Provided is an aerial vehicle including an emergency control device through power regulation. The aerial vehicle includes a power unit configured to supply power for the aerial vehicle, a flight control device configured to receive a wireless control signal from control terminal, and control a movement of the aerial vehicle based on the received control signal, and a power regulation device arranged between the power unit and the flight control device and configured to transmit the power from the power unit to the flight control device, wherein the power regulation device includes a communication unit configured to externally receive an emergency control signal through certain radio waves, a verification unit configured to verify whether the received emergency control signal is given according to a predetermined authority, and a power regulation unit configured to cut off the power supplied from the power unit to the flight control device.

A system and method is provided that captures command and control string data during an unmanned vehicle operation. The control string includes user inputs (e.g., mouse inputs, keyboard inputs, etc.) and display outputs (i.e., data displaying to the user via displays). The control string data is captured and stored during the sortie (i.e., a flight) and the control string is preserved (also referred to as impounded) when a mishap occurred during the sortie.

A deployable device mountable on a carrier vehicle and configured to collect situation awareness data. The deployable device includes at least one recorder device configured to collect situation awareness data. The deployable device is capable of being ejected from the carrier vehicle and can be configured to operate as a vehicle and/or be towed by the carrier vehicle. The deployable device can continue collection of situation awareness data after being ejected.

A method for triggering a plurality of emergency measures associated with an aircraft emergency is disclosed. The method includes determining a risk level for an aircraft emergency by evaluating a plurality of flight parameters and/or aircraft parameters using a predefined logic. For each emergency measure of the plurality of emergency measures a threshold is defined and each emergency measure of the plurality of emergency measures is only triggered if the determined risk level exceeds the threshold defined for the emergency measure. Further, a system for use onboard an aircraft for triggering a plurality of emergency measures associated with an aircraft emergency and an aircraft comprising such a system are disclosed.

A method and system for generating an alert report on board an aircraft, comprising an on-board acquiring module configured to acquire data relating to the aircraft, the data originating from sensors and/or equipment installed in the aircraft. An on-board processing module is configured to detect possible anomalies by automatically partitioning the data into a set of homogeneous groups, each anomaly being revealed by a corresponding datum belonging to no homogeneous group. An on-board alert-emitting module is configured to emit an alert report on each detection of an anomaly. An on-board transmitting module is configured to transmit the alert report to the ground and in real-time.

A multi-layered edge computing method for aircraft monitoring and analysis includes providing an aircraft having a plurality of sensors connected to a flight data acquisition unit (FDAU), and providing a processing device having a processor, a non-transitory computer-readable memory, and a transmitter, wherein the processing device is in communication with the FDAU, wherein sensor data stored within the FDAU is communicated to the processing device, wherein, during flight of the aircraft, the processor analyzes the sensor data from the FDAU to detect an occurrence of at least one emergency event. The processing device ranks the at least one emergency event for transmission priority according to sensor type and severity and provides a signal transmitted to a flight control authority upon ranking of the at least one emergency event, wherein the signal has an alert sequence according to the ranking.

A method for triggering a first emergency measure associated with an aircraft emergency comprising the steps of determining a risk level for an aircraft emergency and triggering the first emergency measure if the risk level exceeds a first threshold for the first emergency measure is described and claimed. The risk level is determined by evaluating a plurality of flight parameters and/or aircraft parameters using a predefined logic. The first threshold is adjusted according to a position of the aircraft over ground. Furthermore, a system for use onboard an aircraft for triggering a first emergency measure and an aircraft comprising such a system are disclosed.

Aircraft tracking and emergency location avionics architectures that integrate existing fixed Emergency Locator Transmitter (ELT) installations, their associated aircraft avionics systems and existing flight deck interfaces with an Autonomous Distress Tracker (ADT) transceiver unit in a coupled configuration. Some of the architectures allow the ADT unit and its advanced distress detecting and reporting capabilities to monitor the activation control path for the ELT and the associated ELT activation outputs. Other architectures place the ADT unit and its advanced distress detection capabilities and ground-controlled capabilities in the activation control path for the ELT. Additional architectures entail the connection of an ADT unit to an ELT remote panel on the flight deck of an aircraft.

Presented herein are methods, systems, devices, and computer-readable media for recording and conveying information/data by a device. The device may record and store data associated with a catastrophic or emergency event. The device may transmit and convey data to facilitate locating the device after a catastrophic event. In some embodiments, a device may be configured to be ejected from a vehicle before or during a catastrophic event.

Aircraft tracking and emergency location avionics architectures that integrate existing fixed Emergency Locator Transmitter (ELT) installations, their associated aircraft avionics systems and existing flight deck interfaces with an Autonomous Distress Tracker (ADT) transceiver unit in a coupled configuration. Some of the architectures allow the ADT unit and its advanced distress detecting and reporting capabilities to monitor the activation control path for the ELT and the associated ELT activation outputs. Other architectures place the ADT unit and its advanced distress detection capabilities and ground-controlled capabilities in the activation control path for the ELT. Additional architectures entail the connection of an ADT unit to an ELT remote panel on the flight deck of an aircraft.