A system includes a robotic arm, a rotisserie control linkage, and a computer system. The robotic arm includes a touch probe and laser head. The rotisserie control linkage is configured to couple to a transport cart. The computer system is communicatively coupled to the robotic arm and the rotisserie control linkage and is configured to control the system to probe, using the touch probe of the robotic arm, a transparent outer layer of an aircraft canopy located on the transport cart in order to determine surface measurements of the aircraft canopy. The computer system also controls the system to ablate, using a plurality of predetermined parameters and the laser head of the robotic arm, an interface layer located between the transparent outer layer and the aircraft canopy, wherein movements of the robotic arm during the ablation are based on the surface measurements.

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.

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.

A method includes obtaining sensor data captured by a sensor of an aircraft during a power up event. The sensor data includes multiple parameter values, each corresponding to a sample period. The method further includes determining a set of delta values, each indicating a difference between parameter values for consecutive sample periods of the sensor data. The method further includes determining a set of quantized delta values by assigning the delta values to quantization bins based on magnitudes of the delta values. The method further includes determining a normalized count of delta values for each quantization bin. The method further includes comparing the normalized counts of delta values to anomaly detection thresholds. The method further includes generating, based on the comparisons, output indicating whether the sensor data is indicative of an operational anomaly.

A method of retrofitting an environmental control system of an aircraft includes inserting the orifice plate through the connector slot and the connector ring slot into the receptacle. The method also includes aligning the covering portion with the connector slot.

A method eliminates voids in the bond line and manipulates a thickness of the bond line. This method includes: applying an adhesive at a center of an area of a structure; placing a doubler on the adhesive over the area of the structure, wherein the doubler has a peripheral edge; and maintaining a negative pressure at the peripheral edge of the doubler while simultaneously maintaining a positive pressure at the doubler to purge entrapped gases and control a thickness of the bond line at the peripheral edge of the doubler.

A system aggregates data related to a non-conformance system in an aircraft and allocates resources to repairing the non-conformance condition. The system includes a service bus that receives and distributes the non-conformance condition and an optimizer tool that generates repair alternatives. The optimizer tool allows dynamic reconfiguration of rules to activate and deactivate or change a weight of individual rules in a rule set.

The invention concerns a charger for aeronautical maintenance equipment, the charger comprising at least one so-called “high-frequency” input electrical connector comprising a plurality of power supply pins capable of receiving a three-phase AC voltage delivered by an external power supply source at a frequency of 400 Hz, and two detection pins, a so-called “high-frequency” charging module, connected to the at least one high-frequency input electrical connector, intended to be connected to a power storage module of the aeronautical maintenance equipment, and capable of converting the AC voltage received at the plurality of power supply pins of the high-frequency input electrical connector into a DC voltage for charging the storage module, and a control module capable of generating a detection voltage between the detection pins of the high-frequency input electrical connector allowing the external power supply source, when it detects the detection voltage, to authorize the supply of the AC voltage to the plurality of power supply pins of the high-frequency input electrical connector.

The invention concerns a charger for aeronautical maintenance equipment, the charger comprising at least one so-called “high-frequency” input electrical connector comprising a plurality of power supply pins capable of receiving a three-phase AC voltage delivered by an external power supply source at a frequency of 400 Hz, and two detection pins, a so-called “high-frequency” charging module, connected to the at least one high-frequency input electrical connector, intended to be connected to a power storage module of the aeronautical maintenance equipment, and capable of converting the AC voltage received at the plurality of power supply pins of the high-frequency input electrical connector into a DC voltage for charging the storage module, and a control module capable of generating a detection voltage between the detection pins of the high-frequency input electrical connector allowing the external power supply source, when it detects the detection voltage, to authorize the supply of the AC voltage to the plurality of power supply pins of the high-frequency input electrical connector.

A method for measuring the hardware and operational state of a dual-circuit solenoid valve including first and second coaxial coils each associated with a circuit is disclosed. The method includes the steps of injecting a sinusoidal current into the first coil; measuring the voltage induced across the terminals of the second coil; and plotting at least one curve of a first magnitude proportional to the measured induced voltage as a function of a second magnitude proportional to the injected sinusoidal current.