Abstract: Methods and related apparatus for improving synchronization of two or more engines on an aircraft are disclosed. Such method may be used where each engine comprises a first spool and a second spool, and, where a rotational speed of a first spool of a first engine has been substantially synchronized with a rotational speed of a first spool of a second engine. An exemplary method comprises receiving a value of a sensed parameter useful in controlling the first engine; adding a bias to the value; and using the biased value for controlling the first engine to cause a change in rotational speed of the second spool of the first engine in relation to the rotational speed of the first spool of the first engine.

Abstract: Several embodiments of buffer zones are provided that are contemplated to be disposed with respect to two or more adjacent elements on an aircraft. The buffer zones adjust for dynamic spacing between the elements to help control different gapping requirements between the elements installed in the aircraft. Embodiments include an aircraft interior panel configuration, an aircraft interior wall panel configuration, an adjustable width aircraft bulkhead, and an aircraft personal service unit.

Abstract: A blended wing body aircraft wherein at least each profile section corresponding to the normalized half-span values from 0 to 0.2 has a thickness ratio having a nominal value within the range set forth in Table 1. Also, a blended wing body aircraft wherein at least each profile section corresponding to the normalized half-span values from 0.15 to 0.3 has a normalized chord having a nominal value within the range set forth in Table 1, and wherein a ratio between a maximum thickness of the center body and the chord length along the centerline has a nominal value of at least 16%. Also, a blended wing body aircraft wherein a region of the aircraft defined by normalized half-span values from 0.1 to 0.2 has a normalized chord having a dimensionless rate of change from ?3.5 to ?5.1, and a thickness ratio having a rate of change from ?0.27 to ?0.72.

Abstract: An aircraft cabin comprising a credenza and a lounge chair disposed above the credenza is disclosed. The lounge chair is adjustable between a first configuration defining a first seating arrangement and a second configuration defining a second seating arrangement. Also disclosed is a mechanism to facilitate the adjustment of the lounge chair.

Abstract: Systems and methods for presenting media content in an aircraft are provided. A first video display unit is communicatively coupled to a personal electronic device for obtaining therefrom a request to present the media content. A wireless access point is communicatively coupled to the first video display unit for receiving from the first video display unit a first command to query the personal electronic device for media presentation parameters, and the wireless access point is communicatively coupled to the personal electronic device for obtaining the media presentation parameters therefrom. A second video display unit is communicatively coupled to the first video display unit via the wireless access point. The wireless access point is configured for issuing a second command to at least one of the first and second video display units to cause the media content to be presented according to the media presentation parameters.

Abstract: A seat for a vehicle includes a seat pan and a backrest configurable into an upright position, a partially reclined position and a fully reclined position. The seat also includes a first pivot axis towards a front of the seat pan. The first pivot axis is vertically fixed in relation to a horizontal reference line for each of the upright position, the partially reclined position and the fully reclined position.

Abstract: Methods and apparatus for distributing electric power from a power source of an aircraft to a plurality of electrical loads of the aircraft during a limited power availability condition are disclosed. An exemplary method comprises: distributing electric power from the power source of the aircraft to the plurality of electrical loads; receiving one or more signals indicative of a demand for electric power by one or more of the plurality of electrical loads; and adjusting the power distribution to the plurality of electrical loads based on the demand for electric power by the one or more plurality of electrical loads. The power distribution is also adjusted to maintain an overall power consumption of the plurality of electrical loads at or below a threshold.

Abstract: An air gasper (air) for a vehicle includes an air inlet (26), a first housing (24) disposable through a panel in the vehicle (12), the first housing (24) being connected to the air inlet (26), a second housing (70) disposed within the first housing (24), an air outlet (72) disposed within the second housing (70), downstream of the air inlet (26), and a first mechanism (102, 70) connected between the first housing (24) and the second housing (70). The first mechanism (102, 70) permits the second housing (70) to be stowed within the first housing (24) in a stowed position and also permits the second housing (70) to extend outwardly from the first housing (24) in a deployed position.

Abstract: Wing to fuse junction shaping, and associated systems and methods are disclosed herein. An aircraft includes: a fuselage, a wing, and a fairing that covers a junction between the wing and the fuselage. The fairing is configured to receive an inboard section of the wing. An outer surface of the fairing includes an upstream bump proximate to a leading edge of the wing, a midsection sculpting, and a downstream bump proximate to a trailing edge of the wing.

Abstract: An isolation mount connecting a panel to a structure includes a housing disposable on the structure, a fastener receiver with a panel-facing surface, and a damper connecting the housing to the fastener receiver. The panel-facing surface of the fastener receiver defines a static coefficient of friction between the panel-facing surface and the panel discouraging rotation of panel-facing surface around a longitudinal axis.

