Abstract: A heat exchanger with at least one cooling segment having a first, a second, and a third portion. A first heat carrier flow path, through which a first heat carrier medium flows, extends through the first portion. A second heat carrier flow path, through which a second heat carrier medium flows, extends through the second portion. A first coolant flow path, through which a first coolant medium flows, extends through the third portion. The heat exchanger comprises at least one cooling body, a second coolant medium flowing through a second coolant flow path extending through the cooling body. The first and the second heat carrier flow paths are thermally coupled, respectively, to the first and the second coolant flow path, to discharge heat energy of at least one of the first and the second heat carrier medium to at least one of the first and the second coolant medium.

Abstract: A measuring device for an aircraft is provided in order to determine physical properties of aerosol particles in real time. The device includes a heating device that separates volatile and solid aerosol particles, and a particle sensor that measures acquired data. The physical properties of the solid aerosol particles are determined with an analyzer. The determined analytical data is forwarded to other internal aircraft systems via a communication interface. Due to the formation of a measuring data or analytical data network with several airliners equipped with the measuring device, accurate and up-to-date information on the particle pollution, for example, along flight paths, can be obtained and used for defining no-fly zones, if so required.

Abstract: The invention relates to an aircraft protection device for protecting potentially exposed aircraft structures from direct impacts and a method of protecting an exposed edge of an aircraft component. The method includes the steps of winding filament around a foam core to create an impact protection device. A portion of the filament winding and foam core is removed from the impact protection device to create a receiving section whereby the receiving section is configured to correspond to and receive the exposed edge of the aircraft component. The impact protection device is secured to the exposed edge of the aircraft component such that the exposed edge is received in the receiving portion of the impact protection device.

Abstract: A holding device for attaching at least one fixture to a fuselage cell structure of an aircraft, includes a basic element attached to the fuselage cell structure, to which at least one fixture element to accommodate the fixture is fastened, wherein the basic element is embodied as a hook-and-loop element, the hook-and-loop bristles of which co-act with corresponding hook-and-loop bristles of at least one fixture element, which is also embodied as a hook-and-loop element thus forming a hook-and-loop connection, wherein the space between the interengaging hook-and-loop bristles is filled with an adhesive.

Abstract: A device for determining ageing of a hydraulic fluid in a hydraulic system with a multitude of hydraulic components is provided. The device comprises at least one temperature determination device and at least one ageing determination device, wherein the temperature determination device determines the respective temperature of each discrete fluid volume of the hydraulic fluid in the hydraulic system, and from the aforesaid the ageing determination device determines an increase in ageing. Generally, the temperature determination device carries out a numerical thermal simulation of the hydraulic system, component by component, including determining at least one temperature of at least one hydraulic component of the hydraulic system, which simulation is supported by measuring the temperatures of individual hydraulic components by means of temperature sensors.

Abstract: A process for measuring the through stress distribution (12) in a workpiece (10) by taking progressive cuts (14, 16) and measuring the deflection of the workpiece at the cut point.

Abstract: A silencer for an auxiliary power unit of an aircraft includes an inlet, an outlet, a housing, and a flow channel of a porous material, arranged in the housing. Between the housing and the flow channel an intermediate space is created, which space is divided by at least one outer partition into outer cells arranged around the flow channel. A central body includes a casing that is permeable to gas at least in some regions and that is arranged in the interior of the silencer. The central body includes inner partitions dividing the central body into inner cells. The resonance frequency of the inner cells corresponds to the natural frequency of the first radial mode in a channel formed between the central body and the inner surface of the inlet. In this manner particularly good sound attenuation is achieved with a compact installation space of a silencer.

Abstract: A ventilation system for an avionics bay has two strut assemblies for stiffening the floor of the cockpit, each strut assembly being arranged symmetrically regarding to the central plane of the aircraft, and means of distribution of the blowing air in the cabinets of the bay from the strut assemblies. The extraction circuit includes exhaust ducts integrated in the cabinets and couples together by tight inter-cabinets junctions in an overall configuration of maximized compactness.

Abstract: An aircraft fuselage includes at least one opening that can be closed by a flap or door, which comes to abut against at least one door stopper that is arranged on a fuselage-side door frame bulkhead and transfers the impact forces into an intermediate costal for diversion into an aircraft structure that encompasses bulkheads, wherein the door frame bulkhead exhibits an opening, through which an impact section of the door stopper extends, wherein a fastening plate section adjoining the latter comes to abut the rear side of the door frame bulkhead, which interacts with means for directly introducing the impact forces from the door stopper into the intermediate costal.

Abstract: A method for guiding an aircraft during its final approach to a landing runway, whereby the aircraft is guided during its approach by aircraft position information obtained from an GNSS satellite navigation system, wherein: prior to the start of the final approach a first time tFAF is determined corresponding with the start of said final approach and a second time tTD corresponding with the landing of the aircraft on said runway, then a set of satellites is determined of the satellite navigation system for excluding from the calculation of said aircraft position information during at least a part of the time interval comprised between said first and second times; and during the final approach, the aircraft position information is determined while excluding the information corresponding with all the satellites of said set of satellites and the aircraft is guided along its final approach path by said position information.

Abstract: A cable raceway support device for an aircraft, formed from an electrically conductive material, comprising a pedestal having a fastening plane for the fastening of the device onto a primary structure and also having, on a support face which is an opposite face to the fastening plane, at least one pair of jaws having at least one electrical contact enabling a sliding electrical contact to be formed and the support face has a contact that projects, and also has a jaw overhanging the support face, the jaw forming with part of the pedestal the pair of jaws forming a stirrup-shaped clamp comprising a base and two branches, one branch of the clamp merging with the pedestal, and the other branch of the clamp corresponding to the jaw and bearing a second contact facing the first contact.

Abstract: A method of lifting an aircraft at a lifting location, the method comprising: securing a fitting to the aircraft when the aircraft is at the lifting location; engaging the fitting with a crane hook; transmitting lifting load from the crane hook to the aircraft via the fitting; and removing the fitting from the aircraft. A fitting for transmitting lifting loads from a crane hook to an item, the fitting comprising: an attachment member configured to be secured to the item; and a lifting member which is pivotally coupled to the attachment member and configured to be engaged by the crane hook so as to transmit lifting loads from the crane hook to the item. A crane hook with a ball-and-socket connection is provided.

Abstract: A machining method for machining a superficial portion of a laminate using machine tool having a depth limiter which restricts a maximum depth of the machine tool. A guide frame having an inner guide contour restricts a maximum dimension of the superficial portion, and is secured over the superficial portion. The superficial portion is machined while the machine tool is guided by the guide contour. From another point of view, a machining apparatus for machining a superficial portion of a material is provided. The machining apparatus comprises a guide frame, an inner guide contour for guiding a machine tool, an attachment member for securing the guide frame to an attachment member, adjacent to the superficial portion, of the material.