Aspects of the disclosure relate to identifying and responding to problem conditions for a fleet of aerial vehicles. This may include receiving at one or more processors of one or more server computing devices sensor feedback from an AV of the fleet. A problem condition may be identified using the sensor feedback. A mitigation response for the problem condition relating to a mission assigned to the aerial vehicle may be determined. The mitigation response may be sent to the AV in order to cause the aerial vehicle to maneuver according to the mitigation response and thereby automatically respond to the problem condition.

A method and a system for monitoring a mechanical system, the mechanical system including a lubrication system provided with a reservoir containing a lubricating liquid, with a lubrication circuit designed to lubricate the mechanical system, as well as with a particle detection device arranged in the lubrication circuit. The detection device makes it possible, in particular, to count the number of particles flowing through the lubrication circuit and/or the flow rate of the particles. Comparing that number or that flow rate with a first threshold makes it possible to determine a risk of damage affecting the mechanical system and to anticipate the maintenance or reinforced monitoring operations that possibly need to be performed.

A method and a system for monitoring a mechanical system, the mechanical system including a lubrication system provided with a reservoir containing a lubricating liquid, with a lubrication circuit designed to lubricate the mechanical system, as well as with a particle detection device arranged in the lubrication circuit. The detection device makes it possible, in particular, to count the number of particles flowing through the lubrication circuit and/or the flow rate of the particles. Comparing that number or that flow rate with a first threshold makes it possible to determine a risk of damage affecting the mechanical system and to anticipate the maintenance or reinforced monitoring operations that possibly need to be performed.

A removable barrier and an aircraft including such a removable barrier. The barrier including a panel configured to block at least partly an opening delimited by a frame, a plurality of straps each connected to the panel and each having first and second ends, for each strap, a first connection configured to connect the first end of the strap and a first edge of the frame at least temporarily, a second connection configured to connect the second end of the strap and a second edge of the frame at least temporarily, at least one folded overlength at the level of at least one of the first and second ends of the strap, at least one breakable connection keeping the overlength folded.

An engine vibration monitoring and control system includes an aircraft autopilot and a flight management system (FMS). The FMS is in operable communication with the aircraft autopilot and is configured to determine when the aircraft autopilot is engaged and disengaged. The FMS is also adapted to receive vibration data from an engine vibration data source and is configured, upon determining that the aircraft autopilot is engaged, to: process the vibration data to determine when engine vibrations exceed one or more first thresholds, and when the engine vibrations exceed the one or more first thresholds, supply commands to the autopilot that cause the autopilot to take corrective actions to reduce the engine vibrations below the one or more first thresholds.

An engine vibration monitoring and control system includes an aircraft autopilot and a flight management system (FMS). The FMS is in operable communication with the aircraft autopilot and is configured to determine when the aircraft autopilot is engaged and disengaged. The FMS is also adapted to receive vibration data from an engine vibration data source and is configured, upon determining that the aircraft autopilot is engaged, to: process the vibration data to determine when engine vibrations exceed one or more first thresholds, and when the engine vibrations exceed the one or more first thresholds, supply commands to the autopilot that cause the autopilot to take corrective actions to reduce the engine vibrations below the one or more first thresholds.

Systems and methods relate to electric propulsor fault detection. An exemplary system includes at least a first inverter configured to accept a direct current and produce an alternating current, a first propulsor, a first motor operatively connected with the first propulsor and powered by the alternating current, and at least a noise monitoring circuit electrically connected with the direct current and configured to detect electromagnetic noise and disengage the at least an inverter as a function of the electromagnetic noise.

To locate an intermittent fault in a communication structure of an aircraft comprising pieces of equipment that are interconnected by cabling forming a plurality of communication media that are shared, an analyzer retrieves an error report relating to transmission errors observed on each of said communication media, performs a count of the transmission errors, per type of error and per communication chain, computes a median of the counts for communication chains comprising the same pair of wired pieces of equipment, and when, for a communication chain, the count exceeds a threshold equal to the median plus a predefined margin, generates an alarm indicating detection of an intermittent fault in association with the communication chain that led the threshold to be exceeded. Thus, intermittent faults are easily located and repaired.

To locate an intermittent fault in a communication structure of an aircraft comprising pieces of equipment that are interconnected by cabling forming a plurality of communication media that are shared, an analyzer retrieves an error report relating to transmission errors observed on each of said communication media, performs a count of the transmission errors, per type of error and per communication chain, computes a median of the counts for communication chains comprising the same pair of wired pieces of equipment, and when, for a communication chain, the count exceeds a threshold equal to the median plus a predefined margin, generates an alarm indicating detection of an intermittent fault in association with the communication chain that led the threshold to be exceeded. Thus, intermittent faults are easily located and repaired.

A thrust reverser of a nacelle may include a translating sleeve and an inner fixed structure a pressure relief assembly. A pressure relief mechanism may include a pressure relief door coupled via a hinge and a latch to the inner fixed structure. Alternatively, a pressure relief door may be coupled to a frame via a hinge and a latch to the inner fixed structure. The pressure relief assembly may limit deflections between the thrust reverser and the pylon in response to a burst duct. The pressure relief door may release from the latch automatically in response to an over pressurization event.