Abstract: A propulsion system for an aircraft includes: (1) an engine configured to generate a mass flow, (2) a nozzle having a pathway having a throat and a trailing edge, the throat or the trailing edge being configured to enlarge and contract, (3) a deployable obstructer disposed in the nozzle, (4) a first pressure sensor to sense the static pressure of the mass flow at the nozzle exit, (5) a second pressure sensor to sense the ambient pressure proximate the aircraft, and a (6) controller. The controller is coupled with the first and second pressure sensors, the deployable obstructer, and the throat or the trailing edge (whichever is configured to enlarge and contract). The controller receives the static and ambient pressures and when there is a disparity, the controller controls at least one of the deployable obstructer, the throat, and the trailing edge in a manner that reduces the disparity.

Abstract: An arrangement for use with a propulsion system for a supersonic aircraft includes a center body configured for coupling to an inlet and to support a boundary layer formed when the supersonic aircraft is flown at a predetermined altitude supersonic speed. The arrangement further includes a first vortex generator disposed on the center body. The first vortex generator extends a first height above the center body. The arrangement still further includes a second vortex generator disposed on the center body. The second vortex generator extends a second height above the center body, the second height being greater than the first height. The first height and the second height are greater than approximately seventy-five percent of a thickness of the boundary layer proximate a location of the first vortex generator and the second vortex generator, respectively, when the aircraft if flown at the predetermined altitude and the predetermined speed.

Abstract: An aircraft includes the aircraft component. The aircraft component includes an outer skin portion, a plurality of major stiffeners, and a plurality of minor stiffeners. The outer skin portion has an interior side and an exterior side configured to define an exterior boundary of the aircraft. The major stiffeners are integral with the outer skin portion and extend out from the interior side. The major stiffeners are configured to resist global deflection of the aircraft component in response to a bird strike on the aircraft component. The minor stiffeners are disposed between the major stiffeners, are integral with the outer skin portion, and extend out from the interior side. The minor stiffeners are configured to resist perforation of the aircraft component in response to the bird strike on the aircraft component.

Abstract: Systems, aircraft, and non-transitory media are provided. An avionics system for an aircraft includes a storage device and one or more data processors. The storage device stores instructions for monitoring an actual performance of the aircraft. The one or more data processors are configured to execute the instructions to: generate a lateral component and a longitudinal component of a measured moving air mass relative to the aircraft; generate a plurality of wind independent positions of the aircraft along a potential aircraft trajectory based on a prediction model; and generate a plurality of wind corrected positions of the aircraft based on the plurality of wind independent positions, on the lateral component, and on the longitudinal component.

Abstract: The voter circuit and method determines a voted output among plural inputs each carrying circular data. To supply the voted output, a statistical average (e.g., mean or median) is computed by grouping the plural inputs into pairs, and for each pair generating a minimum angular difference by selecting the minimum of (a) the absolute difference between the pairs of inputs, and (b) the conjugate of the absolute difference between the pairs of inputs. The voted output is a statistical average generated from the minimum angular difference.

Abstract: A system and method is provided for data over power in an aircraft that includes a direct current power source for providing power over power lines to devices onboard the aircraft and a data injector coupled to the power lines for digitally modulating radio frequency data onto twisted pair data over power lines to provide data and power to the devices. A controller is coupled to the direct current power source and the data injector for providing the data to digitally modulate the radio frequency onto the twisted pair data over power lines such that power for the devices onboard the aircraft and data for control of the device onboard the aircraft are provided to the devices onboard the aircraft over the twisted pair data over power lines.

Abstract: The voter circuit and method determines a voted output among plural inputs each carrying circular data. To supply the voted output, a statistical average (e.g., mean or median) is computed by grouping the plural inputs into pairs, and for each pair generating a minimum angular difference by selecting the minimum of (a) the absolute difference between the pairs of inputs, and (b) the conjugate of the absolute difference between the pairs of inputs. The voted output is a statistical average generated from the minimum angular difference. The monitor circuit and method assesses validity among the plural inputs by comparing inputs in pairs, two-by-two, generating for each pair a minimum angular difference and comparing the difference to a threshold and persistence time is confirmed. The monitor declares an input invalid that is in disagreement with all other inputs paired against it.

Abstract: An acoustic barrier assembly includes a first wall that is gas impermeable. The acoustic barrier assembly further includes a second wall that is gas impermeable. The second wall is disposed opposite the first wall. The acoustic barrier assembly further includes a periphery wall coupling the first wall with the second wall in a manner that forms a pocket between the first wall and the second wall. The periphery wall is flexible, and the pocket is fluid-tight. The acoustic barrier assembly further includes a gas disposed in the pocket. The gas has a first molecular weight that is lower than a second molecular weight of air. The acoustic barrier assembly still further includes a biasing member that is disposed within the pocket. The biasing member is coupled with both the first wall and the second wall.

Abstract: Exemplary embodiments of a decorative hard flooring system for an aircraft are disclosed herein. The hard flooring system includes a plurality of decorative hard floor assemblies at least some of which include a decorative hard flooring layer and a metallic substrate layer having at least one aperture formed therein to receive a warming element. The flooring system further includes, a power supply coupled to the warming element and a controller coupled to the power supply to control the power supplied to the warming element. An ambient temperature sensor coupled to the controller to provide an indication of ambient temperature so that the controller controls the power supply to power the warming elements to warm the decorative hard floor assemblies to be substantially at the ambient temperature.

