Abstract: A method determines a thrust force of an aircraft engine that is attached to an aircraft by a force transferring element having a strain gauge for determining its strain state and a temperature sensor for measuring a surface temperature of the force transferring element adjacent to the strain gauge. The method includes: determining the surface temperature; determining a strain of the force transferring element; determining the strain state of the force transferring element based on the determined strain and compensating for temperature effects by taking into account the surface temperature, the compensation of the temperature effects taking into account both static and transient influences; and calculating the thrust force of the aircraft engine from the determined strain state.

Abstract: The invention concerns a communications system and a communications method and software for passengers in an aircraft. The aircraft comprises an aircraft-supported data-processing arrangement and at least one on-board communications interface for communication with a passenger appliance, the communications system being arranged to receive a passenger profile from the passenger appliance by means of the communications interface of the aircraft and transmitting it to the data-processing arrangement.

Abstract: A height-adjustable device has synchronously height-adjustable lifting devices each having a standing and lifting element, which are height-adjustable relative thereto. The height adjustment is configured to be carried out via pulling elements, formed by redirection devices, to raise the lifting element relative to the standing element. Each pulling element is secured in a non-positive or positive locking manner to lifting devices, and each are configured such that a lengthening in the region of the first lifting device brings about a synchronous shortening in the region of the second lifting device. Each pulling element is constructed to raise only the one lifting element relative to the standing element. The height-adjustable device has a locking device that locks the pulling elements by a non-positive or positive locking engagement on the corresponding one of the pulling elements. The locking device is constructed to synchronise the movement of the pulling elements.

Abstract: A data communication system has: a cabin module with a transmission and reception unit; and a furniture module, which is fastened in a furniture item anchored in a cabin, and has a transmission and reception unit. The transmission and reception units each have a controllable light source and a light sensor. The furniture module is disposed relative to the cabin module such that light emanating from the light source of the transmission and reception unit of the cabin module is detectable by the light sensor of the transmission and reception unit of the furniture module and light emanating from the light source of the transmission and reception unit of the furniture module is detectable by the light sensor of the transmission and reception unit the one cabin module.

Abstract: A device for cleaning the core engine of a jet engine includes a supply unit, which provides the cleaning medium, a nozzle unit, which is configured for feeding the cleaning medium into the core engine, and a line connection between the supply unit and the nozzle unit. The nozzle unit includes a means for the rotationally fixed connection to the fan shaft of the jet engine, and that a rotary coupling is provided between the nozzle unit and the line connection. The device may be arranged with a turbo fan jet engine. A method for cleaning, the core engine of a jet engine uses the device.

Abstract: Aircraft seat having a first seat element and a second seat element, the second seat element being mounted so as to be adjustable relative to the first seat element, a spring element that moves the second seat element relative to the first seat element being provided, it being possible for the force acting on the second seat element by the spring element to be released by an actuating element such that the spring element is deactivated in a first switching position of the actuating element, and the spring element is activated in a second switching position of the actuating element, where a force limitation element is provided, by which the force acting on the second seat element by the spring element can be limited to a predetermined value such that intermediate states between the first and the second switching positions can also be set.

Abstract: The invention relates to a floor connection assembly for the mechanical connection of an aircraft seat to a floor structure of an aircraft, comprising at least three fastening points, wherein the floor connection assembly can be fastened on at least three fastening points with in each case one fastening element to the floor structure. The floor connection assembly comprises an adapter plate, wherein the mechanical connection between the adapter plate and the fastening elements is supported about at least one axis in a substantially torque-free manner.

Abstract: The object of the invention is a device for cleaning the core engine of a jet engine, having a supply unit, which provides the cleaning medium, a nozzle unit, which is configured for feeding the cleaning medium into the core engine, and a line connection between the supply unit and the nozzle unit. The invention provides that the nozzle unit has a means for the rotationally fixed connection to the fan shaft of the jet engine, and that a rotary coupling is provided between the nozzle unit and the line connection. The object of the invention is further an arrangement of such a device and a turbo fan jet engine, and a method for cleaning the core engine of a jet engine using the device.

Abstract: A method for a position determination of a turbine blade of a high-pressure turbine stage of a gas turbine that is connected to a high-pressure compressor via a shaft, wherein each turbine blade of the high-pressure turbine is recorded on a record card with a relative position. The method includes: determining a position of a blade lock of a stage of the high-pressure compressor, where the stage is selected such that, when the gas turbine is mounted, the blade lock is brought into view of a boroscope, which is guided through a boroscope opening on the gas turbine by rotating the shaft, and so that the blade lock can be identified; and marking that turbine blade on the record card that is in view of a second boroscope, which is guided through a second boroscope opening on the gas turbine when the blade lock is in view of the boroscope.

