Abstract: A system and method for detecting ground resonance and providing a warning regarding the same includes supplying, from an inertial navigation system (INS), inertial data indicative of an inertial profile of a rotorcraft, and supplying, from a sensor system, sensor data that indicates when the rotorcraft is at least partially on a landing surface. The sensor data is processed, in a processing system, to determine when the rotorcraft is at least partially on the landing surface, and when the rotorcraft is determined to be at least partially on the landing surface, the inertial data is processed, in the processing system to determine when the inertial profile of the rotorcraft indicates ground resonance may occur. Upon determining that ground resonance may occur, one or more alert signals are generated in the processing system.

Abstract: A method including: receiving data associated with a unique identity of a vehicle asset to identify the vehicle asset; receiving data associated with a unique identity of a smart wheel chock to identify the smart wheel chock; associating the identified vehicle asset with the identified smart wheel chock, such that a location of the smart wheel chock can represent a location of the vehicle asset; receiving location data associated with the location of the smart wheel chock, wherein the received location data is based, at least in part, on location data generated by one or more systems on the smart wheel chock; and identifying the vehicle asset location based on the received smart wheel chock location data such that the vehicle asset can be determined and relayed to a user device to locate the vehicle asset.

Abstract: A smart wheel chock includes a chock body including a ground engaging surface and a wheel engaging surface for engaging a wheel of a vehicle; a processor housed within the chock body; a position tracking sensor housed within the chock body, wherein the position tracking sensor is configured to detect a location of the wheel chock; a wireless communication module in communication with the processor and configured to transmit the location of the wheel chock; a power system configured to supply power to the processor and wireless communication module; and a visual indicator on the chock body, wherein the visual indicator is configured to be visible while the chock body is engaged with the wheel, and wherein the visual indicator includes a unique identifier for the smart wheel chock.

Abstract: A system and method for detecting ground resonance and providing a warning regarding the same includes supplying, from an inertial navigation system (INS), inertial data indicative of an inertial profile of a rotorcraft, and supplying, from a sensor system, sensor data that indicates when the rotorcraft is at least partially on a landing surface. The sensor data is processed, in a processing system, to determine when the rotorcraft is at least partially on the landing surface, and when the rotorcraft is determined to be at least partially on the landing surface, the inertial data is processed, in the processing system to determine when the inertial profile of the rotorcraft indicates ground resonance may occur. Upon determining that ground resonance may occur, one or more alert signals are generated in the processing system.

Abstract: An adaptive aircraft electrical power distribution system includes an aircraft power source, a power connector, an aircraft power distribution bus, and a bidirectional power controller. The aircraft power source is operable to generate and supply electrical power. The power connector is mounted on a fuselage of the aircraft. The aircraft power distribution bus is operable to distribute electrical power to an aircraft electrical load. The bidirectional power controller is mounted in the aircraft and is electrically coupled to the aircraft power source, the aircraft power connector, and the aircraft power distribution bus. The bidirectional power controller is configured to: sense when the aircraft power source is generating and supplying electrical power, sense when electrical power is being supplied to the power connector from an external power source, and selectively couple at least one of the aircraft power source or the power connector to the aircraft power distribution system.

Abstract: An adaptive aircraft electrical power distribution system includes an aircraft power source, a power connector, an aircraft power distribution bus, and a bidirectional power controller. The aircraft power source is operable to generate and supply electrical power. The power connector is mounted on a fuselage of the aircraft. The aircraft power distribution bus is operable to distribute electrical power to an aircraft electrical load. The bidirectional power controller is mounted in the aircraft and is electrically coupled to the aircraft power source, the aircraft power connector, and the aircraft power distribution bus. The bidirectional power controller is configured to: sense when the aircraft power source is generating and supplying electrical power, sense when electrical power is being supplied to the power connector from an external power source, and selectively couple at least one of the aircraft power source or the power connector to the aircraft power distribution system.