Abstract: An air to air refueling system that monitors and adapts the movement at an end of an air to air refueling hose of a tanker aircraft to counteract undesirable movements at the end of the hose though generating aerodynamic loads in the end of the hose. The system includes grid fins at the end of the hose that are automatically rotated to counteract the undesirable movements.

Abstract: A computer assisted method for manufacturing a foldable paraboloid antenna includes election of a two-dimensional radial Origami pattern with triangular cells and election of a paraboloid surface. The Origami pattern is projected from the paraboloid surface focus onto the paraboloid surface to print the Origami pattern on the paraboloid surface, obtaining triangles with curved sides. A pattern with triangles with straight sides on the paraboloid surface is obtained by joining vertices of the projected curved-sided triangles. The method includes scaling and calculating centroids of the triangles, to reduce each triangle referenced on the corresponding centroid and to determine spacing, obtaining a mesh with segments and triangular cells delimited by the segments. The triangular cells have triangles of reflective rigid material. The mesh is flexible, so each segment width is at least the sum of the thicknesses of two adjacent rigid triangles, and periphery cells have a rounded outer edge.

Abstract: A deployable assembly for antennae includes a structure having a reflective surface and n pairs of segments, each pair of segments corresponding to one side of a deployed polygonal shape. N hinge joints are between the two segments of a side. N hinged angular links are between every two adjacent sides. The structure is changeable from a stowed substantially cylindrical shape into a deployed substantially planar polygonal shape with n sides. A deployable boom is between two segments. The boom lays stowed between the two segments before deployment and ends in a feeder electromagnetically feeding the antenna and includes a clamping element for keeping the structure closed when stowed. The feeder acts as structural support element when stowed and electromagnetic feeder for the antenna when deployed. A cable network shapes the reflective surface, with corresponding cables held by tensor elements protruding from the back of the segments.

Abstract: An articulated mechanism is included in an articulated pointing system. The articulated mechanism includes first, second, and third spherical joints, and a first, second, and third lever. The first and second spherical joints are linked by the first lever. The first lever includes a first projecting portion. The first and third spherical joints are linked by the second lever, the second lever including a second projecting portion projecting in an opposite direction of the first projecting portion. The second and third spherical joints are linked by the third lever, such that the longitudinal axes of the first lever and of the second lever are perpendicular. The articulated pointing system includes a basement platform and a mobile platform joined by two articulated hinges. The hinges are moved by actuators. The articulated mechanism has the first lever attached to the mobile platform and the second lever attached to the basement platform.

Abstract: A method and system for Air-To-Ground communications allowing integration of the aircraft communication with a terrestrial cellular communications network. The solution is carried out in the aircraft so any existing standard terrestrial cellular communication network may be used without requiring any modification. The constraints due to the special aircraft conditions (speed and height) are efficiently solved, allowing broad interoperability with the cellular communications network, satisfying the increasing high speed data demand. Specifically, in order to solve the handover constraints the aircraft antenna will create at least two radiation patterns: one for maintaining the current connection with the serving base station and another one or more to search the next suitable best station for handover.

Abstract: An assembly having an aircraft door and auxiliary equipment. The aircraft door and the auxiliary equipment are connected by a flexible deformable bellows having creases. The door comprises a passing through hole and a support joinable to the first end of the bellows. The auxiliary equipment comprises a support joinable to the second end of the bellows and a projecting part. The projecting part is configured to have elevation movement and/or azimuth movement, and the projecting part crosses the interior of the bellows and the hole of the door and protrudes out of the door. At both ends of the bellows a clamp joins and tightens each end of the bellows with the corresponding support. There is a fixed joint between the first end of the bellows and the door and a movable joint between the second end of the bellows and the auxiliary equipment.

Abstract: A referencing system to assist a receiver aircraft in relative positioning during in-flight refueling operation that includes an array of references congregated on a spot of the tanker aircraft, wherein the array of references provide a distinguishable visual indicator depending on the sector where the receiver aircraft positions.

Abstract: A computer assisted method for manufacturing a foldable paraboloid antenna includes election of a two-dimensional radial Origami pattern with triangular cells and election of a paraboloid surface. The Origami pattern is projected from the paraboloid surface focus onto the paraboloid surface to print the Origami pattern on the paraboloid surface, obtaining triangles with curved sides. A pattern with triangles with straight sides on the paraboloid surface is obtained by joining vertices of the projected curved-sided triangles. The method includes scaling and calculating centroids of the triangles, to reduce each triangle referenced on the corresponding centroid and to determine spacing, obtaining a mesh with segments and triangular cells delimited by the segments. The triangular cells have triangles of reflective rigid material. The mesh is flexible, so each segment width is at least the sum of the thicknesses of two adjacent rigid triangles, and periphery cells have a rounded outer edge.

Abstract: A system for monitoring the degradation status of refueling hoses on air includes a device with at least one sensor adapted to produce data about the external surface of the refueling hose. The method for monitoring the degradation status of refueling hoses on air includes moving a device with at least one sensor along a refueling hose or moving a refueling hose with respect to the device, producing data about the external surface of the refueling hose from the at least one sensor, and analyzing the data for monitoring the degradation status of the refueling hose. It allows providing a system and method for monitoring the degradation status of refueling hoses on air that reduces the risk of personal injury associated to hose damage inspection and is cost saving.

