a coating exhibiting the required surface resistivity.

Abstract: In order to absorb ions and corrosive products which accumulate in a hydraulic circuit during its operation, particularly a hydraulic circuit in an aircraft which operates to control the operation of the aircraft, a solid material is disposed within the liquid which circulates through the circuit which is capable of chemically fixing these ions or products at its surface. The solid material may comprise a corrodible grade of iron and it may be in the form of a type of sieve.

Abstract: A piloting aid system for displaying symbols representative of determined characteristics of the flight of an aircraft and representative of its environment is disclosed. The symbols are displayed on the screen of a display unit which displays a symbol representing the aircraft near a predetermined point on the display screen and a rectangular window for guiding the flight path of the aircraft. The sides of the guidance window are parallel to mutually perpendicular axes provided on the screen. The abscissa and ordinate of the predetermined point are respectively proportional to the drift and to the slope relative to the ground of the aircraft flight path.

Abstract: In a method for at least partly metalizing the surface of a laminated component, the layer of material which is to form part of the surface of the component is first metalized; then it is coated, as are the other layers of non-metalized material, with a polymerizable resin; and lastly the coated layers are stacked on the lower part of a mould, which is then subjected to pressure, possibly under heat.

Abstract: A flexible, electrically conductive jointing material consists of an elastomer containing metal in a divided state distributed in its mass. The metal is in the form of laminae or paillettes of aluminium or of aluminium alloy, the length of which is greater than their width or thickness. The elastomer, which may be the product known under the name "Thiokol", exhibits a pasty consistency when applied enabling it to be spread with a spatula and mixed in situ. The jointing material may be used for connecting together the structural parts of aircraft.

Abstract: A method of preparing an antistatic coating exhibiting a desired value of surface resistivity which is substantially stable with respect to time takes as its starting point a commercial antistatic product having a synthetic resin base and substantially free from metallic particles but of which the surface resistivity, measured after mixing with its hardener and drying, is very much below the desired value. A compatible insulating resin is added to this product so as to raise the surface resistivity, still measured after mixing with the hardener and drying, to a value much higher than the desired value. The resulting product is then subjected to an accelerated ageing treatment causing a reduction in surface resistivity with terminal asymptotic development to the level of the desired value. Such a coating may be applied to radomes and other aircraft surface elements, and has the advantage that its conductivity does not increase appreciably with age.

Abstract: A connecting rod for the control and/or transmission of force, particularly for use in aeronautical construction, comprises a tubular body formed of high-strength fibres bonded together by polymerized epoxy resin. The body has frusto-conical end portions each surrounding a frusto-conical skirt portion of an end member which is adapted to receive coupling means. A ferrule, also formed of bonded fibres, is provided to tighten each frusto-conical end portion of the body against the frusto-conical skirt portion of the corresponding end member.

Abstract: An aircraft is equipped with a rearwardly pointed television camera connected to an electronic receiver situated in front of the pilot. The image provided by the camera at the receiver appears in mirror reversed inverted or symmetrically opposite position, in order that the maneuvers required for rearward firing can be carried out by the common piloting reflexes for forward firing.