Abstract: A flow element for fluidic contact with a hot gas flow inside an aircraft engine includes: a base material, which has a hot gas surface that faces the gas flow and a remote surface that is remote from the gas flow, the base material being completely surrounded by a chroming layer on the hot gas surface and on the remote surface; an adhesive layer on the chroming layer in first portions; an alitising layer, the alitising layer being arranged on the adhesive layer in the first portions; and a thermal barrier layer being arranged on the alitising layer in the first portions. The alitising layer is arranged on the chroming layer in second portions that do not have an adhesive layer, the chroming layer and the alitising layer forming a chroming-alitising layer in the second portions.

Abstract: Method for testing a temperature-compensated, pressure-gradient-controlled pressure switch, which is pneumatically associated with a primary pressure chamber and comprises a secondary pressure chamber for temperature compensation, wherein, by using at least one temperature-control apparatus between the primary pressure chamber and the secondary pressure chamber, a temperature gradient is set which is sufficiently great to produce a pressure gradient between the primary pressure chamber and the secondary pressure chamber that corresponds at least to the triggering pressure gradient of the pressure switch.

Abstract: A filter for binding constituents of a gas stream includes a supporting member and a filter layer applied to surfaces of the supporting member. The filter layer includes a component for the physisorption of constituents, a component for the chemisorption of constituents, and a component for dissolving oil constituents which comprises ionic liquids.

Abstract: The invention concerns a securing system for passenger appliances in an aircraft, the securing system comprising a retaining device which can be mounted on or in an aircraft seat. The retaining device comprises a connection device, the connection device being displaceable between a park position and a use position. The securing system has a portable mounting adapter, the mounting adapter having a connection arrangement, and the connection device and the connection arrangement being detachably and mechanically connectable to each other in load-bearing manner. The mounting adapter is arranged to be connected to the passenger appliance in load-bearing manner.

Abstract: A nozzle installation includes at least one nozzle configured for introducing cleaning media containing solids into a jet engine, and for a rotationally fixed connection to a shaft of a turbofan of a jet engine. The at least one nozzle has a swivel coupling to which a line connection is connectable. A flexible hose forms a connection of a nozzle-side outlet of the swivel coupling to an inlet of the at least one nozzle.

Abstract: The present invention relates to an aircraft seat having a seat base, a seat unit, and a floor attachment assembly, where a first side of the seat base is configured to be fastened to the seat unit, and a second side of the seat base is configured to be fastened to the floor attachment assembly, and the floor attachment assembly is configured to be mechanically connected to a floor structure of an aircraft in order to fasten the aircraft seat to the aircraft, where the seat base is formed by at least one flexurally rigid shell component, where the shell component has a cavity for receiving at least one functional element, with the cavity being closed.

Abstract: The invention relates to an aircraft seat comprising an adjusting device, the aircraft seat comprising at least one adjustable seat element. The seat element has an adjustable state and a locked state, the seat element being adjustable by means of manual force application and/or force application by a spring element and/or force application due to the weight of parts of the aircraft seat only in the adjustable state. The adjusting device comprises at least one control element and at least one locking element, the locking element being movable by means of the control element between a locking position in which the seat element is locked, and a neutral position in which the seat element is adjustable. The control element is an electronic and/or electric switch, and the locking element can be moved between the locking position and the neutral position by means of an electrically operated actuator which can be actuated by means of signals from the switch.

Abstract: An aircraft having at least two aero engines is provided with an air diverter configured to divert bleed air from the aero engines in order to supply air to an air-conditioning system of an aircraft cabin; an air-quality sensor configured to monitor air quality of the bleed air diverted from at least one of the aero engines and, on detection of pollution, to transmit a signal; and an indicator configured to display an indication depending on the signal transmitted from the air-quality sensor.

Abstract: Visible built-in component for the interior fittings of an aircraft, comprising a partially transparent stone layer or glass layer and a luminous layer arranged thereunder for backlighting the stone layer or glass layer, wherein the luminous layer comprises a plurality of luminous strips and a partially transparent intermediate layer is provided between the luminous layer and the stone layer or glass layer.

Abstract: Authentication method and corresponding software for a passenger of an aircraft of an airline, wherein a data processing apparatus of the airline generates flight-specific authentication data for the use of an on-board communication device, and the authentication data are transmitted to a portable passenger device of the passenger by means of a communication network. The authentication data allow the authentication of the passenger device by wirelessly transmitting the authentication data to the onboard communication device.

Abstract: The invention relates to a floor attachment assembly for mechanically connecting two aircraft seats to a floor structure of an aircraft, which assembly comprises four attachment points. The floor attachment assembly can be attached to the floor structure by means of one attachment element in each case at the four attachment points. The floor attachment assembly comprises two adapter plates, the two adapter plates being interconnected by means of a connection element. The mechanical connection between at least one of the adapter plates and at least one of the attachment elements is movable along at least one axis. Furthermore, the invention relates to a corresponding aircraft seat.