Abstract: An apparatus includes a first input power bus having a first input terminal coupled to a first input power source, a first output terminal, and a first group of line diodes between the first input terminal and the first output terminal. The apparatus also includes a second input power bus having a second input terminal coupled to a second input power source, a second output terminal coupled to the first output terminal of the first input power bus, and a second group of line diodes between the second input terminal and the second output terminal. The first output terminal and the second output terminal are coupled to provide power to a load.

Abstract: Aircraft Auxiliary Power Unit (APU) controllers and related methods are described herein. An example APU controller includes a sensor interface to receive a signal from a speed sensor. The signal includes pulses representing a rotational speed of an engine of an APU. The APU controller also includes an overspeed detection circuit including a counter to count a number of pulses from the signal occurring within a time interval, a digital-to-analog converter (DAC) to convert the number of pulses into an analog voltage signal and a comparator to: compare the analog voltage signal to an overspeed threshold signal and generate a shutdown command in response to the analog voltage signal exceeding the overspeed threshold signal. The APU controller also includes a valve driver to, in response to receiving the shutdown command, cause a fuel shutoff valve to cease fuel flow to the engine of the APU.

Abstract: A power bus system for supplying electric power to a load includes a first power bus circuit coupled to a first power source and including a first primary inductor, a second power bus circuit coupled to a second power source and including a second primary inductor, and a third power bus circuit coupled to the load and including a first secondary inductor electrically connected in series with a second secondary inductor. The first primary inductor and the first secondary inductor are arranged as a first transformer, the second primary inductor and the second secondary inductor are arranged as a second transformer, and the first power bus circuit is electrically isolated from the second power bus circuit.

Abstract: Aircraft Auxiliary Power Unit (APU) controllers and related methods are described herein. An example APU controller includes a sensor interface to receive a signal from a speed sensor. The signal includes pulses representing a rotational speed of an engine of an APU. The APU controller also includes an overspeed detection circuit including a counter to count a number of pulses from the signal occurring within a time interval, a digital-to-analog converter (DAC) to convert the number of pulses into an analog voltage signal and a comparator to: compare the analog voltage signal to an overspeed threshold signal and generate a shutdown command in response to the analog voltage signal exceeding the overspeed threshold signal. The APU controller also includes a valve driver to, in response to receiving the shutdown command, cause a fuel shutoff valve to cease fuel flow to the engine of the APU.

Abstract: An adaptive polyhedral display device includes at least at least N-number of display devices, a location sensor, and a display system. Each display device is coupled together to form a polyhedron structure that has at least (N+1) sides and an inner volume. Each display device includes a touch sensitive display and an associated display controller, and each touch sensitive display at least partially defines a different one of the sides of the polyhedron structure. The location sensor is disposed within the inner volume, and is configured to sense a location of the polyhedron structure. The display system processor is disposed within the inner volume and is configured to individually communicate with each one of the display controllers and, in response to the location data, to command each display controller to render, on its associated touch sensitive display, a user interface associated with a sensed location.

Abstract: A system and method for limiting in-rush current from a power source to a load includes sensing that a load has been electrically connected to receive electrical power from the power source. A current limiter circuit is configured to at least inhibit electrical current flow from the power source to the load for a predetermined time period. After the predetermined time period, the current limiter circuit is configured to no longer at least inhibit the electrical current flow from the power source to the load. Upon sensing that the load has been electrically disconnected from the power source, the current limiter circuit is reconfigured to at least inhibit electrical current flow from the power source to a load that may be subsequently connected to receive electrical power from the power source.

Abstract: Embodiments of an avionic media system are provided, as are embodiments of an actuated media docking station and embodiments of an over-center locking mechanism suitable for usage in an actuated media docking station. In one embodiment, the avionic media system includes an actuated media docking station and an onboard electronic device. The actuated media docking station includes, in turn, a housing assembly, a mass media device (“MMD”) receptacle coupled to the housing assembly, a connector mounted to the MMD receptacle and configured to interface with the MMD when inserted into the MMD receptacle, and an actuator coupled to the housing assembly and to the MMD receptacle. The actuator moves the MMD receptacle between: (i) a loading position in which an MMD can be inserted into the MMD receptacle, and (ii) a retaining position in which removal of an MMD from the MMD receptacle is physically obstructed.

Abstract: A system and method for limiting in-rush current from a power source to a load includes sensing that a load has been electrically connected to receive electrical power from the power source. A current limiter circuit is configured to at least inhibit electrical current flow from the power source to the load for a predetermined time period. After the predetermined time period, the current limiter circuit is configured to no longer at least inhibit the electrical current flow from the power source to the load. Upon sensing that the load has been electrically disconnected from the power source, the current limiter circuit is reconfigured to at least inhibit electrical current flow from the power source to a load that may be subsequently connected to receive electrical power from the power source.

Abstract: Embodiments of an avionic media system are provided, as are embodiments of an actuated media docking station and embodiments of an over-center locking mechanism suitable for usage in an actuated media docking station. In one embodiment, the avionic media system includes an actuated media docking station and an onboard electronic device. The actuated media docking station includes, in turn, a housing assembly, a mass media device (“MMD”) receptacle coupled to the housing assembly, a connector mounted to the MMD receptacle and configured to interface with the MMD when inserted into the MMD receptacle, and an actuator coupled to the housing assembly and to the MMD receptacle. The actuator moves the MMD receptacle between: (i) a loading position in which an MMD can be inserted into the MMD receptacle, and (ii) a retaining position in which removal of an MMD from the MMD receptacle is physically obstructed.