Abstract: An aircraft cabin section includes a door frame, which forms a door opening, a passenger door, which is arranged on the door frame and is configured to close the door opening, and a door insulation arrangement, which is larger in at least one direction than the door opening. The door insulation arrangement is produced from a textile which is heat-insulating and/or airflow-inhibiting. Furthermore, a corresponding door insulation arrangement and an aircraft having such an aircraft cabin section or such a door insulation arrangement are disclosed.

Abstract: An electrothermal ice protection system (IPS) installed on an aircraft includes a sensor, a parting strip assembly, and a controller. The sensor monitors a direction of a local incident airflow that is imparted on the sensor. The parting strip assembly is coupled to the critical surface and includes a plurality of heating sections. The controller is in signal communication with the sensor and the parting strip assembly. The controller determines a direction of surface airflow incident on a critical surface of the aircraft based on the local incident airflow and selectively concentrates power to at least one targeted heating section among the plurality of heating sections with respect to non-targeted heating sections among the plurality of heating sections based on the direction of the surface airflow.

Abstract: A fixed-wing cargo aircraft having a kinked fuselage to extend the useable length of a continuous interior cargo bay while still meeting a tailstrike requirement is disclosed. The fuselage defines a continuous interior cargo bay along a majority of its length and a pitch axis about which the cargo aircraft rotates during takeoff while still on the ground. The fuselage includes a forward portion defining longitudinal-lateral plane of the cargo aircraft an aft portion extending aft from the pitch axis to the aft end and containing an aft region of the continuous interior cargo bay that extends along a majority of a length of the aft portion. The aft portion has a centerline extending above the forward upper surface of the aircraft.

Abstract: An aircraft comprises a hydrogen-fuelled propulsion system, a plurality of like generally cylindrical hydrogen storage tanks and a conveying system arranged to convey hydrogen from the hydrogen storage tanks to the hydrogen-fuelled propulsion system. The aircraft further comprises a fuselage having a cargo bay (502) including one or more (510A-G) of the plurality of hydrogen storage tanks, the longitudinal axes (511A-G) of the one or more hydrogen storage tanks within the cargo bay extending parallel to the longitudinal axis (501) of the fuselage and lying in one or more planes (595, 597) extending across the width dimension of the cargo bay. The hydrogen storage tanks within the cargo bay have a common aspect ratio R in the range 4.2?R?25.7, allowing the volume of space with the cargo bay occupied by stored hydrogen to be maximised or approximately maximised.

Abstract: Airstair systems and associated methods are disclosed. In one embodiment, the airstair has a deployable upper step, a primary deployment device and a secondary deployment device. The upper step is movable between a stowed configuration when a door of the aircraft is closed and a deployed configuration when the door is open. The primary deployment device resiliently biases the upper step toward the deployed configuration. The secondary deployment device is movable in coordination with a movement of the door and configured to drive the deployable upper step toward the deployed configuration during opening of the door and during a failure of the primary deployment device.

Abstract: An aft pivot assembly includes a height adjustment mechanism integrated into a device for mounting a payload, to enable release of the payload. The aft pivot assembly releasably secures an aft portion of the payload, such a pod, store, ordinance, or fuel tank. The aft pivot assembly includes a shaft operable with the mount device and a release component, the shaft being rotatable about multiple shaft axes relative to the mount device so as to either minimize or eliminate carriage loads about the aft portion, while reacting jettison loads during a jettison event or phase. The rotation of the shaft about its shaft axes can further be limited via a limit device. As the payload transitions from a carriage phase to a jettison phase, the shaft moves in multiple degrees of freedom and in multiple axes relative to the mount device.

Abstract: A fuel pump system for an aerial refueling system including: a variable displacement motor operable to be driven by a hydraulic fluid pressure; a fuel pump operable to be driven by the variable displacement motor; and a drive system controller (DSC) connected to the variable displacement motor, wherein the DSC is operable to direct an operation of the fuel pump in modes comprising: a flow control mode operable to maintain an output fuel flow rate from the fuel pump to a predetermined maximum inlet pressure at a reception coupling for a receiver aircraft; a fuel pressure control mode operable to regulate the output fuel flow rate to not exceed the predetermined maximum inlet pressure; and a priority mode operable to reduce the output fuel flow rate in response to a decrease in the hydraulic pressure. Also a method of refueling a receiver aircraft.

Abstract: A method may include receiving, via a processor, an ejection initiation signal indicating an ejection event for an ejection seat of an aircraft has been initiated; commanding, via the processor, a retraction mechanism to retract a cuff assembly towards a seat back of the ejection seat in response to the ejection initiation signal; and commanding, via the processor, a guillotine to sever a cord coupled to the cuff assembly.

Abstract: Aircraft door (1) having an inside door opening lever (6) coupled to a vent flap (5) by a conditional opening mechanism having two modes and including a flap stop (20) to cooperate with a stop surface (21). The stop (20) has a first trajectory, the stop surface (21) being arranged outside this first trajectory of the flap stop (20). The stop (20) has a second trajectory, the stop surface (21) being arranged on this second trajectory of the flap stop (20).

Abstract: Methods of assembling an aircraft wing includes adhering fuel dams to stringers and adhering the fuel dams to ribs. Fuel dams include a fuel-dam body that defines a channel shaped to receive a portion of a stringer of an aircraft wing. The fuel-dam body includes a stringer adherent surface, a rib adherent surface, and a pair of spaced-apart flanges extending from the rib adherent surface and positioned to project from the rib adherent surface on opposing sides of a notch of a rib.

