Abstract: Nose landing gear arrangements including a folding follow-up door for reducing airflow noise for aircrafts, aircrafts including such nose landing gear arrangements, and methods for making such nose landing gear arrangements are provided herein. 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 extend outside of the fuselage substantially along a generally vertical plane. A folding follow-up door is pivotally coupled to the main strut and extends to the fuselage. The folding follow-up door includes a first door section and a second door section that extend outwardly in directions away from each other to define an unfolded position. The folding follow-up door is foldable to move the first and second door sections towards each other about the generally vertical plane to define a folded position.

Abstract: In one embodiment, multi-mode use of an aircraft cockpit is realized a processor in the aircraft determining whether the aircraft is operating in a flight mode or a non-flight mode. When operating in the non-flight mode, the processor deactivates aircraft engines and permits wireless device access to one or more aircraft systems. When operating in the flight mode, the processor enables aircraft engines and prevents wireless device access to one or more aircraft systems.

Abstract: A system is provided for engine and generator control. The system includes a compound AC generator, a generator control unit (GCU) module and an engine electronic controller (EEC) module. The compound AC generator includes a shaft, and a permanent magnet generator (PMG) configured to be driven by the shaft to generate an AC power signal. The GCU module is configured to control the compound AC generator. The PMG is coupled to the GCU module and the EEC module such that it is configured to simultaneously supply the AC power signal to the GCU module and to the EEC module.

Abstract: A method for determining a pressure time history of a pressure wave originating from a vehicle traveling at or above supersonic speeds when the pressure wave undergoes a focusing due to convergence and intersection with a neighboring pressure wave originating from the vehicle is disclosed herein. The method includes, but is not limited to, solving a lossy nonlinear Tricomi equation with a processor and reporting an output from the processor containing a solution to the lossy nonlinear Tricomi equation. The lossy nonlinear Tricomi equation includes a variable relating to an actual atmospheric dissipative effect in a vicinity of the focusing. The solution includes, but is not limited to, a prediction of the pressure time history of the pressure wave as the pressure wave undergoes focusing. The prediction reflects the actual atmospheric dispersive and dissipative effects.

Abstract: In one embodiment, a method for health and trend monitoring for aircraft systems includes receiving, by a processor on the aircraft, a plurality of sensor signals from a respective plurality of sensors onboard the aircraft and determining a reference signal from a subset of the plurality of sensor signals. Next, each of the plurality of sensor signals is individually compared to the reference signal to provide a plurality of difference signals. Each of the plurality of difference signals is compared to a threshold value, and a maintenance message is provided for any respective sensor associated with any of the plurality of difference signals exceeding the threshold value. An aircraft employing the health and trend monitoring system is also disclosed.

Abstract: Method and arrangement for adjusting nitrogen and oxygen concentrations within regions of an aircraft. The method includes separating nitrogen from ambient air onboard an aircraft thereby establishing a high-concentration nitrogen supply and then dispensing high-concentration nitrogen from the supply to a fire-susceptible, non-habitable region of the aircraft where the high-concentration nitrogen is reservoired thereby decreasing the capability for the atmosphere therein to support combustion. Oxygen is also separated from the ambient air thereby establishing a high-concentration oxygen supply that is dispensed to an occupant cabin of the aircraft thereby increasing the level of oxygen concentration within the cabin to a level greater than the naturally occurring concentration of oxygen at the experienced internal cabin pressure.

Abstract: Disclosed is a runway alerting method and system for an aircraft performing a landing maneuver. During the landing maneuver, a minimum stopping position and a maximum stopping position for the aircraft along the runway is determined using aircraft energy state, deceleration and braking information. The minimum stopping position is based upon the aircraft performing a maximum flare maneuver prior to touchdown on the runway and the maximum stopping position is based upon the aircraft performing a minimum flare maneuver prior to touchdown on the runway. The minimum and maximum stopping positions are presented to the aircraft pilot on a display to assist the pilot in safely landing the aircraft.

Abstract: A display system for use in a flight deck of an aircraft is disclosed herein. The flight deck has an instrument panel. The display system includes, but is not limited to, a display screen that is adapted for mounting to the instrument panel and that is configured to extend along substantially an entire lateral length of the instrument panel without any discontinuity of display capability. The display system includes, but is not limited to, a plurality of image sources associated with the display screen. The plurality of image sources is configured to cause a plurality of images to appear on the display screen.

Abstract: Systems, media, and methods are provided for oscillation monitoring. An aircraft system includes a first oscillation monitoring module and a second oscillation monitoring module. The first oscillation monitoring module is configured to select first oscillating portions of an input signal, generate a frequency signal that indicates a frequency of the first oscillating portions, and generate a first failure signal in response to the frequency of the first oscillating portions exceeding first oscillatory fault detection requirements for the input signal. The second oscillation monitoring module is configured to select second oscillating portions of the input signal based on the frequency signal generated by the first oscillation monitoring module and to generate a second failure signal in response to a frequency of the second oscillating portions exceeding second oscillatory fault detection requirements for the input signal.