Abstract: Embodiments relate to aircraft arresting systems that use a net or a cable that extends across a section of a runway. Ends of the net or cable are secured to an elongated tape, which is secured to and forms a part of an energy absorbing brake system. The elongated tape is secured around a tape reel and is allowed to reel out (or “pay out”) once the aircraft is engaged. Described is a system for adjusting the height of the tape such that its elevation can be altered between the point at which it leaves the energy absorbing brake system and when it reaches the aircraft runway.

Abstract: An aircraft undercarriage having a leg for mounting to move on an aircraft structure between a deployed position and a retracted position is provided. The undercarriage generally includes a brace member arranged between the structure of the aircraft and the leg in order to stabilize the leg in the deployed position, and a drive actuator for moving the leg from the deployed position to the retracted position. The brace member includes a strut arm having a proximal end that is designed to be hinged on the structure of the aircraft. The arm presents a longitudinal slot extending until the slot reaches a distal end in order to terminate in a bend and having slidably engaged therein a finger that is secured to the leg, the drive actuator being coupled to the strut arm.

Abstract: The invention relates to a device (1) for ejecting a parachute, comprising a housing (2) with an ejection opening (3), wherein the housing (2) is suitable for at least partially accommodating the parachute. In order to enable a robust and repeated ejection of the parachute with a low weight of the device (1), according to the invention a movable base (4) is arranged within the housing (2), which base (4) is connected to the housing (2) via at least one spring element, wherein the base (4) can be releasably fixed in place within the housing (2) using a fixing means (5), wherein the device (1) is configured such that if a parachute is arranged within the housing (2), the base (4) is accelerated by the spring element when the fixing means (5) is released, so that the parachute is ejected through the ejection opening (3) by means of the base (4). Furthermore, the invention relates to a method for ejecting a parachute.

Abstract: An aircraft wing has a flap arrangement with an inboard flap configured to move in a chordwise extension direction relative to the wing, the inboard flap having an outboard side, and an outboard flap adjacent to the inboard flap and configured to move in the chordwise extension direction relative to the wing, the outboard flap including an inboard side. A flap interconnect between the inboard flap and outboard flap has a roller mounted to a pin extending from the outboard side of the inboard flap and a guide track extending from the inboard side of the outboard flap. The guide track engages the roller on the inboard flap to limit deflection of the outboard flap relative to the inboard flap during movement of the inboard flap in the chordwise extension direction and movement of the outboard flap in the chordwise extension direction, to provide relative alignment of the inboard flap and outboard flap.

Abstract: The disclosure relates to an arrangement comprising a flyable unmanned transporting device and a movable catch arm, which is provided at a ground station, for holding the transporting device at the ground station, wherein at least one recess is provided on the transporting device, and the catch arm, at its end facing away from the ground station, has at least one expansion element which can be introduced into the at least one recess and, in the introduced state, can be expanded in order to produce a form fit between the at least one recess and the at least one expansion element.

Abstract: Device and method for reducing gust loads acting on control surfaces of an aircraft. Each control surface is movable by at least one actuator, and a flight control system provides reference variables Xsoll and {dot over (X)}soll to actuate the actuator of each control surface. Xsoll indicates a target position, force, or moment of the actuator, and {dot over (X)}soll indicates a time derivative of Xsoll. The device includes: a first sensor system identifying a position, force, or moment, indicated by variable Fext,Boe, as produced by gusts acting from outside on the control surface; and a regulator regulating the actuator of the control surface based on Fext,Boe, Xsoll and {dot over (X)}soll, and XA and {dot over (X)}A, resulting from the actuator acting on the control surface and detected by a second sensor system, wherein regulation of the actuator by the regulator enables compensation of the position, force, or moment produced by gusts acting on the control surface.

Abstract: An ice-breaking system for an aircraft, comprising a pneumatic ice-breaking device, an air inlet adapted to receive air from the environment outside the aircraft and an air outlet adapted to discharge air into the outside environment, and a motorized valve having an air loading port connected to the air inlet and an air discharge port connected to the air outlet, the valve being configured to supply air to the pneumatic ice-breaking device in a pulsating way. When the aircraft is in motion, the kinetic energy of the air at the air inlet and originating from the relative motion between the air and the aircraft is converted into air pressure at the pneumatic ice-breaking device, and the air outlet is positioned so that when the aircraft is in motion the air pressure at the air outlet is lower than the outside ambient pressure.

