Abstract: A flight guidance panel includes a housing, a first flight guidance display, a second flight guidance display, a standby display, and a controller. The housing defines a first longitudinal side and a second longitudinal side. The first flight guidance display is disposed in the first longitudinal side of the housing and the second flight guidance display is disposed in the second longitudinal side of the housing. The standby display is disposed between the first flight guidance display and the second flight guidance display. The controller is configured for generating at least one functional panel indicating flight parameters on the first flight guidance display and on the second flight guidance display. The controller is further configured for generating standby flight information for presentation on the standby display.

Abstract: A system for virtually experiencing an aircraft includes a trailer, an aircraft fuselage, a cabin module, a head mounted display, and a controller. The aircraft fuselage is disposed in the trailer and defines an interior with a first portion and a second portion. The first portion is substantially unfurnished. The cabin module is disposed in the second portion and includes furnishings. The head mounted display is configured for movement within the interior. The controller is configured for generating a virtual aircraft interior based on a position and an orientation of the head mounted display relative to the interior of the aircraft fuselage and for controlling the head mounted display to display the virtual aircraft interior.

Abstract: Apparatuses and methods for testing electrical wiring of a device are provided. In one example, the device has a conductive portion, an electrical component, and a multiphase plug that is electrically coupled to a neutral conductor and at least two phase conductors. The neutral conductor is coupled to the conductive portion and the at least two phase conductors are coupled to the electrical component. The apparatus includes a receptacle that removably couples to the multiphase plug. A grounding cable removably couples to the conductive portion. A power supply generates power and is in electrical communication with the receptacle to communicate the power to the receptacle. An annunciator is in electrical communication with the power supply and the grounding cable and is configured to generate a response when the receptacle, the multiphase plug, the conductive portion, and the grounding cable are in electrical communication to communicate the power therethrough.

Abstract: A method for constructing an inflatable environment on top of or beneath a surface of an extraterrestrial object includes spraying Regishell onto an airform or piping the Regishell into a sandwich membrane layer of the airform. When performing the spraying of the Regishell, the method further includes combining basalt material with the Regishell and applying the combination of the basalt material and Regishell to a reinforcement layer, the reinforcement layer being internal to the airform to strengthen the inflatable environment. When performing the piping of the Regishell into the sandwich membrane, the method further includes using the sandwich membrane layer as a permeable membrane or drilling one or more holes in the sandwich membrane layer forming vents to create the permeable membrane, and releasing the gas from the sandwich membrane layer from the vents to cure and conform the Regishell as a rigid shape and structurally sound layer.

Abstract: An aircraft, a control surface arrangement, and a method of assembling an aircraft are disclosed herein. In an exemplary embodiment, the aircraft includes, but is not limited to, an airframe, a control surface, and a rotary actuator. The rotary actuator rotatably mounts the control surface to the airframe. The rotary actuator supports the control surface on the airframe and is configured to rotate the control surface with respect to the airframe when the rotary actuator is actuated. The rotary actuator is further configured to deliver torque to the control surface from a longitudinally intermediate portion of the rotary actuator.

Abstract: The present application relates to providing auxiliary port function distinction by illuminating a first light emitting diode around a data transfer capable port wherein the first light emitting diode is illuminated in a first color, illuminating a second light emitting diode around a charge only port, receiving a first data connection request at the charge only port, illuminating the first light emitting diode a second color in response to the data connection request, receiving a second data connection request at the data transfer capable port, initiating a data connection handshake between a device connected to the data transfer capable port and a processor in response to the second data connection request, and illuminating the first light emitting diode the second color in response to the initiation of the data connection handshake.

Abstract: Interactive interfaces and data structures representing physical and/or visual information are provided using smart pins (also called “pins” herein). Pins representing vectors of information may be provided. For instance, in the context of cybersecurity, each pin may represent an attack vector that an adversary can use to attack a system. Each pin may have a depth meter and may move up or down according to its value in an operating range. Each pin may also have a color, a number, or both, representing its current value in the operating range. Such pins may provide both a three-dimensional representation of data that is intuitive to users.

Abstract: Aircraft and air scoop systems are provided. An aircraft includes an interior compartment, an outer skin, an air scoop, a movable element, and a passive pneumatic actuator. The interior compartment encloses a substantially constant interior air mass at a cabin pressure during flight and the outer skin at least partially defines a ventilated cavity. The air scoop is disposed on the outer skin and communicates air between the ventilated cavity and an external environment in which the aircraft is located. The movable element is movable between an open position and a closed position over the air scoop to define an air flow area through the air scoop. The passive pneumatic actuator is operatively coupled with the movable element and moves the movable element towards the closed position in response to an increasing altitude of the aircraft based on a differential pressure between the interior air mass and the external environment.

Abstract: Apparatuses for supporting an aircraft component adjacent to an aircraft and methods for the same are provided. In one example, the apparatus includes an adapter for removably coupling to the aircraft component. A winch subassembly includes an axle that is coupled to the adapter and has a longitudinal axis. A first gear is operatively coupled to the axle to drive the axle to rotate about the longitudinal axis for rotating the adapter. The winch subassembly is configured to couple to a lift to position the adapter adjacent to the aircraft.

