Abstract: A method and tool for repairing a damaged zone of an aircraft radome, using the actual radome itself as a heating chamber to avoid resorting to an autoclave and the removal of certain parts of the radome which cannot withstand the curing temperature needed for the repair. The method for repairing a radome, wherein the radome comprises a composite panel exhibiting a double curvature forming a dome, the panel comprising at least one damaged zone, comprises the steps of closing an interior space of the panel using a cap to form a repair chamber. The surface of the panel forms the repair chamber containing the damaged zone. Another step is heating the space inside the repair chamber to form a heating chamber allowing the curing expected for repairing the damaged zone.

Abstract: A new and improved system for interconnecting components in a vehicle body structure, and especially for interconnecting fiber-reinforced composite components in a fuselage structure of an aircraft. The system includes: a first adapter member having a first mating portion that is adhesively bonded with a profile of a first component of the structure in more than one plane, and a first attachment portion connected to the first mating portion; a second adapter member having a second mating portion that is adhesively bonded with a profile of a second component of the structure in more than one plane, and a second attachment portion connected to the second mating portion; and a connector member to securely interconnect the first and second attachment portions of the first and second adapter members.

Abstract: A method for aiding the landing of an aircraft on a landing runway comprises the following steps implemented automatically by a processing unit: a) acquiring information relating to the runway; b) acquiring information relating to a current situation of the aircraft; i) determining a landing position of the aircraft on a central longitudinal axis of the runway, as a function of a trajectory determined between a current position of the aircraft and this landing position to comply with at least one constraint relating to a roll angle of the aircraft; j) determining a parameter relating to the landing position; k) determining a deviation between this parameter and a reference value; l) comparing this deviation with a predetermined threshold; and m) as a function of the result of the comparison carried out in step l), commanding, if appropriate, the signaling of an alert via the signaling system of the aircraft.

Abstract: A lightweight shield for aircraft protection against threat of high energy impacts, which comprises, a structural layer that has a first side and a second side, the first side being intended for receiving the impact, and a ballistic material layer for absorbing high energy impacts, having a first side and a second side. The first side of the ballistic material layer is faced to the second side of structural layer and joined to the structural layer via a progressively detachable interface and, the second side of the ballistic material layer is a free surface.

Abstract: The invention includes a process for one's own global navigation satellite system and at least one other global navigation satellite system including the following: Receiving ranging signals and navigation messages or ranging signals only from the at least one other global navigation satellite system, and processing the received ranging signals and navigation messages in a similar way as the ranging signals and navigation messages of the owned global navigation satellite system.

Abstract: A virtual window assembly for an airborne vehicle includes at least one camera configured to capture a panoramic and time-resolved image data stream from the view to the outside of the airborne vehicle, an image data processor coupled to the camera and configured to receive the captured image data stream and split the image data stream into a plurality of partial image data streams corresponding to different viewing angles of the panoramic image data stream, and a plurality of electronic displays mounted to an inside of a hull of the airborne vehicle, coupled to the image data processor and configured to receive partial image data streams. Each of the electronic displays is configured to display one of the partial image data streams so that the physical mounting location of the electronic displays in the airborne vehicle corresponds to the associated camera viewing angle of the displayed partial image data stream.

Abstract: A connection comprising a first duct, a second duct, a flexible tube which comprises a first end configured to cover part of the first duct, and a second end configured to cover part of the second duct, a first clamping system configured to clamp the first end of the flexible tube around the first duct, and a second clamping system configured to clamp the second end of the flexible tube around the second duct.

Abstract: A component monitoring apparatus [100] including an input [110] to receive sensor data from a sensor arrangement [S1-S4]. The sensor data representative of a use of a respective component [105] during a monitoring interval. A memory [118] provided to store received sensor data and a life parameter associated with the component [105], an interface [126] provided to communicate with a remote device and a power cell [128] provided to power the apparatus [100]. The apparatus [100] arranged to: store in the memory [118] received sensor data, in response to a trigger, read the sensor data from the data memory [118] and transfer the sensor data to the remote device, and, in response to receipt of a data packet containing a life parameter associated with the usage of the component [100], store the life parameter to the memory [122].

Abstract: Provided is an end system device for a network system with a first port for connection with the network system, a second port for connection with the network system, a local interface and a switching device. The switching device is designed to switch into a first or a second mode. In the first mode, the switching device is set up to relay data received at the first and second port to the local interface, and relay data received at the local interface to the first port and the second port. In the second mode, the switching device is set up to relay data received at the first port to the second port or to the local interface, relay data received at the second port to the first port or to the local interface, and relay data received at the local interface to the first port and the second port.

Abstract: A method for aiding the landing of an aircraft on a landing runway comprises the following steps implemented in an automatic manner by a processing unit: a) acquiring information relating to the landing runway; b) acquiring information relating to a current situation of the aircraft; c) determining, as a function of said information, at least one deviation between at least one parameter relating to a landing position of the aircraft on the landing runway and a reference relating to a central longitudinal axis of the landing runway; d) comparing this deviation with a predetermined threshold; and e) as a function of the result of the comparison carried out in step d), commanding, if appropriate, the signaling of an alert by means of a signaling system of the aircraft.

