Abstract: A fuselage arranged within a fuselage outer shell; at least one main rotor located on top of the fuselage; at least one engine provided for driving the at least one main rotor; and at least one energy source storage unit comprising at least one energy source configured to provide energy for powering the at least one engine for driving the at least one main rotor; wherein the at least one energy source storage unit is arranged outside the fuselage outer shell; and wherein the fuselage and the fuselage outer shell form in vicinity of the at least one energy source storage unit a crashable structure configured to be crashable in an emergency landing at least for limiting effects of impact on the at least one energy source storage unit.

Abstract: A method for manufacturing a soundproofing assembly involving providing a first panel of honeycomb structure, fastening an intermediate plate against a second face of the first panel, adhesive-coating a layer of adhesive on the intermediate plate, providing a second panel of honeycomb structure, bonding the first face of the second panel to the layer of adhesive, and perforating the intermediate plate and the layer of adhesive through the cells of the first panel or the cells of the second panel at the bonding zone of the second panel. Such a method makes it possible to save time by dispensing with additional preparation steps.

Abstract: Computer systems (100) for satellite image acquisition and mission-plan calculation devices (120) for satellite and also Earth observation satellites (110). Based on the observation that the uncertainty connected with meteorological conditions can lead to the development of mission plans, for satellites, with low effectiveness, the uncertainty is characterized and used to improve the preparation of mission plans for satellite. A model of the uncertainties is built upon observations and/or past meteorological forecasts. Next, at the time of planning, the model is used by presenting the observations and/or the current forecast as input to the model. In that way, the acquisition zones for which it is unlikely to get acceptable images on the preferred acquisition date may be identified.

Abstract: A battery and an electrical battery monitoring device are disclosed having a first group of sensing switches connected in series on a first monitoring circuit, the sensing switches, a second group of electrical sensing switches connected in series on a second monitoring circuit, an input unit to provide an input to the first and second monitoring circuits, a monitoring unit to receive an output from the first and second monitoring circuits, wherein the monitoring unit receives at least two outputs from two measuring points of the first monitoring circuit, the two measuring points being separated by at least one sensing switch. The location of a defective battery cell may be early detected and precisely located by the monitoring of the battery cells in rows and columns.

Abstract: A method for distributing a file in a network according to the 3GPP standard includes transmitting, by the first client entity, a file distribution request including the first address, modifying, by the gateway, in the file distribution request, the first address to a second address, transmitting the file distribution request including the second address to the second content server, modifying, by the second content server, the second address in the request to a third address, transmitting the request including the third address to the second client entity, transmitting, by the second client entity, a request to download the file comprising the third address to the content server, receiving, by the second client entity, the file, and storing, by some entities, correspondences between the addresses.

Abstract: A method for position calculation of an antenna is provided. The method comprises calculating ranges between the antenna and the at least three transponders. The calculation includes range measurements between an antenna and at least three transponders. Respective positions of the at least three transponders are known. The method further comprises providing a first coordinate of three coordinates. The three coordinates indicate a position of the antenna. The method further comprises calculating second and third coordinates of the three coordinates based on the calculated ranges between the antenna and the at least three transponders. The method further comprises predicting ranges between the antenna and the at least three transponders based on the provided first coordinate and the calculated two coordinates. The method further comprises performing an optimization process based on the calculated ranges and the predicted ranges to infer an optimized position of the antenna.

Abstract: A leading edge structure (1) for a flow control system of an aircraft (101) including a double-walled leading edge panel (3) with a first side portion (11) extending to a first attachment end (17), a second side portion (13) extending to a second attachment end (19), an inner wall element (21) facing a plenum (7), an outer wall element (23) facing ambient flow (25), and a core assembly (97). The outer wall element (23) includes micro pores (31) and the inner wall element (21) includes openings (33) which form a fluid connection from ambient flow, through the core assembly (97) and to the plenum (7). The thickness of the outer wall element is reduced due to the first attachment end (17) and/or at the second attachment end (19) attached to the inner wall element (21) by both bonding and fasteners (85, 87, 89, 91).

