A rotor for an aircraft is described having: a support angularly fixed with respect to an axis and housing a power source; a unit rotatable about axis and housing an electrical load of the resistive type; and a power supply system for the electrical load and comprising: a first transformer electrically interposed between the power source and the load; the first transformer comprises: a first winding arranged on the support and a second winding arranged on the unit, a stator carried by the support, rotationally fixed with respect to axis and to which the first winding is fixed; and a rotor operatively connected to the unit and to which the second winding is fixed; the power supply system comprises a capacitive circuit electrically connected to the first transformer, so as to reduce the reactive power absorbed by the rotary transformer.

A rotor for an aircraft is described having: a support angularly fixed with respect to an axis and housing a power source; a unit rotatable about axis and housing an electrical load of the resistive type; and a power supply system for the electrical load and comprising: a first transformer electrically interposed between the power source and the load; the first transformer comprises: a first winding arranged on the support and a second winding arranged on the unit, a stator carried by the support, rotationally fixed with respect to axis and to which the first winding is fixed; and a rotor operatively connected to the unit and to which the second winding is fixed; the power supply system comprises a capacitive circuit electrically connected to the first transformer, so as to reduce the reactive power absorbed by the rotary transformer.

An abnormality warning system provides an abnormality warning for multiple motor systems that drive a motor used correspondingly to each of multiple rotors included in an electric aircraft. The abnormality warning system includes an abnormality determination unit and a warning level setting unit. The abnormality determination unit determines an abnormal one of the motor systems. The warning level setting unit sets a warning level to warn abnormality, based on at least position information of the rotor in the electric aircraft or the usage of the rotor corresponding to a motor system determined to be abnormal by the abnormality determination unit.

An abnormality warning system provides an abnormality warning for multiple motor systems that drive a motor used correspondingly to each of multiple rotors included in an electric aircraft. The abnormality warning system includes an abnormality determination unit and a warning level setting unit. The abnormality determination unit determines an abnormal one of the motor systems. The warning level setting unit sets a warning level to warn abnormality, based on at least position information of the rotor in the electric aircraft or the usage of the rotor corresponding to a motor system determined to be abnormal by the abnormality determination unit.

A camera with a field of view toward an external environment of an aircraft is disposed within an aircraft door such that a ground surface is within the field of view of the camera during taxiing of the aircraft. A display device is disposed within an interior of the aircraft. A processor is operatively coupled to the camera and to the display device. The processor analyzes image data captured by the camera for docking guidance by identifying, within the captured image data, a region on the ground surface corresponding to an alignment fiducial indicating a parking location for the aircraft, determining, based on the region of the captured image data corresponding to the alignment fiducial indicating the parking location, a relative location of the aircraft with respect to the alignment fiducial, and outputting an indication of the relative location of the aircraft to the alignment fiducial.

Liquid-gauging systems for estimating amounts of liquid within collapsible bladders. In some embodiments, a liquid-gauging system of this disclosure includes one or more liquid-gauging sensors that each output a signal relating to an amount of liquid within a corresponding collapsible bladder. In some embodiments, each liquid-gauging sensor comprises a variable capacitor having capacitor plates located so that the spacing between the capacitor plates changes with changing amounts of liquid within the collapsible bladder. In some embodiments, each liquid-gauging sensor comprises a pressure sensor for measuring forces, such as gravitational forces, that change with changing amounts of liquid within the collapsible bladder. In some embodiments, a liquid-gauging system is configured for an aircraft or other moving vehicle and includes one or more additional sensors to adjust the estimating process to account for changes in attitude of the vehicle during use. Corresponding methods, liquid-storage systems, and collapsible bladders are also disclosed.

Systems and methods for logging flight time in one or more digital logbooks employ an application that runs on mobile devices to determine when aircraft takeoff and aircraft landings have occurred. Indications of the determined aircraft takeoff and an indication of the determined aircraft landing are stored in memory. The mobile devices send determined aircraft takeoffs and aircraft landings to a data management server, which queries an official flight data source for office flight records that correspond to the determined aircraft takeoffs and determined aircraft landings. The mobile device, via the mobile application, requests confirmation of whether the user was a required flight crew member on a flight corresponding to the determined aircraft takeoff and the determined aircraft landing.

Systems and methods for logging flight time in one or more digital logbooks employ an application that runs on mobile devices to determine when aircraft takeoff and aircraft landings have occurred. Indications of the determined aircraft takeoff and an indication of the determined aircraft landing are stored in memory. The mobile devices send determined aircraft takeoffs and aircraft landings to a data management server, which queries an official flight data source for office flight records that correspond to the determined aircraft takeoffs and determined aircraft landings. The mobile device, via the mobile application, requests confirmation of whether the user was a required flight crew member on a flight corresponding to the determined aircraft takeoff and the determined aircraft landing.

The present disclosure is directed to a flight deck barrier apparatus or device including a frame having a first jamb, a second jamb, and a header. A foldable barrier mechanically coupled to the second jamb. An edge beam mechanically coupled to the foldable barrier. The edge beam configured to mechanically cooperate with strikers along the first jamb and mechanically cooperate with strikers along the second jamb. The edge beam including a plurality of catches. Respective ones of the plurality of catches interlock with corresponding ones of the strikers along the first jamb when the foldable barrier is in a stowed position such that a flight deck of an aircraft is accessible. Respective ones of the plurality of catches interlock with corresponding ones of the strikers along the second jamb when the foldable barrier is in an expanded position limiting access to the flight deck barrier of the aircraft.

A fault resilient airborne network includes a plurality of aircraft system components installed within an aircraft and at least one agent in communication with the plurality of aircraft system components during in-flight operation of the aircraft. The at least one agent is configured to monitor an aircraft system component for a fault, observe a fault within the aircraft system component, and provide reconfiguration instructions to the aircraft system component in response to the observed fault. The at least one agent is further configured to predict a life expectancy of the aircraft system component using machine learning models while monitoring the aircraft system component for a fault, and provide reconfiguration instructions to the aircraft system component when the life expectancy of the aircraft system component meets a threshold. The reconfiguration instructions are configured to cause an adjustment in at least some of the plurality of aircraft system components.