Abstract: An assembly for an interior of a vehicle with the assembly having a monument wall configured to mount to the interior of the vehicle. A panel is configured to mount to an overhead support structure adjacent to the monument wall. The panel includes a front side configured to face into the interior of the vehicle and an opposing back side. One or more latch assemblies are configured to connect the panel to the overhead support structure adjacent to the monument wall. The latch assemblies include a latch mounted to the back side of the panel, a track with one or more rails, a follower with an arm and a head with the head sized to engage with the track, and a pull mechanism to unlock the latch.

Abstract: A stringer runout configuration has a pair of fittings with each fitting having a fitting web that is configured for attachment to a stringer web of a stringer on opposite sides of a terminating end of the stringer. The stringer web has a terminating end with a curved configuration and base flanges with rounded terminating ends. Each fitting has a base flange that has a bottom surface with a first surface area and a second surface area positioned at different heights. The first surface area of each of the fittings is configured for attachment to a stringer base flange on opposite sides of a terminating end of the stringer. The second surface area of each of the fittings is configured for attachment to a composite panel surface adjacent the terminating end of the stringer. These and other detailed design features described herein enhance the capability of the runout configuration.

Abstract: An air direction arrangement for an aircraft. The air direction arrangement contains an inlet opening and an inlet channel connected thereto and which is at least partially surrounded by an outer wall. The inlet channel is configured to guide air to an engine of the aircraft. The outer wall contains at least one outlet channel and at least one outlet element. The outlet element is configured to selectively release or close the outlet channel for an air flow from the inlet channel into the environment of the aircraft. The air direction arrangement contains a heat exchanger in the outlet channel to discharge thermal energy to the air flow which is flowing from the inlet channel into the environment of the aircraft.

Abstract: An aerial resupply system (ARS) including a supply aircraft. The supply aircraft includes at least one of supply fuel, an ordinance, and data. The supply aircraft also includes a retractable boom system (RBS) configured for selective stowage within a fuselage of the supply aircraft and configured to supply at least one of supply fuel, the ordinance, and data to a location external to the fuselage.

Abstract: The present disclosure provides an aircraft door system including an aircraft door configured to translate from a closed position to an open position. The aircraft door system further includes a plurality of door pressure stops positioned along a length of the aircraft door and a handle coupled to the aircraft door. A rotation of the handle causes a first translation of the aircraft door in an inward direction and a forward direction. The aircraft door system further includes a hinge system coupled to the aircraft door. An outward force applied to the aircraft door causes a second translation of the aircraft door in an outward direction and a forward direction. The hinge system causes the aircraft door to translate such that the aircraft door remains parallel to the aircraft fuselage throughout an entirety of the second translation until the aircraft door reaches the open position.

Abstract: A passenger furniture device for a passenger seat provided within a vehicle cabin, in particular an aircraft cabin, including at least a base element having at least an upper utility surface for a passenger, a removable section element which is mounted to one side of the base element, and a simple latch mechanism. In particular, the latch mechanism may be a simple plug-in and clip device. The latch mechanism is an easy to handle releasable attachment and fixation device to release the removable section from the base element, particularly only by crew and service members of the aircraft. The latch mechanism is provided on the base element and the section element such that the section element is detachably mounted to the base element via the latch mechanism.

Abstract: An aircraft door mechanism includes an aircraft structure (14) delimiting an opening (24); an aircraft door (26) movable between a position closing off the opening (24) and a released position of the opening (24); and a guide system (28) for moving the door (26) between the closed off and released positions. The guide system (28) includes a main rail (46) that is fixed relative to the structure and a main carriage (48) mechanically connected to the door (26) and able to slide on the main rail (46) during the movement between said closed off and released positions. The main rail (46) is positioned between the door (26) and the structure during at least part of the movement of the door (26) between said closed off and released positions.

Abstract: The aircraft seat unit includes a first seat 13, a second seat 14, an intermediate portion 15 disposed between the first seat 13 and the second seat 14, and a front wall 11 adjacent to the intermediate portion 15. An axis line X1 of the first seat 13 and an axis line X2 of the second seat 14 are respectively disposed at angles that are oriented in mutually opposite directions with respect to a traveling direction. The intermediate portion 15 is disposed in a space between the first set and the second seat and is capable of supporting a load of a bassinet 30 placed thereon. The front wall 11 includes engagement holes 11e that detachably engage with engagement portions 32 of the bassinet 30.

Abstract: An assembly having an aircraft door and auxiliary equipment. The aircraft door and the auxiliary equipment are connected by a flexible deformable bellows having creases. The door comprises a passing through hole and a support joinable to the first end of the bellows. The auxiliary equipment comprises a support joinable to the second end of the bellows and a projecting part. The projecting part is configured to have elevation movement and/or azimuth movement, and the projecting part crosses the interior of the bellows and the hole of the door and protrudes out of the door. At both ends of the bellows a clamp joins and tightens each end of the bellows with the corresponding support. There is a fixed joint between the first end of the bellows and the door and a movable joint between the second end of the bellows and the auxiliary equipment.

Abstract: A cushion length adjusting system for use in an ejection seat of an aircraft may include a seat pan and first cushion length adjuster coupled to the seat pan. The cushion length adjuster may be hingedly or slidingly coupled to the seat pan. The cushion length adjuster may be configured to adjust a leg support length for greater ergonomics for a pilot of an aircraft.