Abstract: A measurement system for measuring a dynamic deformation of an object, the measurement system comprising an optical fiber, the optical fiber extending at least partially into a tube that is configured to be secured to the object, the optical fiber having a measurement sector that is able to move inside the tube, the measurement sector comprising at least one Bragg grating. The measurement system comprises a non-Newtonian fluid filling at least one chamber delimited by the tube, the measurement sector extending into the at least one chamber, the non-Newtonian fluid being in contact with the tube and the measurement sector.

Abstract: The present disclosure relates to a reactor device (2) for converting powdered metal oxides, in particular metal oxides contained in regolith, to metal powder and molecular oxygen (O2), the reactor device (2) comprising a cathode reactor vessel (8) providing a receiving space (14) for the powdered metal oxides and adapted to be connected to an electron source (21) such that the powdered electrode oxides can be converted to the metal powder and oxygen ions (O2?) by the application of an electrical potential, and an anode reactor vessel (4) adapted to be connected to an electron sink (22) to attract the oxygen ions (O2?) travelling through an electrolyte (6) from the cathode reactor vessel (8) to the anode reactor vessel (4) during operation of the reactor device (2); wherein the anode reactor vessel (4) at least partially surrounds the cathode reactor vessel (8).

Abstract: An air directing arrangement for controlling flow of air at a compartment outlet of a fuselage of a rotorcraft. The air directing arrangement comprises a continuous surface that covers the compartment outlet outside the fuselage and forms a flow channel for directing an air flow at the compartment outlet; a first flow-through opening that is formed at a first position of the flow channel, wherein the first flow-through opening forms an air inlet area; and a second flow-through opening that is formed at a second position of the flow channel, wherein the second flow-through opening is arranged downstream of the first flow-through opening in the predetermined flow direction, and wherein the second flow-through opening forms an air outlet area; wherein the air inlet area is smaller than the air outlet area.

Abstract: A hatch locking device for an aircraft or spacecraft hatch, in particular for a cargo door, includes an actuation lever for actuating the hatch locking device which is rotatable about a pivot axis and includes a protruding section, a latch hinged rotatable about a hinge axis at a hatch frame and engageable with a corresponding latch counter part of a fuselage frame, and a connector mechanically connecting the protruding section and the latch so rotation of the actuation lever causes rotation of the latch. An aircraft or spacecraft hatch including such hatch locking device as well as an aircraft with such an aircraft or spacecraft hatch.

Abstract: An actuation system for a cargo door of an aircraft. The cargo door covers an opening into a cargo bay when it is in a closed position. The actuation system includes a first actuator configured to outwardly rotate the cargo door from the closed position to a first open position, and a second actuator configured to outwardly rotate the cargo door from the first open position to a second open position.

Abstract: A method for controlling a rotorcraft, the rotorcraft comprising at least two combustion engines, at least one regulation system and one transmission system, the at least two engines being mechanically connected to the transmission system respectively by at least two couplings. Such a control method comprises at least identifying an N2-regulated engine, identifying a non-N2?-regulated engine and generating a control setpoint limit for at least one first regulation system of the N2-regulated engine and depending on the speed of rotation N2 of at least one first output shaft of the N2-regulated engine.

Abstract: A sealant smoothing tool for smoothing sealant in a gap between two aircraft parts is disclosed including a main body having a base surface for abutting sliding along a top surface of the aircraft parts, a spatula holder for holding a spatula, the spatula holder being configured to movably mount the spatula relative to the main body, and a resilient biasing member, configured to provide a biasing against the spatula or the spatula holder, such that the spatula supplies a biasing force to the sealant. An aircraft having two parts sealed by the sealant smoothing tool, a kit of parts including a sealant smoothing tool and one or more spatulas, and a method of smoothing sealant to seal a gap between two aircraft parts are also disclosed.

Abstract: Two components of an aircraft structure are joined by providing a threaded opening in one of them and supporting an alignment insert in that opening. The alignment insert is used to guide drilling of the second component such that a hole is produced which is aligned with the threaded opening, for instance using an alignment projection which physically guides a drill. The alignment insert may then be removed. A fastener is then inserted through that hole and into the threaded opening, then tightened to form the completed joint.

Abstract: An aircraft wing, including a main wing and a trailing edge high lift assembly movably arranged at a main wing trailing edge, the high lift assembly including a flap and a connection assembly movably mounting the flap to the main wing, such that the flap is movable between retracted and extended positions. In the extended position, a gap is present between a main wing lower rear panel and a flap leading-edge section. In the retracted position, the gap is closed or minimized. The flap is movable between an extended position, a first retracted position, and a second retracted position where the flap is moved beyond the first retracted position in a forward direction, and the wing comprises a gap closing device configured to close or minimize the gap in both the first and second retracted positions of the flap, and to open the gap in the flap extended position.

Abstract: A actuator arrangement is disclosed in which the high-lift device support that supports and guides movement of a high-lift device, such as a flap, is in axial alignment with a control actuator assembly that controls one or more control surfaces. This allows a single support fairing to be sufficient for covering both the track member and the control actuator assembly and allowing for reduced drag and weight.

