A system for controlling lighting on an aircraft, the system comprising a number of sensors, a number of aircraft lights, and a processor. The sensors are configured to detect states of the aircraft. The processor is communicatively coupled with the aircraft lights and is configured to determine that a condition is met according to one of the states detected by one of the plurality of sensors and automatically turn on one of the plurality of aircraft lights when the condition is met.

According to one aspect of the present disclosure, a device and technique for unmanned aerial vehicle (UAV) impact monitoring includes a UAV having a propulsion system configured to fly the UAV to a destination; a retention mechanism for retaining and releasing a package carried by the UAV; and an indicator reader module configured to determine a status of an impact indicator attached to the package.

An electronic module assembly for controlling the deployment of one or more airbags in an aircraft includes a power source, a crash sensor configured to produce a signal in response to a crash event and an accelerometer that is configured to produce a signal in response to a crash event. A processor starts a timer upon detection of the signal from the crash sensor. When the processor receives a signal from the crash sensor, the processor is configured to determine if a signal has also been received from the accelerometer and if signals from both the crash sensor and the accelerometer indicate a crash event then the processor reads a memory associated with an inflator. The processor reads a timing value selected for the inflator and fires the inflator when the timer has a value equal to the timing value selected for the inflator.

An on-board emergency response system for a vehicle include a drone being integrated with a vehicle to become separated only when the vehicle is in trouble or experiencing difficulties. Activation of the drone may be from inside the vehicle or remotely via a communication link. The drone is automatically ejected or activated when abnormal conditions inside or outside the vehicle are detected. The drone may provide a backup communication when needed. Once the drone is ejected from the plane, it then follows the vehicle from above at a predetermined distance. It also sends its location, video and images taken inside and outside the vehicle to the command center. If a disaster is inevitable, the drone then tracks the vehicle all the way to its destination. Since the vehicle's actual location is immediately known to the central command, the rescue team can take off in no time, skipping the search altogether.

There is provided a system for predicting loading of a landing gear including, a plurality sensors positioned proximate to the landing gear. The plurality of sensors measure strain applied to the landing gear, and each sensor yielding strain data. The system further includes a processor that receives the strain data from the plurality of sensors and predicts at least one ground load based on strain data. There is further provided a method for predicting loading of a landing gear. The method includes powering a plurality of sensors located proximate to a landing gear structure, interrogating the plurality of sensors via data acquisition circuitry to yield strain data, instructing the data acquisition circuitry as to a sampling rate and data resolution to be used for the interrogating, and, finally, processing the strain data to predict a ground load.

A system and method for operating an aircraft. The system includes a health and usage monitoring system (HUMS) system for sensing health and usage data during flight of the aircraft, and a data transmission unit. The data transmission unit retrieves HUMS data from the HUMS system and generates a trigger signal when the retrieved HUMS data meets a selected criterion, the trigger signal being indicative of a condition of the aircraft. In response to the trigger signal, the data transmission unit transmits the retrieved HUMS data to a remote location.

A health and monitoring system or HUMS mounted within a hollow structural subassembly of an aircraft landing gear assembly, the subassembly having an access port for access to the HUMS without requiring disassembly of the structural subassembly so as to require jacking up the aircraft.

An aircraft undercarriage comprising a shock absorber further comprising first and second portions that are mounted to slide telescopically relative to each other and that can come into internal abutment in the event of the shock absorber being compressed, the undercarriage being fitted with a detector device for detecting the shock absorber coming into internal abutment, which comprises firstly a punch secured to the first portion of the shock absorber or to a portion of the undercarriage that does not slide relative to the first portion of the shock absorber, and secondly a sacrificial piece secured to the second portion of the shock absorber or to a portion of the undercarriage that does not slide relative to the second portion of the shock absorber, the punch and the sacrificial piece being arranged in such a manner that, in the event of the two portions of the shock absorber coming into internal abutment, the punch strikes the sacrificial piece so as to form an indentation therein.

A control system and method of controlling access to storage bins in a vehicle. The system includes a lock configured to be selectively movable between a locked position to prevent access to an interior of the storage bins and an unlocked position to allow access to the interior of the storage bins. A switch is positioned in a cabin of the vehicle. A control circuit is configured to determine an operational status of the vehicle and selectively position the locks. The control circuit can also receive an override signal from the switch and unlock the locks in certain situations.

Methods and apparatus are provided for generating a runway landing alert for an aircraft. The method comprises establishing a Runway Awareness Advisory System (RAAS) envelope for the designated target runway of the aircraft. A track of the aircraft is monitored with reference to a centerline of the target runway. Any deviation by the aircraft from the centerline of the target runway is detected and determined if it is within a margin of error. If the deviation is within the margin of error, an altitude parameter of the RAAS envelope is increased. If the aircraft is determined to still be maneuvering with respect to the centerline of the target runway, the altitude parameter of the RAAS envelope is decreased. Otherwise, an alert is generated if the aircraft is outside of the RAAS envelope.