Abstract: The present application relates to providing auxiliary port function distinction by illuminating a first light emitting diode around a data transfer capable port wherein the first light emitting diode is illuminated in a first color, illuminating a second light emitting diode around a charge only port, receiving a first data connection request at the charge only port, illuminating the first light emitting diode a second color in response to the data connection request, receiving a second data connection request at the data transfer capable port, initiating a data connection handshake between a device connected to the data transfer capable port and a processor in response to the second data connection request, and illuminating the first light emitting diode the second color in response to the initiation of the data connection handshake.

Abstract: Fractional Fourier Transform (FrFT)-based spectrum analyzers and spectrum analysis techniques are disclosed. Rather than using the standard Fast Fourier Transform (FFT), the FrFT may be used to view the signal content contained in a particular bandwidth. Usage of the FrFT in place of the frequency or time domain allows viewing of the signal in different dimensions, where “spectral” features of interest, or signal content, may appear where they were not visible in these domains before. This may allow signals to be identified and viewed in any domain within the continuous time-frequency plane, and may significantly enhance the ability to detect and extract signals that were previously hidden under interference and/or noise, provide or enhance the ability to extract signals from a congested environment, and enable operation in a signal-dense environment.

Abstract: Vertical resolution and/or vertical accuracy of terrain elevation data near an aircraft runway is adjusted by obtaining local terrain data, yielding a first elevation value for a query location. A processor receptive of the first elevation value computes plane equations based on a predetermined standard model adapted to geometrically conform to the aircraft runway, yielding a second elevation value for the query location. The processor selectively uses the first and second elevation values to generate an adjusted elevation value that is supplied to a terrain avoidance and warning system.

Abstract: A transport trailer and a method for transporting an oversize load are provided. In one nonlimiting example, the transport trailer includes a trailer. The trailer includes an elongated body that extends in a length direction and that has an upper base surface. A support assembly is configured to support the oversize load and is pivotably coupled to the trailer to move between a first position and a second position. In the first position, the support assembly extends over the upper base surface and beyond the trailer in a width direction that is transverse to the length direction to define a wide load overhang that extends beyond the trailer in the width direction. In the second position, the support assembly is positioned at an incline relative to the first position to one of reduce and eliminate the wide load overhang.

Abstract: A ventilation system for ventilating a passenger compartment of an aircraft, an aircraft, and a method of operating the ventilation system are disclosed herein. The ventilation system includes, but is not limited to, a bezel, a fluid vent, an electronic sensor, and a valve. The bezel defines a bezel aperture and the fluid vent defines an axis that passes through the bezel aperture to direct a stream of air through the bezel into the passenger compartment. The electronic sensor is associated with the bezel and is configured to generate a bezel position signal. The valve is configured to vary a flow rate of the stream of air through the fluid vent based on the bezel position signal.

Abstract: The modular networking system supplies data and aircraft power to an inflight entertainment, communication or cabin management device within the aircraft. At least one universal module package for placement within the passenger cabin carries an Ethernet switch which has a processor programmed to support deterministic networking, such as according to AVB/TNS protocols. Devices within the cabin are attachable to ports on the Ethernet switch. A power converter circuit and power injector circuit within the module package supply power to devices attached ports on the Ethernet switch. A microcontroller-controlled circuit switch selectively admits or inhibits supply of power attached devices in response to the received control data from the avionics system.

Abstract: An aircraft includes a processor, an airframe, a pitch attitude flight control surface coupled with the airframe, a nose wheel coupled with the airframe, main wheels coupled with the airframe, and a brake system coupled with the main wheels. The processor is programmed to determine that the aircraft has entered a braking segment of a landing phase of a flight of the aircraft while the aircraft is on a ground surface and to command the pitch attitude flight control surface with a nose up command during the braking segment in response to determining that the aircraft has entered the braking segment. The nose up command causes the pitch attitude flight control surface to generate a downforce that increases traction between the main wheels and the ground surface due to a weight shift from the nose wheel to the main wheels and directly due to the downforce on the main wheels.

Abstract: The present application teaches methods and apparatuses related to providing dynamic auxiliary port power management including providing a first current to a first auxiliary port and a second current to a second auxiliary port, determining a system power level in response to the first current and the second current, comparing the system power level to a system power level threshold, and providing a third current to the second auxiliary port in response to the system power level exceeding the system power level threshold, the third current having a lower amperage than the second current.

Abstract: Flight control systems, flight control laws, and aircraft are provided. An flight control system includes an input configured to receive a pitch rate command, a processor operative to receive the pitch angle command, to calculate a pitch angle saturation limit, to compare the sum of the pitch rate command, the scaled pitch rate, and the scaled pitch angle to the pitch angle saturation limit, to convert the pitch rate command system to the pitch angle command system in response to the sum exceeding the pitch angle saturation limit value to limit the pilot pitch-up pitch rate command, and to couple the pitch rate command to an aircraft control surface for the failure case of one of control surface, and the aircraft control surface configured to adjust an aircraft control surface setting in response to the pitch rate command and/or pitch angle command to protect an aircraft from being in stall condition.

Abstract: Interior panels for interiors of aircraft, aircraft, and methods from making interior panels for interiors of aircraft are provided. In one example, the interior panel includes a first relatively hard layer having a first surface that is configured to receive noise from the interior and a second surface that is disposed opposite the first surface. The first relatively hard layer has micro-perforated holes that are formed therethrough and that are spaced apart from each other. A second layer is disposed adjacent to the second surface and has a plurality of openings that are in fluid communication with the plurality of micro-perforated holes. A third layer is disposed adjacent to the second layer. The first relatively hard layer, the second layer, and the third layer are cooperatively configured to attenuate the noise.