Abstract: An assist device for ensuring the accuracy and integrity of position information of an aircraft on the ground includes a processing unit for determining in the airport (AE) a zone (ZP) of insensitivity to multipath GPS signals, the zone (ZP) having a rectangular shape, which is determined relative to the threshold (O) of the runway, and which has a length (L1) equal to the length of the runway and a width (L2) depending on a maximum illumination distance (D). The device further includes a unit for verifying, while the aircraft is moving in the airport (AE), whether the position relative to position information of the aircraft is inside said runway zone (ZP). A method for ensuring the accuracy and integrity of position information of an aircraft on the ground is also disclosed herein.

Abstract: The disclosed embodiments concern an aircraft fuselage section made of composite material with an internal skeleton having frames that form the radial structure of the fuselage and stringers that form the longitudinal structure of said fuselage, and a skin made of composite material, surrounding the internal skeleton, with said skin having an evolving thickness along a longitudinal axis X, with an approximately constant, regular interior profile. The disclosed embodiments also concern a process for manufacturing the skin of an aircraft fuselage section made of composite material, having a draping operation for strips of fibers precoated with resin around a mold, with the number of strips of fibers varying longitudinally depending on the area of the fuselage being considered so as to create a skin with an evolving thickness.

Abstract: A fuselage element including a first fuselage segment including a skin, and a junction device for connecting the first segment to a second adjacent fuselage segment is disclosed. The first segment extending along the longitudinal axis of the fuselage element includes stiffening elements extending along the axis. The end of at least one stiffening element extends beyond a free edge of the skin by a predetermined length.

Abstract: A bridging seal comprising a stack of two or more layers of elastomer, the bridging seal having a first edge and a second edge opposite the first edge, adjacent layers being attached to each other at the first and second edges, wherein adjacent layers of the bridging seal have opposing surfaces and a substantial portion of the opposing surfaces is unbonded. The bridging seal may be used to seal a gap between two aerodynamic surfaces on an aircraft.

Abstract: A method and device for accessing maintenance functions of an aircraft from a mobile maintenance terminal. First, the situation of the aircraft is determined. Then, if this situation allows a mobile maintenance terminal to access a maintenance information system on the ground and the information system of the aircraft, a connection is established between the mobile maintenance terminal and the maintenance information system on the ground and at least one maintenance command intended for the information system of the aircraft is transmitted to the maintenance information system on the ground. If this situation allows the mobile maintenance terminal to access only the information system of the aircraft, a connection is established between the mobile maintenance terminal and the information system of the aircraft and at least one maintenance command is transmitted to the information system of the aircraft.

Abstract: The invention relates to a fuselage of an air- or spacecraft. The fuselage comprises at least one shell element and one insulation element. The insulation element is configured as a passive, watertight insulation element and can be mounted on an inner side in a completely air- and watertight manner. The invention furthermore relates to a respective aircraft or spacecraft.

Abstract: The present invention provides a method for controlling an internal pressure in an aircraft or spacecraft, the method comprising the following steps: detecting the internal pressure in the craft and an external pressure Pa outside of the craft and comparing said pressures with each other; and adjusting a flap of at least one outflow valve to a blade position, in which the flap directs air flowing past an outer surface of the craft into the craft to increase the internal pressure, if the external pressure exceeds the internal pressure by a predetermined value during the descent of the craft. The idea, on which the present invention is based, is to assign a double function to the outflow valve: during normal flight the positive pressure in the craft is relieved by means of the outflow valve.

Abstract: The device comprises servocontrol means which automatically control, in a combined manner, an automatic thrust system of the aircraft and airbrakes of the aircraft, as a supplement to usual means for steering the vertical trajectory, so that the aircraft attains a speed setpoint and/or altitude setpoint, at the location defined by a geographical constraint.

Abstract: A method and device for providing a pilot warning signal is provided, where such method can include providing a first signal to indicate a pedal angle of a pedal, providing a second signal which is directly dynamically dependent on the pedal angle, pairing up values of the first signal and the second signal at specific times, determining an angle change of the pairs of values and an increment of the pairs of values at two successive times, and generating the pilot warning signal when actuation of the pedal and a stimulated tumbling movement of the aircraft are ascertained and if the determined angle change of the pairs of values is greater than a first threshold value or the determined angle change of the increment of the pairs of values is greater than a second threshold value. A computer program product and a warning device are also provided.

Abstract: A device for defrosting a leading edge of an aircraft, includes at least one opening (52) for ejecting hot air, a pipe (56) for directing the hot air from a power plant to the ejection opening (52), and elements (58) for measuring the pressure inside the pipe (56), characterized in that the pipe (56) includes at least one cross-section reduction called a chokepoint (62) upstream from the elements (58) for measuring pressure.

