Abstract: A flight deck arrangement includes, but is not limited to, a window. The flight deck arrangement further includes a surface disposed proximate the window and positioned below the window. The flight deck arrangement further includes a rail mounted to the surface. The rail is disposed proximate the window and positioned below the window. The rail extends along the surface in a direction generally aligned with a lower portion of the window. The flight deck arrangement still further includes a visor mounted to the rail and selectively positionable along the rail.

Abstract: A composite reinforcement structure including a first skin having a first end and a second end and a second skin having a first end and a second end. The first end of the first skin and the first end of the second skin are coupled. A corrugated spar is disposed between the first skin and the second skin and is bonded to the first skin and the second skin.

Abstract: Air vehicles, fly-by wire systems, and method for preemptive mitigation of turbulence are provided. An air vehicle includes a flight control surface, a sensor, and a controller. The sensor is configured to determine a velocity of an air mass that is separated from the air vehicle by a predetermined distance. The controller is communicatively coupled with the sensor and is configured to determine whether the air mass will disturb smooth flight of the air vehicle. The controller is further configured to manipulate the flight control surface in response to determining that the air mass will disturb smooth flight of the air vehicle.

Abstract: Display systems, controllers, and methods are provided. A display system for an aircraft includes a display unit, an input device, and a controller. The controller is communicatively coupled with the display and the input device and is configured to retrieve an electronic checklist that includes a plurality of tasks including an annotated task associated with at least one of a note, a warning, a caution, and task information. The controller is further configured to hide from view the at least one of the note, the warning, the caution, and the task information in an image of the electronic checklist based at least in part on viewing criteria. The controller is further configured to generate a signal that causes the display unit to visually present the image.

Abstract: A propulsion system for a supersonic aircraft includes an engine including an engine core and an engine bypass, a compression surface upstream of the engine, a shroud surrounding the engine configured to direct airflow passing over the compression surface towards the engine, and a plurality of vortex generators positioned upstream of the engine. The vortex generators have a height such that when the supersonic aircraft is flown at a predetermined altitude and predetermined speed, the plurality of vortex generators create vortices that propagate partially outside of a boundary layer formed proximate a surface of a supersonic inlet. The vortices cause a high-velocity portion of the airflow to move towards the engine core and a low-velocity portion of the airflow to move towards the engine bypass. The plurality of vortex generators are disposed aft of a terminal shock and have a height greater than the thickness of the boundary layer.

Abstract: The disclosed embodiments relate to an aircraft having an in-flight leveling system for a seat onboard the aircraft that includes a swivel mechanism providing selective rotational movement of the a rear portion of the seat to compensate for an angle of inclination of the aircraft during flight. A locking mechanism is coupled to the swivel mechanism to retain the seat in a first position for use on the ground and a second position for use during flight. An actuator moves the locking mechanism between a locked condition and an unlocked condition permitting the seat to move between the first position to the second position enabling the seat to be substantially level when the aircraft is on the ground and during flight.

Abstract: Aircraft, vibration isolation assemblies, and methods of assembling vibration isolation assemblies are provided. An aircraft includes a vibration isolation assembly. The vibration isolation assembly includes a mounting track, a plate, a clamp block, a vibration isolator, and a support fitting. The mounting track defines a cavity and includes flanges that define an opening to the cavity. The plate is configured to be positioned on the flanges outside of the cavity. The clamp block is configured to be fastened to the plate under the flanges of the mounting track within the cavity. The vibration isolator is configured to be laterally constrained by the clamp block within the cavity. The support fitting is configured to be secured to the vibration isolator outside of the cavity.

Abstract: A system for controlling a pressure field around an aircraft in flight is disclosed herein. In a non-limiting embodiment, the system includes, but is not limited to, a plurality of pressure sensors that are arranged on the aircraft to measure the pressure field. The system further includes, but is not limited to, a controller that is communicatively coupled with the plurality of pressure sensors. The controller is configured to receive information that is indicative of the pressure field from the plurality of pressure sensors. The controller is also configured to determine when the pressure field deviates from a desired pressure field based on the information. The controller is also configured to transmit an instruction to a movable component onboard the aircraft that will cause the movable component to move in a manner that reduces the deviation.

Abstract: A mounting assembly for mounting a sound-deadening body to a fuselage of an aircraft and a method for attaching a sound-deadening body to a fuselage of an aircraft using the mounting assembly is disclosed herein. In a non-limiting embodiment, the mounting assembly includes, but is not limited to, a retaining member that is configured to engage the sound-deadening body. The mounting assembly further includes an isolating member that is engaged with the retaining member. The isolating member is configured for connection to the fuselage and is further configured to diminish transmission of vibration from the fuselage to and through the retaining member, and therefore to reduce the transmission of sound into the cabin.