Abstract: A transmitter for a dual-frequency satellite-to-earth downlink. The transmitter comprises a plurality of modulators, a first and a second plurality of amplifiers. In one embodiment, each of the modulators is configured to modulate respective input data onto a respective one of a first plurality of signals in a first frequency band and to modulate the respective one of the first plurality of signals onto a respective one of a second plurality of signals in a second frequency band. Each of the first plurality of amplifiers is configured to amplify one of the first plurality of signals to a first predetermined signal strength. Each of the second plurality of amplifiers is configured to amplify one of the second plurality of signals to a second predetermined signal strength. A number of the plurality of modulators is smaller than a sum of a number of the first and second pluralities of amplifiers.

Abstract: A structural component for an aircraft or spacecraft, comprising: a planar member; a reinforcing member which projects from the planar member and is rigidly connected thereto; the reinforcing member comprising at least a foam layer and a cover layer, a plurality of pins extending at least through the foam layer and the cover layer, and at least the pins and the cover layer comprising a curable matrix.

Abstract: An aircraft landing gear comprising a wheel rotatably mounted on an axle, a first gearing element that rotates with the wheel, a second gearing element configured to mesh with the first gearing element such that rotation of the first gearing element causes rotation of the second gearing element, wherein the second gearing element is connected to a generator, such that rotation of the second gearing element causes the generator to generate electrical energy, further comprising a heat dissipation device connected to the generator wherein the heat dissipation device comprises an electrical heating element connectable to the generator to receive generated electrical energy and convert it to heat energy, and a fluid receptacle adjacent the heating element, such that fluid in the receptacle can be heated. An aircraft landing gear further comprising a cavitation braking device, an aircraft and a method of braking.

Abstract: A conductive device to form electrical connections on the surface of a structure made of composite material. The device includes a thin interface layer having a face via which the device is fixed to the surface of the structure made of composite material. A conductive metal element is placed on the face of the interface layer opposite the face making contact with the surface of the structure. The conductive element is configured to be able to undergo tensile and compressive stresses without damage. A protective layer is configured to protect the conductive element from attack from the environment surrounding the structure. These various elements are arranged relative to one another such that the length of the conductive element can vary as a function of temperature variations independently of the amplitude of the variations undergone by the structure on which the device is mounted.

Abstract: A method of controlling the attitude of a spacecraft in spinning around itself with a non-zero total angular momentum HTOT. The spacecraft includes a set of inertia flywheels configured to form an internal angular momentum HACT. The axis of the total angular momentum HTOT is aligned with a principal axis of inertia of the spacecraft, in the course of which the inertia flywheels are controlled to form an internal angular momentum HACT. The following expression, in which J is the inertia matrix of the spacecraft: Hact×J?1(Htot?J?1Htot) is negative if the principal axis of inertia targeted is the axis of maximum inertia of the spacecraft and is positive if the principal axis inertia targeted is the axis of minimum inertia of the spacecraft.

Abstract: An aircraft of flying wing or blended wing body type comprising, for access to a pressurized housing, a non-pressurized door in the trailing edge of the aircraft and a pressurized door on the pressurized housing. The distance between the center of the pressurized door and a plane of symmetry of the aircraft is less than or equal to the distance between the center of the non-pressurized door and the plane of symmetry, and the pressurized door is located on a wall other than a rear wall of the pressurized housing or upstream of a rear extremum point of the housing in the absence of any such rear wall.

Abstract: A method and equipment for installing a tapped insert in a cylindrical bore, the equipment including a tool body comprising a threaded end portion, the threaded end portion being adapted to a threaded inner wall portion of a cylindrical body of the tapped insert; a screw of diameter lower than a diameter of an inner bore of the tool body, the comprising at one end a thread complementary to the inner tapped aperture of the core of the tapped insert; and a positioning ring installed to slide on the tool body, the tool body and the positioning ring comprising complementary sliding means adapted to enable relative sliding of the positioning ring on the tool body in a longitudinal direction and to maintain the positioning ring on the tool body in a defined longitudinal transverse section.

Abstract: Data is routed within a data network (8), for example a mobile ad hoc network (MANET), comprising at least one wireless network node (10), typically having a router (11). A processor (18) analyzes characteristics of a wireless link (12ab) between a pair of nodes (10a, 10b) within the network (8). Following such analysis, the processor (18) assigns a link class to the wireless link (12ab), the link class being chosen from a predefined set of link classes. A first link class represents that the link (for example link 12ab) is suitable for carrying one or more types of traffic (for example real-time audio and text), but not suitable for one or more other types of traffic (for example real-time video of a certain quality). A second link class represents that a link (for example link 12ac) is suitable for two or more types of traffic (for example real-time audio and real-time video) including at least one type of traffic (for example real-time video) not supported by the first link class.

Abstract: System and method to generate automatically a compact application code suitable for taking advantage of the intrinsic power of processors. The system can generate the application code executable by a processor from a formal specification associated with an application, the formal specification including operators, and the system including an analyzer to code each operator of the formal specification by a corresponding operation code followed by a minimum number of input code(s) and output code identifying input and output parameters associated with the operator, thus automatically generating a compact application code suitable for being stored in a memory associated with the processor and for being executed by an interpreter of the processor.

Abstract: A device for visually scaring animal species, in particular bird species includes means for generating at least one visual signal including at least one image, varying in size over time, which simulates approach via an increase in the size of the image. For example, the visual signal includes one of the following images: eyes, a disc, and a spiral.