Abstract: A fastening system for an aircraft to fasten at least one tank to contain liquid hydrogen, allowing easy access to the tank. The fastening system includes a longitudinal box, upper formers fastened to the upper end of the longitudinal box and lower formers fastened to the lower end of the longitudinal box, at least two upper formers including two fastening devices to each connect a fastening point of the tank to an upper former, at least one lower former including two second fastening devices to each connect a second fastening point of the tank to the lower former. The fastening system allows an operator to access the tanks that are capable of being fastened by the fastening system.

Abstract: A mounting member configured to support a cabin component to be mounted to a mounting rail. The rail mounting arrangement comprises a disengagement locking mechanism that prevents a removal of the mounting member along a transversal direction of the mounting rail, while still allowing movement along the longitudinal direction. The rail mounting arrangement includes a securing mechanism that is configured to secure the mounting member at the desired location along the mounting rail.

Abstract: An aircraft wing section assembly is disclosed having a structural spine, a movement mechanism including a support rod 1 extending through the structural spine, a first lever, for connection to and for moving a first moveable control surface, pivotally mounted to the support rod, a second similar lever for connection to and for moving a second moveable control surface, and a connection mechanism for connecting the first and second levers such that pivotal movement of the first lever causes pivotal movement of the second lever, and an actuation mechanism for actuating pivotal movement of the first lever, such that, in use, when the actuation mechanism actuates pivotal movement of the first lever, the second lever also pivotally moves, thus causing movement of both the first and second moveable control surfaces. Also disclosed is an aircraft wing assembly, an aircraft and a method of operating an aircraft.

Abstract: A component includes at least a first sub-component and a second sub-component each fully or partially including metal or metal alloy material or having an at least partially metallized surface or surface region, the first sub-component and the second sub-component providing a pair of connection interfaces configured to establish a permanent connection of the first sub-component and the second sub-component, wherein at least one of the pair of connection interfaces comprises nanowires. The disclosure further provides a method for manufacturing such a component.

Abstract: A method for operating a water supply system for an aircraft, as well as a corresponding water supply system operating in accordance with the method and an aircraft having such water supply system. The method includes two operation sequences of a pump and a valve, each sequence including a time delay between operation of the pump and operation of the valve.

Abstract: A cradle for supporting an aircraft landing gear assembly is disclosed including a chassis for transporting the cradle and an arm movable between a stowed position and an elevated position with respect to the chassis. The arm has a set of clamps for securing the landing gear assembly to the cradle. In this way the landing gear assembly is held securely in the stowed position for storage and transport, and held securely in the elevated position for installation to an aircraft, such that damage to the landing gear assembly during transportation and installation is minimised.

Abstract: A method for assembling aircraft panels by welding improves the flexibility thereof. Panels are butted together along longitudinal joining lines and fixed to one another via their longitudinal edges by welding without the longitudinal ends of their welded edges being connected to one another. Longitudinal hoops are fixed to partially cover the concave surface of the panels at least partially at the ends. The absence of welding at the ends introduces the desired flexibility. The disclosure also covers the fuselage portions formed by assembling panels according to this method and the aircraft including such portions.

Abstract: A device for latching a door of an oxygen mask container in an aircraft cabin includes a door for an oxygen mask container having an inner side, outer side and hinge, a first latching device attached to the inner side, and a second latching device movable relative to the first latching device to selectively engage or disengage the second latching device. A retaining element is attachable to a structural part inside the oxygen mask container. A test control device on the inner side of the door includes a movable hook element and can move the hook element to a first or second position. The hook element can engage the retaining element in the first position to restrict an opening degree of the door. The hook element is placed in the second position such that when the door is opened, the hook element is moved past the retaining element.

Abstract: A method for transferring a spacecraft (10), such as an artificial satellite, from an initial elliptical orbit (30) to a final geostationary orbit (50), the spacecraft taking at least one intermediate elliptical orbit (40) propelled by electric propulsion means (12, 13), the method includes: when the spacecraft is in an intermediate orbit, a nominal thrust step (410) in which the propulsion means generate nominal thrust while the spacecraft is on at least part of a first orbital arc (41) passing through the apogee A of the intermediate orbit, and a minimum thrust step (420), in which the propulsion means are partly stopped or slowed while the spacecraft is on at least part (43) of a second orbital arc (42) passing through the perigee P of the intermediate orbit, the two orbital arcs being complementary.

Abstract: A ground service system that includes a ground service device and a connecting interface. The ground service device secures rotor blades of a multi-blade rotor of a rotary-wing aircraft in a non-operational mode of the rotary-wing aircraft, when the ground service device is attached to the connecting interface on the rotary-wing aircraft. The ground service device includes a rack with three struts and an attachment device that are releasably attachable to four receiver mounts of the connecting interface. The ground service device further includes clamps for releasably connecting the rotor blades with the four receiver mounts to secure the rotor blades in the non-operational mode of the rotary-wing aircraft.