Abstract: A system is provided for identifying a source of an audible nuisance in a vehicle. The system includes a device including a camera configured to receive a visual dataset, and to generate a camera signal in response thereto. The system includes a dock configured to removably couple to the device. The dock includes a microphone array configured to receive the audible nuisance, and to generate a microphone signal in response thereto. The system includes a processor module configured to be communicatively coupled with the device and the dock. The processor module is configured to generate a raw soundmap signal in response to the microphone signal. The processor module is configured to combine the camera signal and the raw soundmap signal, and to generate a camera/soundmap overlay signal in response to combining the camera signal and the raw soundmap signal.

Abstract: A console assembly for use on a flight deck of an aircraft includes, but is not limited to, a console having a recess. The recess has an opening. The console assembly further includes a mounting assembly mounted within the recess. The console assembly further includes a support surface mounted to the mounting assembly. The console assembly further includes a closeout panel that is mounted to the support surface. The support surface fits within the recess. The mounting assembly facilitates movement of the support surface between a retracted and a deployed position. The support surface is disposed within the recess while in the retracted position and outside of the recess while in the deployed position. The closeout panel is disposed at a location on the support surface that causes the closeout panel to close the opening of the recess when the support surface is in the retracted position.

Abstract: Aircraft, wing-to-body fairing assemblies, and air exchange systems are provided. An aircraft includes a fuselage, a wing secured to the fuselage, an outer skin panel, and an air exchange system. The outer skin panel is secured to the wing and/or the fuselage and at least partially defines a cavity. The air exchange system is secured to the outer skin panel and exchanges air between the cavity and an external environment. The air exchange system includes an air inlet, a diffuser, and a silencer. The air inlet is disposed in the outer skin panel and accommodates an air flow between the cavity and the external environment. The diffuser is attached to the air inlet and has a varying cross sectional area to change the speed of the air flow. The silencer is attached to the diffuser and communicates the air flow between the diffuser and the cavity and reduces noise.

Abstract: An auxiliary power unit inlet assembly includes an inlet duct having a first end and a second end. The auxiliary power unit inlet assembly further includes a door associated with the second end of the inlet duct. The door moves between a first position and a second position. The door closes the second end of the inlet duct when in the first position and permits air to enter the second end of the inlet duct when in the second position. The auxiliary power unit inlet assembly further includes a sound absorbing component mounted to the door and disposed proximate the inlet duct. The sound absorbing component is positioned at a location on the door such that a noise generated by the auxiliary power unit will directly impinge on the sound absorbing component.

Abstract: Aircraft, aircraft exterior speaker systems, and methods of projecting sound waves from an exterior of an aircraft are provided. An aircraft includes an outer skin membrane, a vibration actuator, and a controller. The outer skin membrane has an exterior surface that defines an exterior boundary of the aircraft. The vibration actuator is coupled for common vibration with the outer skin membrane. The controller is operatively coupled with the vibration actuator and is configured to generate a command for the vibration actuator based on audible content to be projected from the exterior surface. The controller is further configured to transmit the command to the vibration actuator. The vibration actuator is configured to vibrate in response to receiving the command.

Abstract: An aircraft data network is provided that can include a first Remote Data Concentrator (RDC), a network switch and a second RDC. The first RDC can receive one or more input signals comprising data from a transmitting system, and translate the data per a network protocol to generate translated data having a format in accordance with the network protocol. The network switch can receive the translated data from the first RDC, determine a destination for at least some of the translated data, and route at least some of the translated data toward a first receiving system. The second RDC can receive at least some of the translated data from the network switch, convert at least some of the translated data to generate converted data having a format designed for use by the first receiving system, and communicate the converted data to the first receiving system.

Abstract: Nose landing gear arrangements for aircrafts, aircrafts including such nose landing gear arrangements, and methods for making such nose landing gear arrangements are provided. In one example, a nose landing gear arrangement includes a wheel assembly and a main strut. The main strut is operatively coupled to the wheel assembly and is configured to move between an extended position and a retracted position. The main strut in the extended position extends outside of the fuselage substantially along a generally vertical plane to position the wheel assembly for takeoff and/or landing of the aircraft. The main strut in the retracted position is disposed inside the fuselage. A flexible sheet is disposed adjacent to the main strut and is configured such that when the main strut is in the extended position the flexible sheet is positioned substantially around the main strut.