Abstract: A refueling apparatus for interconnecting a tanker aircraft (11) with a receiver aircraft in flight comprising a boom (21) joined to said tanker aircraft (11) by means of a mechanical articulation (41) having control means including a central computer station, an inner fuel conduit, a refueling nozzle (27) at its distal end and, and a smart tip assembly comprising a first module (83) having load sensing means, a second module (85) having load alleviation means and a third module (87), joined to the nozzle (27), having a mechanical fuse (99) for allowing the safe separation of tanker and receiver aircraft in the event of overloads. The invention also comprises a method of load alleviation for minimizing the loads on the boom (21).

Abstract: Control station which comprises: a seat (10) for the operator of the said control station, the seat (10) comprising at least one arm rest (30), and a control and command assembly, said assembly comprising a control stick (1) with controls, mechanical components for transmitting and generating forces and movement to and from the control stick (1), components (17) for measuring the position of the control stick (1), and electronic components which are connected to the control stick (1) and via which the control and command assembly is operated, the control stick (1) of the said control station being incorporated in the seat (10), the control stick (1) being situated moreover on the armrest (30).

Abstract: Training method for the simulation of an operation performed by at least one device which is part of a real apparatus, wherein the method comprises providing to display means overlaid images under controlled depth order of a virtual apparatus, and real images of said device, and providing a simulated response to control means, based on data of the position and behavior of said device and on data of the position and behavior of said virtual apparatus.

Abstract: A backup device for raising a refueling boom interconnecting a tanker aircraft with a receiver aircraft in flight, the boom being joined to the tanker aircraft by a mechanical articulation and a hoist cable. The backup device includes a secondary cable fixed at one side in the boom, and fixed at the other side in a cable actuator placed inside the tanker aircraft, the secondary cable being extended along the underside of the tanker aircraft and along the boom, and attached to them in at least three intermediate points with clips or staples that can be released by a force exerted through the secondary cable. The cable actuator has rolling devices to roll the secondary cable for raising the boom to the stowed position.

Abstract: Method and device for in-flight boom refuelling operations using an articulated boom (11) and a cable (18), said boom (11) comprising movable aerodynamic surfaces (16), said method comprising the following steps: a) from a completely stowed-away and retracted position of the boom (11), the cable (18) is initially released, thereby starting to lower the boom (11), such that the said cable (18) is kept tensioned during the whole of step a) by means of the force supplied by the movable aerodynamic surfaces (16) and/or the force of gravity acting on the boom (11); b) after reaching the maximum deployed position of the boom (11), or the bottom end of the flight envelope of the boom (11), release of the cable (18) is stopped; c) while keeping the length of released cable (18) fixed, the boom (11) is brought into a suitable position for commencing the manoeuvres for refuelling of the receiver aircraft; d) the manoeuvre for connecting the boom (11) to the receptacle of the receiver aircraft is started by means of

Abstract: An aircraft telescopic in-flight refueling mast comprising a metallic structural beam (31), electrically connected to the aircraft by flexible conductive means (33), having inside a fixed metallic tube (11) and a metallic telescopic tube (11) providing the fuel conduit, and, attached to said beam (31), flight control surfaces (41) and protection means against electric discharges, specially lightning strikes and electro-static discharges, including insulated means (39, 51) and low conductive means (15, 17) for reducing the lightning currents at a safe level and for draining the static charge created during the refueling, and conductive means (19, 21, 23, 33, 43) providing a safe lightning current path and good electrical bonding for electro-static discharge.

Abstract: Method for the certification of heater blankets by means of infrared thermography, in which a heater blanket (1) to be certified is enclosed in a vacuum bag (3,4,5,5?,8,9,10) arranged above a support (2) and thermally insulated therefrom, the vacuum is formed inside said bag and said heater blanket is connected until its temperature is stabilized at a predefined value, considerably higher than the ambient temperature, whereupon the best infrared image or images of said heater blanket (1) are recorded and stored by means of an infrared camera (14) situated opposite it, then interrupting the electric power supply to said heater blanket and processing the stored images so as to produce, finally, a certification report.

Abstract: A fairing for streamlining the junction between the horizontal stabilizer and the fuselage or the fin of an aircraft, comprising an upper fairing shell, a lower fairing shell, a leading edge extension, and several fittings to join the upper and lower fairing shells to the horizontal stabilizer. The upper and lower fairing shells are solid laminates of composite material that are designed with a shape, composition, and thickness such that they can be elastically deformed when they are fitted to the horizontal stabilizer, providing a contact force permitting them to lay permanently in contact with the fuselage or fin. A process for manufacturing the fairing shells.