Abstract: Measures for managing satellite bearer resources of a satellite telecommunications network. A corpus of data based on historical satellite bearer resource allocations is maintained. A machine learning agent is trained with the corpus to determine a plurality of weights for use in directing satellite bearer resource management in the satellite telecommunications network. A satellite bearer resource allocation request is received. A set of features is extracted from a current environment of the satellite telecommunications network. The set of features defines currently allocated satellite bearer resources. On the basis of the determined plurality of weights and the set of features, satellite bearer resources of the satellite telecommunications network are managed to satisfy the request.

Abstract: A method of optimizing the noise generated by a hybrid power plant of a rotorcraft in flight, the hybrid power plant driving a main rotor of the rotorcraft in rotation and being provided with at least one engine, with at least one electric machine, and with at least one electrical energy source that electrically powers the electric machine. The method includes a determination step for determining a required power delivered by the hybrid power plant and that is required for the flight phase, and a distribution step for distributing the required power between the at least one engine and the electric machine as a function of a target noise level and of the required power for the flight phase, as well as of a model for the noise generated by the at least one engine as a function of one of its parameters.

Abstract: A time-delay latch for securing a structure in a specified position includes a housing, a fluid chamber contained within the housing for holding fluid, a pin that extends through the fluid chamber and is axially movable within and through the fluid chamber, and a release frame movably secured within the housing. When the pin is in a latched position, the release frame engages with the pin to prevent axial movement of the pin. When the pin is in an unlatched position, the release frame disengages from the pin to allow axial movement of the pin. The axial movement of the pin between the latched position and the unlatched position requires a prescribed duration of time to elapse. During operation, the axial movement of the pin between the unlatched position and the latched position can occur faster than the prescribed duration of time.

Abstract: A hatch locking device for an aircraft hatch includes an eccentric bush which can be connected to a hatch bulkhead of the aircraft hatch panel, an inner lining which is introduced into the eccentric bush and has a bolt receptacle which is oriented centrally along a bolt receptacle axis for receiving a locking bolt, a conical pressing sleeve in the inner lining, a conical clamping sleeve, the outer conical shell face of which is in displaceable engagement with an inner conical shell face of the conical pressing sleeve, and the inner cylindrical shell face of which is flush with the outer wall of the bolt receptacle, and linear actuators which are mounted on in each case two opposite sides of the conical pressing sleeve in the inner lining and are designed to displace the conical pressing sleeve along the bolt receptacle axis with respect to the conical clamping sleeve.

Abstract: A multipurpose connector for connecting a multiplicity of lines of an aircraft monument. The multipurpose connector comprises a base bracket, a system connector plate configured to receive a multiplicity of first line adapters, a monument connector plate configured to receive at least one second line adapter, and a movement device configured to move the system connector plate relative to the base bracket and the monument connector plate between an open position and a closed position. The system connector plate is, in the closed position, arranged relative to the monument connector plate such that the at least one second line adapter of the monument connector plate is operatively connected to an associated first line adapter of the system connector plate, and, in the open position of the system connector plate, the multiplicity of first line adapters and the at least one second line adapter are detached from one another.

Abstract: A system for assisting in the landing of an aircraft including a processing unit configured to: during a first phase of a landing runway approach procedure, when the aircraft flies above a predetermined height with respect to a landing runway threshold, determine a bias of position and speed information from an inertia unit of the aircraft, as a function of the merged position and speed information determined as a function of information from a receiver of ILS guidance signals and of information from a signal receiver of a satellite navigation system, then, during a second phase of the approach procedure, when the aircraft flies below the predetermined height, determine so-called adjusted aircraft position and speed information by applying, to information from the inertial unit, a correction corresponding to the bias determined during the first phase of the approach procedure.