Abstract: An aircraft fuel system including a fuel line for carrying liquid fuel, and a microwave energy transmitter for energizing water carried in the fuel line. Also, a method of suppressing ice formation in an aircraft fuel system, the fuel system including a fuel line carrying liquid fuel, and a microwave energy transmitter, the method comprising transmitting microwaves along the fuel line to energize water carried with the fuel in the fuel line.

Abstract: An aircraft refuelling system of an aircraft is provided. The refuelling system comprises a refuelling connector (34) mounted as part of the aircraft and configured to detachably connect to the fuel outlet (2) of a fuel supply apparatus separate from the aircraft, and a fuel pressure regulator (36) having an inlet in communication with a fuel inlet (35) of the refuelling connector (34) and having an outlet in communication with refuelling pipework (39) of the aircraft. The fuel pressure regulator (36), regulates the pressure of fuel in the refuelling pipework (39) when fuel is being passed into the refuelling pipework (39) from the fuel inlet (35) of the refuelling connector.

Abstract: A method and computer program product for planning a landing approach of an aircraft based on an actual position or first nominal position of the aircraft during its approach for landing on a runway, including providing a stabilization flight path section and stabilization region and/or stabilization point defined by an altitude profile by at least one configuration change point in the stabilization flight path section with a change of the overall profile configuration of the airfoils and with a predetermined final approach flight status of the aircraft, and checking or changing position of the at least one configuration change measure in a change and/or the addition of an additional configuration change measure to the stabilization flight path section and by changing a speed profile along the stabilization flight path section so that the aircraft reaches the predetermined final approach flight status in the stabilization region or at the stabilization point.

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.

Abstract: A method and a system for monitoring the operational state of a pump including acquiring a set characteristic diagram of the pump, the characteristic diagram of the pump being defined by a functional relationship between a first pump operating parameter characteristic of the operational state of the pump and a second pump operating parameter characteristic of the operational state of the pump. Subsequently, an actual characteristic diagram of the pump is acquired when the pump is installed in a higher-level system, in particular an aircraft system, and is running. Finally, the actual characteristic diagram of the pump is compared with the set characteristic diagram of the pump.

Abstract: A Sandwich panel with a core structure, in particular with a honeycomb-shaped core structure, and plane-parallel cover layers applied to both sides of this core structure, to form a floor surface in a fuselage airframe of an aircraft, the core structure having at least one recess into which at least one reinforcing structure is integrated, wherein the at least one reinforcing structure is formed with at least one core, said core having at least one recess into which a stopper is introduced, into which at least one attachment element can be introduced to attach at least one further component to the sandwich panel, and a plurality of prepreg strips which each have a uniform fibre running direction being wound around the core. In addition, the invention relates to a method for the production of a sandwich panel according to the invention.

Abstract: A control unit and a method for controlling a wireless data transmission between a wireless terminal and access points of a communications network in a transportation device, as well as a computer program for executing the method. The wireless terminal is assigned to two or more of the access points in such a way that one communications channel is available between the wireless terminal and the access points for wireless data transmission between the wireless terminal and the access points. A control unit is used, in the case of transmission from the access points towards the wireless terminal, to select at least one of the access points for wireless transmission to the terminal and/or in the case of transmission from the terminal towards the access points, to determine a message for further use in the communications network based on the messages received from the terminal by the access points.

Abstract: An assembly comprising at least two non-metal components which are fixed to each other using at least one fixing system. The fixing system includes a fixing device with a fixing element which is provided with a head and a rod, and a crimping ring which is in contact with one of the components. A protection device is a part of the fixing system which delimits a cavity for confining gas around a portion of the device comprising the crimping ring. In order to improve the repeatability of the operation for positioning the protection device, a guiding device is provided which includes an assembly element on the portion of the fixing device, and an element for guiding the protection device.

Abstract: A method for manufacturing a tool equipment used in molding a panel for a fuselage of an aircraft from a composite material is provided. The method includes manufacturing a mold such that a fixed part includes a hub and an intermediary member. A plurality of removable modules which are able to be mounted on this fixed part are also manufactured and then fastened to the fixed part so as to modify an external surface upon which composite material is laid-up or draped during the molding of the panel.

Abstract: The invention relates to a membrane. Partly permeable membranes often have holes or perforations having a specific diameter to allow substances having a smaller particle diameter to pass through, but to hold back substances having a larger particle diameter. Such membranes are subject to wear primarily at the holes, i.e. cracks form which grow through the membrane proceeding from a hole. Particularly in the case of micromechanical membranes having holes having a small diameter in the range of 1 ?m or less, it is very difficult to detect the state of the membrane, in particular whether the latter has cracks. Membranes having cracks can then undesirably allow passage even of those particles which should actually be held back. In medical or hygienic applications, the function can then be impaired.