Abstract: Cradle assemblies for supporting a door of an aircraft to facilitate servicing the door, and arrangements and methods for the same are provided. In one example, a cradle assembly includes a base and a cradle support subassembly pivotably coupled to the base. The cradle support subassembly is configured to support an outer section of the door.

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 an outer covering that has a first surface. The first surface is configured to be exposed to the interior of the aircraft. A second surface is disposed opposite the first surface. The second surface has a first pattern formed therein that is hidden from the first surface. A first light source is operative to generate a first light and is disposed adjacent to the second surface generally aligned with the first pattern. When the first light source generates the first light, a first illuminated pattern corresponding to the first pattern formed in the second surface is visible on the first surface.

Abstract: Interior panels for interiors of vehicles, vehicles, and methods for making interior panels for interiors of vehicles are provided. In one example, the interior panel includes an outer covering having a first surface. A second surface is disposed opposite the first surface. The second surface has a pattern formed therein that is hidden from the first surface. A light source is operative to generate light and is disposed adjacent to the second surface generally aligned with the pattern. When the light source generates light, an illuminated pattern corresponding to the pattern is visible on the first surface. A capacitive sensor is configured to generate a capacitance change signal in response to change in capacitance of the capacitive sensor. A controller is in communication with the capacitive sensor to receive the capacitance change signal and is configured to generate a command signal in response to the capacitance change signal.

Abstract: Cabinets, methods for making cabinets, and aircraft including cabinets are provided. In one example, a cabinet includes a cabinet body that at least partially surrounds a cabinet space and that defines a cabinet opening that allows access to the cabinet space. A cabinet door at least partially covers the cabinet opening when in a closed position and extends upward from a lower edge portion to an upper edge portion. The cabinet door has an outer exposed surface facing generally in a first direction away from the cabinet space when in the closed position. The cabinet door is operatively coupled to the cabinet body for opening from the closed position to an open position including the lower edge portion moving generally upward and the upper edge portion moving generally upward and towards the first direction to expose the cabinet opening.

Abstract: Systems and vehicle are provided. A vehicle system for a vehicle includes: a trajectory selection module configured to select a potential vehicle path relative to a current vehicle movement condition; a trajectory movement condition module configured to estimate a modeled movement condition of the vehicle along the potential vehicle path; a limit comparison module configured to determine whether the modeled movement condition violates vehicle limits; and a violation indicator module configured to generate an indication of impending violation.

Abstract: An aircraft includes an engine, a thrust reverser, landing gear, a brake system, a pilot input device, and a control system. The engine is configured to generate thrust directed to move the aircraft in a forward direction. The landing gear includes wheels. The brake system is configured to generate a braking force on the wheels. The pilot input device is positioned for use by a pilot of the aircraft. The control system is programmed to: determine whether the taxi operations are allowed; receive a request to achieve and hold a taxi speed at a desired taxi speed from the pilot input device; and command the engine, the thrust reverser, and the brake system to achieve and maintain the desired taxi speed in response to receiving the request to hold taxi speed only when the taxi operations are allowed.

Abstract: Exemplary embodiments of a system and method are provided for detecting cracks and crack propagation in aircraft structures subject to repetitive stress. A method for detecting onset or propagation of defects in a structure includes monitoring the structure with an infrared sensor to provide thermal data of the structure within a field of view of the infrared sensor. A processor is used to process the thermal data memory to extract features from the thermal data and utilize at least one machine learning model to detect onset or propagation of defects in the structure. A system includes an infrared sensor having a field of view of the structure and a processor coupled to the infrared sensor and a memory, which contains instructions that cause the processor to process thermal data from the infrared sensor to extract features from the thermal data and utilize at least one machine learning model to detect onset or propagation of the defects in the structure.

Abstract: Systems, methods, aircraft, non-transitory media, and memories are provided. An avionics system for an aircraft includes a storage device and one or more data processors. The storage device stores instructions for converting between airspeed types and the one or more data processors is configured to execute the instructions to: generate a calibrated airspeed of the aircraft; convert the calibrated airspeed to an actual true airspeed of the aircraft; determine an initial approximate relationship between the calibrated airspeed and a computed true airspeed as a function of a pressure altitude of the aircraft; generate an adjusted approximate relationship based on the actual true airspeed and the initial approximate relationship at a chosen pressure altitude; and estimate a future airspeed of the aircraft based on the adjusted approximate relationship and a future altitude.

Abstract: A tree structure represents a terrain area as nested polygons organized in a parent-child relationship, each polygon associated to a specific geographic location. The tree structure defines at least one parent node and a plurality of child nodes, some being leaf nodes containing a height value. A processor uses a distance measure to change the tree structure topology assessing whether all leaf node children of a first parent node lie outside a predetermined distance from an aircraft runway, and if so, converting the first parent node into a leaf node by storing in the first parent node a height value representing the greatest of the respective height values of the leaf node children and by removing the leaf node children; and iteratively repeating for each remaining parent node until it has been determined that every remaining parent node in the data structure cannot be pruned without violating accuracy requirements.

Abstract: A fuel drain engagement tool and a method for draining fuel from a fuel tank are provided. In one example, a fuel drain engagement tool includes a housing. An engagement mechanism is coupled with the housing and extending upward therefrom. The engagement mechanism is configured to engage a fuel drain valve and to move between a contracted state and an expanded state. A compression applicator is coupled with the housing and is positioned to engage the engagement mechanism when the compression applicator is compressed to apply a force to the engagement mechanism that causes the engagement mechanism to move from the expanded state to the contracted state.