Abstract: An optical sensing system comprising an optical fiber, a light source, a first interrogator and a second interrogator. The optical fiber includes one or more optical sensors. The light source is placed at a first end of the optical fiber and is configured to direct light towards the one or more optical sensors. The first interrogator is placed at the first end of the optical fiber. The second interrogator placed at a second, opposite end of the optical fiber. The first interrogator is configured to receive reflected light from the one or more optical sensors, and the second interrogator is configured to receive transmitted light from the one or more optical sensors.

Abstract: A rapidly disassembled hinge suitable for use in an aircraft includes a first attachment plate attached to a supported structure, a second attachment plate attached to a supporting structure, and a pin with a notch in an outer surface thereof, which is insertable into portions of the first and second attachment plates for pivotably connecting the first and second attachment plates together. The pin is inserted so that the notch is positioned within the second attachment structure when the hinge is in an assembled state. A key includes a main body and a distal end extending from the main body, the distal end being insertable within the notch of the pin. The key is movable such that the distal end of the key can be inserted into and removed from engagement with the notch of the pin to provide for toolless disassembly of the hinge.

Abstract: A device for avoiding a potential conflict detected in a predetermined trajectory prediction horizon between a first trajectory of a first ship or aircraft and a second trajectory of a second ship or aircraft is disclosed. Each trajectory includes a plurality of segments formed between multiple navigation points. The device includes a determination unit for determining at least one lateral peripheral envelope of the first trajectory, a division unit for dividing the lateral peripheral envelope into a plurality of juxtaposed sections arranged longitudinally the ones after the others and delimited by transition lines marking the change between sections, each transition line cutting, at a first point of intersection, a segment of the first trajectory and, at a second point of intersection, and an edge of the lateral peripheral envelope, a discretisation unit, and a computing unit.

Abstract: The method includes a step of acquisition of an image of the leading aircraft, a step of extraction of the outline, an adjustment step including implementing an outline registration algorithm, to determine an optimized profile from a comparison of the outline of the leading aircraft with a profile of the leading aircraft determined from a three-dimensional model of the leading aircraft and from an initial position of the following aircraft with respect to the leading aircraft, and a step of determination of the positioning according to six degrees of freedom of the following aircraft with respect to the leading aircraft, from the optimized profile and from the three-dimensional model of the leading aircraft. The method thus makes it possible to rapidly and accurately determine the positioning of the following aircraft with respect to the leading aircraft, this positioning being used to implement a formation flight.

Abstract: A method for fabricating a central caisson of an aircraft wing including a frame formed from U-section crossmembers. Formation of at least one crossmember includes forming a stack comprising at least one layer of resin film applied to a layer of dry fibers, pressing this stack to confer on it a U-section form and such as to compress the layers thereof, and pre-polymerization and/or polymerization of the resin of the stack. The manipulated fiber layers are layers of dry fibers, such that manipulation thereof by an automated machine may be effected for a reasonable cost and at a high throughput. Deposition of resin films carried by removable leaves, i.e., of which one of the faces is not adhesive, likewise facilitates manipulation by an automated installation.

Abstract: A device for measuring the accretion of ice on a studied surface. The device has two arms, a first arm and a second arm, the second arm forming an enclosure for housing an image acquisition system disposed to acquire, through an orifice, images of a part of the studied surface located on the first arm. The device thus makes it possible to dissociate the support of the image acquisition system from that of the studied surface on which ice accumulates. Consequently, it is possible to place the second arm in the direction of the flow of the stream of air flowing along the aircraft while the first arm passes through the stream.

Abstract: A controller for a hydraulic braking system for an aircraft is disclosed. The hydraulic braking system includes a first accumulator and a second accumulator, the controller configured to: receive first signals including first pressure data from a first pressure transducer associated with the first accumulator, receive second signals including second pressure data from a second pressure transducer associated with the second accumulator, monitor the received first and second signals to determine whether a predetermined condition has been met, and issue a warning indicating a loss of integrity of the hydraulic braking system in response to a determination that one or more predetermined conditions has been met. A hydraulic braking system for an aircraft and method to determine the integrity of a hydraulic braking system are also disclosed.