Abstract: The present disclosure provides communication systems, switching devices and methods for switching air-to-ground (ATG) antennas of an aircraft. An air-to-ground (ATG) communication unit has a first set of ports for in-flight ATG communication and a second set of ports for ground communication comprising terrestrial communication and accessing fixed base operator (FBO) services. A switching device is configured to switch connectivity of at least one antenna to the first set of ports of the ATG communication unit when the aircraft is in-flight and is configured to switch connectivity of the at least one antenna to the second set of ports when the aircraft is not in-flight.

Abstract: An interior configuration for an aircraft, comprising a bed positioned adjacent to one side of a fuselage on a floor of a cabin within the aircraft; and a movable table positioned in relation to the bed so that the movable table may be positioned over at least a portion of the bed.

Abstract: Assemblies, apparatus, devices and methods useful in providing lightning protection of avionic components associated with aircraft antennas are disclosed. Aspects of the present disclosure may be used on aircraft comprising structural elements made from composite materials having a relatively low electrical conductivity. An exemplary assembly disclosed comprises: an antenna secured to a structural element of the aircraft and configured to receive wireless signals and/or transmit wireless signals external to the aircraft; a communication unit operatively connected to the antenna for signal transmission between the antenna and the communication unit; and an isolation transformer electrically disposed between the antenna and the communication unit where signal transmission between the antenna and the communication unit is conducted via the isolation transformer.

Abstract: The present disclosure describes a bulkhead assembly for an aircraft interior comprising a pocket door mechanism (48) for supporting and guiding the movement of a pocket door; and a structural member (50) to which the pocket door mechanism is attached. The structural member is attached to a structure of the aircraft and provides support for the pocket door relative to the aircraft structure independently of any decorative member (32, 34) covering the structural member.

Abstract: Methods and apparatus for non-destructive inspection using microwave microscopy are disclosed. In one embodiment, a method for inspecting an electrically-conductive mesh in a composite component using microwave microscopy comprises generating radio-frequency electromagnetic radiation using a microwave microscopy probe disposed adjacent the composite component so that the radio-frequency electromagnetic radiation interacts with the electrically-conductive mesh in the composite component, and, detecting a characteristic associated with the microwave microscopy probe. The detected characteristic is indicative of a condition of the electrically-conductive mesh.

Abstract: A passenger seat for an aircraft has a fixed seat portion with a front facing toward a first direction of the aircraft. The fixed seat portion has a centerline spaced equally from opposed lateral sides of the fixed seat portion. A first engagement member extends upwardly from the front at the centerline to a first engagement end. A moveable seat portion is mounted onto the fixed seat portion and is displaceable relative thereto. The moveable seat portion has a second engagement member extending downwardly from a front of the moveable seat portion to a second engagement end. The second engagement member is displaceable with the moveable seat portion to position the second engagement end under the first engagement end in an engagement position such that the overlapping first and second engagement ends prevent the moveable seat portion from pitching in a second direction opposite to the first direction.

Abstract: An emergency exit assembly for an aircraft, including a window frame, a window assembly having an outer surface abutting the inner surface of the window frame around its perimeter, and retaining elements spaced around the perimeter of the window assembly. The retaining elements are each connected to the window frame and bias the window assembly toward and against the inner surface of the window frame. Each retaining element has a force-release portion so that the window assembly can be disengaged from the window frame through release of the force-release portion. The force-release portion may be a frangible portion breakable upon application of the pulling force. A cable with one or more handle(s) may be connected to the retaining elements to apply the pulling force. A method of accessing an emergency exit of an aircraft is also discussed.

Abstract: An aircraft including a fuselage defining a cabin and baggage bay, engine compartments for receiving engines, an auxiliary power unit compartment for receiving an auxiliary power unit, and a fire suppression system including first and second reservoirs containing a fire suppressant. The reservoirs are each connected to all of the engine compartments for distribution of the fire suppressant thereto. The first reservoir is connected to only one of the auxiliary power unit compartment and baggage bay, and the second reservoir is connected to only the other of the auxiliary power unit compartment and baggage bay. A fire suppression system for an aircraft and a method of connecting a fire suppression system of an aircraft are also discussed.

Abstract: An acoustic abatement apparatus for an aircraft includes a layer of material disposed exterior to a fuselage of the aircraft, where the layer of material connects to the fuselage to establish a gap between the layer of material and the fuselage, a flexible container disposed in the gap, and at least one acoustic resonator connected to the flexible container. The at least one acoustic resonator is tuned to a predetermined resonator frequency.