Abstract: A method for securing a geographical area encompassing a route. A map of the area is obtained. A weapon is associated with a firing modeling consisting of a probability model of hitting its target when shooting, as a function of the firing distance. Positions of potential shelters of threats on the map are determined by using a trained artificial intelligence device. The modeling is applied for each weapon and potential shelter while relating the shots to the route and summing all the probabilities of hitting its target on each portion of the route. The potential shelters most likely to constitute attack threats along the route are determined. A path is defined in order to address these potential shelters most likely to constitute attack threats.

Abstract: An active trim system of a flight control system of an aircraft that transmits a tactile feel to a pilot of the aircraft in response to a manoeuvre. The active trim system includes: a manual control member (6) an elastic deformation means (1) and a reversible actuator (2), intermediate linkage member (4) and a controller. The actuator (2) includes a rod (5) and a motor (3) parallel to the elastic deformation means (1) and is movable by the motor (3) and by the motion of the manual control member (6). The intermediate linkage member (4) is linked to the manual control member (6) between the manual control member (6) and the elastic deformation means (1) and the reversible actuator (2), a controller configured to: move the reversible actuator (2) to a predetermined zero position, and to provide stiffness against a displacement of the intermediate linkage member (4).

Abstract: An apparatus management system for controlling at least one function of an apparatus, such as a vehicle, operated by an operator and exposed to a potential impact approaching the apparatus, includes: an impact reaction system, configured for generating a command for controlling the at least one function of the apparatus; wherein the impact reaction system includes: an intervention control unit; and an operator notification unit. The intervention control unit includes at least one control model configured for assessing at least one command for controlling the at least one function of the apparatus to perform an intervention to avoid the impact. The operator notification unit is configured to issue at least one notification to the operator regarding the at least one command. The intervention control unit is configured to output the at least one command for controlling the at least one function of the apparatus subsequent to issuance of the notification.

Abstract: A multiple hold down and release device for restraining and releasing a payload from a spacecraft performs methods to release a payload from a spacecraft and install a multiple hold down and release device. At a periphery, the device includes hold-down assemblies. Each assembly has a hold-down bracket configured to attach to the payload and a hold-down support, both having conical mating surfaces. Each hold-down support includes a torsion spring(s) around an axis. In pairs of connecting levers, each lever includes a first end coupling to a corresponding hold-down support such that each corresponding lever is articulated with the corresponding hold-down support through an axis; and a second end opposite the first end. Restraint cables join second ends of each pair of connecting levers and are arranged radially with a central area where the restraint cables cross. A central release actuator is configured for cutting the restraint cables.

Abstract: A multiple hold-down and release device for spacecraft includes a central structure including a central section with a cylindrical inner hole, an inner axial shaft insertable into the inner hole. A release bolt aligns with the inner axial shaft. A main bushing is partially arranged inside the inner hole and axially guided by guiding bushings on the main bushing and the inner hole. The main bushing includes a protrusion and internal retainer spring. Arms protruding from the central section are axially preloaded by a pusher opposite the central section. Connecting levers each connect to the end of the corresponding arm by the pusher. Hold-down assemblies on the periphery of the device each include a hold-down support and a fastener with conical contact surfaces, a torsion spring around a torsion spring shaft, and articulated with the corresponding hold-down support by the corresponding torsion spring shaft.

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.