Abstract: A system for monitoring the state of a hook-keeper unit of an aeronautical structure. The hook-keeper unit is movable between a latched state and in a non-latched state, a mechanical warning element is movable between an exposed state and an unexposed state, and a connecting mechanism comprises a first end coupled to the hook-keeper unit, and a second end coupled to the mechanical warning element. The connecting mechanism is configured to automatically transmit the state of the hook-keeper unit to the mechanical warning element. The hook-keeper unit and the mechanical warning element are coupled between them by the connecting mechanism in an automatic bijective relationship, so that when the hook-keeper unit is in the latched state, the mechanical warning element is automatically in the unexposed state, and when the hook-keeper unit is in the non-latched state, the mechanical warning element is automatically in the exposed state.

Abstract: A firing simulation scope, for installation on a rifle, includes an inertial measurement unit, a windage correction adjustment device, an electronic system, a microphone, a display and an interface for connection to a control station.

Abstract: A connecting-separating device is for separating satellites from launchers or satellite dispensers. Circumferentially aligned clamps can be coupled on their inner face on rings of separable elements constituting the union interface between the two separable elements. A release mechanism connects two of the clamps through one of the ends of the clamps. The two clamps are connected by the release mechanism include a protrusion protruding from their outer faces at the end opposite the end connecting with the release mechanism. The rest of the clamps include a protrusion protruding from their outer faces at each of their ends adjacent the adjacent clamps, so that each pair of clamps adjacent and not connected to one another by the release mechanism are connected to one another by connectors connecting the protrusions.

Abstract: A system for warning an open state of a two-part fan cowl of an aeronautical structure, wherein the system includes at least one device arranged between these two parts of the fan cowl and adapted to exert force spacing them apart from each other, thus leaving a predefined gap between them at their lower ends when that two-part fan cowl is in the open state.

Abstract: A high power generation system for aircraft includes: a non-propulsive mechanical power source turning a permanent magnet generator (PMG) to generate AC electrical power; a high voltage rectifier unit (HVRU) converting the AC electrical power to DC electrical power, and a control unit controlling the rotational speed of the non-propulsive mechanical power source and the HVRU, wherein the HVRU is configured to increase voltage and current of the DC electrical power using at least one winding of the PMG.

Abstract: A deformable auxetic structure for absorbing energy of an impact that comprises a plurality of interconnected adjoining tridimensional auxetic cells where each tridimensional auxetic cell comprises at least one surface element and a plurality of legs extending from the surface, the plurality of legs and the surface element being configured such that the sectional cut of the structure in at least two planes perpendicular to the surface element follows an auxetic pattern.

Abstract: A power distribution system for a DC network, the DC network comprising electrical loads, the power distribution system being boarded on an aircraft and comprising: a plurality of AC/DC converters, and at least one AC power source. The power distribution system comprises: an “n” number of AC/DC converters, each one comprising an “(n?1)” number of first outputs and at least an additional output, and an “(n?1)·n” number of electrical loads. Each electrical load comprises two inputs: a first input for being connected with a corresponding first output, and a second input for being connected with any of the additional outputs. The power distribution system is configured to continue supplying electrical power to the DC network in case an AC/DC converter is not energized, such that the second input of such electrical load is connected to any additional output of another AC/DC converter, being the first input disconnected.

Abstract: A method and system for determining the weight and at least a first coordinate of the center of gravity of a structure such as a vehicle, in particular, an aircraft.

Abstract: An air to air refueling hose for an aircraft comprises an internal structure suitable for transporting fuel inside, an intermediate structure arranged around the internal structure, and an external structure arranged around the intermediate structure such that the intermediate structure is located between the internal structure and the external structure, and a sensing arrangement comprising electric conductors arranged along the air to air refueling hose and embedded inside of the external structure.

Abstract: A frictionless service carriage system including: a shaft 1 having a first 2 and a second 3 helix-shaped guide in its surface, each helix shaped-guide 2, 3 defining a linear movement along the longitudinal axis of the shaft 1 of a carriage 4 in opposite directions and both helix shaped-guides 2, 3 crossing each other 2, 3 along the longitudinal axis of the shaft 1, wherein the carriage 4 includes a movable element 5 located successively in each of the helix-shaped guides 2, 3 and movable along the guides 2, 3, the movable element 5 comprising a set of rolling elements 6 along the first or second helix-shaped guide 2, 3 of the shaft 1 and configured such that in a crossing with the other helix-shaped guide 2, 3, the set of rolling elements 6 has at least two contact points with the helix-shaped guide 2, 3 for which it rolls.

Abstract: A lightweight spacecraft dispenser, which consists of a material made from composite materials, and of a ring structure with several payload ports. The ring structure has a surface that extends between opposite ends of the ring structure and that is at least partially spherical. The surface can be completely spherical or partially spherical between the opposite ends.