Abstract: Assembly for testing a panel (11) made of composite material under different combinations of shear-compression loads using an universal tension load machine (16), comprising metallic sheets (12) configured to form, together with the panel (11), a frame of rectangular shape in the same plane than the panel (11), being said metallic sheets (12) able to transmit external loads to the panel (11), two loading parts (19), having translatable lugs (20) to be connected with the universal tension load machine (16), joined at two opposed sides of said frame and a structure (18) to prevent displacements out of the panel (11).

Abstract: Leading edge of supporting surfaces of aircraft. A primary structure (EP) made without ribs is assembled with a specific frontal area (ZF) against impacts. The primary structure comprises two upper and lower covering panels (1, 2) and two diagonal and frontal spars (3, 4), which constitute the strong and rigid structural assembly of the leading edge (BA). The frontal area (ZF) is made up of one or two elemental parts which determine a kind of roof tile which closes the outer aerodynamic contour of the profile of the leading edge (BA) and provides a good behaviour against erosion, operational impacts on the ground and the impact of birds in flight. The invention is applicable to wings, stabilizers and control surfaces of aeroplanes.

Abstract: A process for manufacturing primary structures of composite material with curing in a female tool, comprising the steps of laminating superimposed composite material layers in a pre-impregnated state; placing the obtained laminate over a forming tool, loading the assembly of the laminate and forming tool in a vacuum bell and applying a pre-established forming operation, loading the formed laminate, still in a green state, in a female tool suitable for its curing, placing lateral caul plates in the tool and inserting elastomeric pipes in channels of the caul plates, fitting a central caul plate, sealing the assembly and applying a vacuum bag with perforations to remove the air from its interior. The assembly is cured in an autoclave.

Abstract: A process for manufacturing pre-cured parts of composite material with green-applied stiffeners, comprising the lamination of superimposed pre-impregnated composite material sheets to obtain a base part (1) and a second part (2) intended to be bonded with it; curing the base part (1); hot forming the laminate destined to form the second part (2); removing the second part (2) from the forming tool thereof and deposit it over the base part (1), intercalating a structural adhesive sheet between both of them; closing the assembly of both parts inside a vacuum bag and loading said bag in an autoclave, carrying out a curing cycle of the second part (2) under pressure and temperature, so that it is strongly adhered to the base part (1). The invention is applicable to the field of aeronautics.

Abstract: A process for making a dismountable and/or fixed traction-compression coupling to be applied to composite materials, in which a basic laminate (1) of composite material is folded at least once to obtain at least one skirt (2) forming an angle close to 90° with the rest of the laminate; by using a transition radius between the skirt and the rest of the laminate, a set of distribution plates (5, 6) is applied over the basic laminate to stabilize the skirt and produce a uniform load distribution, making holes in each set of distribution skirt-plates and introducing traction bolts (4) with an initial pretension in said holes, hence obtaining the connection between the components to be joined. The invention is applicable to the aerodynamic structures of aircraft.

Abstract: Leading edge of supporting surfaces of aircraft. A primary structure (EP) made without ribs is assembled with a specific frontal area (ZF) against impacts. The primary structure comprises two upper and lower covering panels (1, 2) and two diagonal and frontal spars (3, 4), which constitute the strong and rigid structural assembly of the leading edge (BA). The frontal area (ZF) is made up of one or two elemental parts which determine a kind of roof tile which closes the outer aerodynamic contour of the profile of the leading edge (BA) and provides a good behaviour against erosion, operational impacts on the ground and the impact of birds in flight. The invention is applicable to wings, stabilizers and control surfaces of aeroplanes.

Abstract: A system for the modification of the rigidity and damping properties of structural joints comprises at least an intermediate structure (3) to receive, on both sides, two structures (1, 2) to be coupled; releasable blocking means (6) to immobilize, in a coupled condition, said two structures to be coupled and said intermediate structure; first and second sets of bistable components (7, 8), the structural resistance features of the components of the first set being different from those of the second set; the components of the first set being internally connected to one of said structures to be coupled and to said intermediate structure; the components of the second set being internally connected to one and other of said structures to be coupled; said bistable components being in an unstable condition when all the mentioned structures are coupled together. The invention is applicable to the field of space vehicles.

Abstract: System for attaching and separating satellites which comprises an open ring or metal band (1) which has a channel formed in its inner perimeter, in which jaws are integrated in a discontinuous way, which can slide in the said channel, two end pieces (5) fixed to the ends of the said ring, a tensioning bolt (4) which joins the two end parts, and three supports for retaining the ring (1) which are fixed to the structure of the launcher (3) of a satellite (2). The invention can be applied to artificial satellites of any weight and size.

Abstract: New type of planar antenna of microwaves appropriate for operating in linear and circular polarization, free of welds and floating potentials, and therefore free of electrostatic discharges and problems related to passive intermodulation products, whose application is of particular interest in aircraft and space technologies. The antenna consists in the interconnection of a microstrip radiator with a spiral antenna of wires. For certain applications wherein the radiators are arranged in a same plane, the radiating effect of the patch may reduce the size of the spiral.