A shield system for an unmanned arial vehicle (AUV) is provided. The shield system includes inner shield members rigidly mounted to at least the rotor arms of the AUV and outer shield members shock mounted to the inner shield members. The shield system defines opening for sensors, payload or mechanical portions of the UAV.

An engine-mounted component life cycle data tracking system is provided. The system includes a plurality of RFID tags associated with, positioned proximate to, and configured to transmit and store identification, repair history, and dynamic data regarding a different engine component of a plurality of engine components, wherein the dynamic data includes engine usage, component usage, and/or component fault information. The system further includes an aircraft-mounted controller that includes non-transient computer readable storage media. The controller is configured to: store identification and repair history data retrieved from the RFID tags in the storage media; store dynamic data for the plurality of engine components in the storage media after each engine cycle; and transmit dynamic data to the RFID tags after each engine cycle for storage. After each engine cycle, the aircraft-mounted controller includes in its storage media the identification, repair history and dynamic data for the plurality of engine component.

An engine-mounted component life cycle data tracking system is provided. The system includes a plurality of RFID tags associated with, positioned proximate to, and configured to transmit and store identification, repair history, and dynamic data regarding a different engine component of a plurality of engine components, wherein the dynamic data includes engine usage, component usage, and/or component fault information. The system further includes an aircraft-mounted controller that includes non-transient computer readable storage media. The controller is configured to: store identification and repair history data retrieved from the RFID tags in the storage media; store dynamic data for the plurality of engine components in the storage media after each engine cycle; and transmit dynamic data to the RFID tags after each engine cycle for storage. After each engine cycle, the aircraft-mounted controller includes in its storage media the identification, repair history and dynamic data for the plurality of engine component.

A remote sensor data acquisition system for an aircraft includes a plurality of remote sensors co-located onboard the aircraft and adapted to measure one or more aircraft-related parameters. A remote sensor interface is co-located with the plurality of remote sensors. The remote sensor interface includes a communication bus having a plurality of nodes to transmit data from the plurality of remote sensors. A plurality of subsystems are each adapted to receive data from the plurality of remote sensors simultaneously and in real time via the remote sensor interface. A remote sensor data acquisition method for an aircraft includes sensing one or more parameters onboard the aircraft via a plurality of remote sensors and transmitting sensor data from the plurality of remote sensors to a plurality of subsystems independently and in real time via a remote sensor interface.

A method, apparatus, and system for controlling an aircraft. A target state for the aircraft is identified. A current mission state is determined for the aircraft. A sequence of actions is selected from a pool of potential actions to reach the target state from the current mission state for the aircraft. The sequence of actions is selected based on the current mission state. The actions in the sequence of actions for which preconditions for the actions that have been met are performed. The actions are performed in an order defined by the sequence of actions.

A method, apparatus, and system for controlling an aircraft. A target state for the aircraft is identified. A current mission state is determined for the aircraft. A sequence of actions is selected from a pool of potential actions to reach the target state from the current mission state for the aircraft. The sequence of actions is selected based on the current mission state. The actions in the sequence of actions for which preconditions for the actions that have been met are performed. The actions are performed in an order defined by the sequence of actions.

A method of monitoring the condition of an aircraft landing gear shock absorber, the shock absorber including at least one spring chamber containing a gas, the method comprising taking a plurality of measurements of the gas pressure and temperature, each gas pressure and temperature measurement pair being taken of at the same instant relative to an operating cycle of the shock absorber; calculating, based on each pair of gas pressure and temperature measurements, a first value; storing the first value in a log; determining a value trend based on the log; and in response to determining that the value trend is outside a first range of values, generating a first notification signal.

A method of monitoring the condition of an aircraft landing gear shock absorber, the shock absorber including at least one spring chamber containing a gas, the method comprising taking a plurality of measurements of the gas pressure and temperature, each gas pressure and temperature measurement pair being taken of at the same instant relative to an operating cycle of the shock absorber; calculating, based on each pair of gas pressure and temperature measurements, a first value; storing the first value in a log; determining a value trend based on the log; and in response to determining that the value trend is outside a first range of values, generating a first notification signal.

The disclosure relates to a device and a method for managing a fleet of information communication devices with reversible attachment on aircraft turbomachines, having: an association of a device among the fleet of devices with a turbomachine among a fleet of turbomachines, an attachment, an acquisition of at least one turbomachine operating parameter, a development of at least one indicator that allows the update of a digital twin of the turbomachine based on the operating parameter acquired, a communication of the indicator that allows the update of the digital twin to a digital twin storage entity.

The disclosure relates to a device and a method for managing a fleet of information communication devices with reversible attachment on aircraft turbomachines, having: an association of a device among the fleet of devices with a turbomachine among a fleet of turbomachines, an attachment, an acquisition of at least one turbomachine operating parameter, a development of at least one indicator that allows the update of a digital twin of the turbomachine based on the operating parameter acquired, a communication of the indicator that allows the update of the digital twin to a digital twin storage entity.