Abstract: A wing (5) for an aircraft (1) and include a fixed wing (7), a high lift system (9) including a high lift surface (27) movably mounted to the fixed wing (7), and a high lift actuation system (29) for moving the high lift surface (27) relative to the fixed wing (7) between a retracted position and at least one deployed position, a foldable wing tip portion (11) mounted to the fixed wing (7) pivotally about an axis of rotation (35) between an extended position and a folded position, a tip actuation unit (13) for moving the foldable wing tip portion (11) between the extended position and the folded position.

Abstract: An adjustable shape kite has a wing of a flexible material and an adjustable bridle system. The wing is a single layer wing that does not include structural support to provide its shape during flight. The bridle system is adjustable to adjust the wing curvature during flight. An aerodynamic shape is formed in the wing with a leading edge and side edges being rolled over by oncoming wind acting against the wing in conjunction with tensile forces acting thereon by the bridle lines of the bridle system.

Abstract: A pilot's seat offering an evacuation device. The seat comprises a ladder fixed to the rear of the back and covered by a detachable cover associated with the seat and deployable between a storage position retracted inside the cover and a deployed evacuation position, in which case the cover is detached. Thus, the evacuation device is incorporated harmoniously into the seat which offers a solid base for the evacuation ladder.

Abstract: An aircraft wing (10) comprising a fixed wing (14) and a movable wing tip device (12). The wing tip device is movable between a flight configuration and a ground configuration, whereby in the ground configuration the span of the wing is reduced compared to the flight configuration. A locking mechanism (30) is provided to lock the wing tip device in the flight configuration, the locking mechanism includes a receiving socket (34) with a first latch and a second latch, and a locking pin (32). In the locked configuration, the locking pin is inserted into the receiving socket such that the first latch and second latch prevents removal of the locking pin from the receiving socket.

Abstract: The present invention relates to a projectile including a body having a longitudinal axis and an intermediate portion comprising a wing or fin deployment device including at least a number N, at least equal to three, of wings or fins able to be deployed, the deployment method comprising at least two phases, a first deployment phase in which each wing or fin switches from a position tangential to the body of the projectile and parallel to the longitudinal axis to a semi-deployed position, and a second deployment phase with the switching of each wing from the semi-deployed position to a deployed position in which it is perpendicular to the body of the projectile, said wing deployment device is configured to synchronize the deployment of wings or fins in the second phase.

Abstract: A spacecraft docking system and method thereof are provided. The system comprises an active docking device and a passive docking device. The active docking device comprises an active docking ring and a docking frame. The active docking device further comprises three sets of buffer mechanisms, each set of the buffer mechanisms comprises a main buffer, two screw nut assemblies, and a self-difference buffer. An upper end and a lower end of the screw nut assembly are movably connected to the active docking ring and the docking frame, respectively. The two screw nut assemblies in each set are simultaneously driven and stretched by the main buffer, being also connected to each other through the self-difference buffer, and able to be relatively adjusted and stretched through the self-difference buffer.

Abstract: In order to be able to reduce the time and cost required for final assembly of an aircraft, a junction rib designed for the wing-central wingbox junction comprises a central web and an upper flange and a lower flange which extend from the main web, on a first side, the main web having a junction surface arranged on a second side opposite the first side, the main web including rows of orifices opening on the second side in the junction surface and on the first side, comprising a first row of orifices and a third row of orifices formed in an upper part of the main web on either side of the upper flange, and a second row of orifices formed in a lower portion of the main web, each one of the rows of orifices comprising orifices in a free state.

Abstract: An aircraft operable between a deployed position and a stowed position is disclosed. The aircraft includes a fuselage, a pair of wing segments, and a translation and rotation mechanism for attaching the wing segments to the fuselage. The mechanism includes an upper assembly having an outer shaft and an inner shaft. A first wing segment is attached to the outer shaft and a second wing segment is attached to the inner shaft. The outer shaft translates downward with respect to the inner shaft. Thereafter, the outer and inner shafts rotate in opposite directions in order to rotate the wing segments on top of one another, parallel to a long axis of the fuselage, and into the stowed position. The operation of the outer and inner shafts is reversed in order to return the wing segments to the deployed position.

Abstract: A spoiler mechanism for an aircraft includes a spoiler fore-section and a spoiler aft-section. The spoiler fore-section includes a forward end configured to couple to a wing structure of an aircraft and a hinge end. The hinge end includes a first hinge coupling and a first retainer portion. The spoiler aft-section includes a second retainer portion and a second hinge coupling coupled to the first hinge coupling of the spoiler fore-section. The first retainer portion and the second retainer portion are configured to engage one another when the spoiler aft-section is aligned with the spoiler fore-section, and the first retainer portion and the second retainer portion are configured to disengage from one another responsive to the spoiler aft-section pivoting upward relative to the spoiler fore-section.