The present invention relates to an electronic test device for at least one avionic function to be tested, intended to be embedded in an aircraft, the aircraft comprising at least one avionic equipment item, the test device being intended to be connected to the at least one avionic equipment item and comprising: an acquisition module, configured to acquire flight data from the at least one avionic equipment item, and a computing module, configured to compute simulated output data, from acquired flight data and via an implementation of the avionic function to be tested, the avionic function to be tested being able, from the flight data, to deliver the output data.

The present disclosure provides systems and methods for guiding a vertical takeoff and landing, VTOL, vehicle to an emergency landing zone. The systems and methods include determining, via at least one processor, candidate landing zone data by interrogating an emergency landing zone database based at least on VTOL vehicle location, the candidate landing zone data representing a list of candidate emergency landing zones. A target emergency landing zone is selected from the list of candidate emergency landing zones based at least on VTOL vehicle related issues including at least one of unanticipated yaw issues, ground effect issues and modified trend vector issues, thereby providing target emergency landing zone data. Guidance for the VTOL vehicle is determined based on the target emergency landing zone data.

This application discloses a drone control method and device and a drone and pertains to the technical field of drone control. The method includes: monitoring a running status of each power motor in a drone; determining according to the running status of each power motor whether the drone is in a crashed state; and controlling the drone to alarm when determining that the drone is in the crashed state. The drone control method and device and the drone can rapidly locate a crashed drone, greatly increasing the probability of finding back the crashed drone.

This application discloses a drone control method and device and a drone and pertains to the technical field of drone control. The method includes: monitoring a running status of each power motor in a drone; determining according to the running status of each power motor whether the drone is in a crashed state; and controlling the drone to alarm when determining that the drone is in the crashed state. The drone control method and device and the drone can rapidly locate a crashed drone, greatly increasing the probability of finding back the crashed drone.

An aircraft landing event system is disclosed including a processor, the processor being configured to receive aircraft braking performance information from a plurality of aircraft that have performed a landing event on a particular runway. The processor is configured to determine an aircraft braking performance indicator on the basis of the aircraft braking performance information of the plurality of aircraft, and communicate the aircraft braking performance indicator to an aircraft landing system of an approaching aircraft that is about to perform a landing event on the particular runway.

An aircraft landing event system is disclosed including a processor, the processor being configured to receive aircraft braking performance information from a plurality of aircraft that have performed a landing event on a particular runway. The processor is configured to determine an aircraft braking performance indicator on the basis of the aircraft braking performance information of the plurality of aircraft, and communicate the aircraft braking performance indicator to an aircraft landing system of an approaching aircraft that is about to perform a landing event on the particular runway.

Methods and systems are provided for runway overrun alerts for an aircraft using manually entered parameters for a non-standard runway. The method includes accessing an interface for an enhanced ground proximity warning system (EGPWS). The following parameters are then manually entered: identification of the non-standard runway; a displaced threshold of the non-standard runway; surface conditions of the non-standard runway; a declared length of the non-standard runway; and availability of thrust reversers on the aircraft. The parameters for the aircraft to safely land and stop on the non-standard runway are calculated with the EGPWS. An alert with the EGPWS is generated if the stopping point of the aircraft is near or beyond the end of the non-standard runway.

Methods and systems are provided for runway overrun alerts for an aircraft using manually entered parameters for a non-standard runway. The method includes accessing an interface for an enhanced ground proximity warning system (EGPWS). The following parameters are then manually entered: identification of the non-standard runway; a displaced threshold of the non-standard runway; surface conditions of the non-standard runway; a declared length of the non-standard runway; and availability of thrust reversers on the aircraft. The parameters for the aircraft to safely land and stop on the non-standard runway are calculated with the EGPWS. An alert with the EGPWS is generated if the stopping point of the aircraft is near or beyond the end of the non-standard runway.

A microwave-based radio system for realising a precise landing approach (MLS), characterised in that an azimuth antenna transmitter and/or an elevation signal transmitter and/or a DME transmitter, and preferably all three said transmitters, are placed aboard an unmanned aerial vehicle, and in particular on a drone. The object of the disclosure is also a method for realising a precise landing approach using such a system.

Methods and systems are provided for guiding or otherwise assisting operation of an aircraft when diverting from a flight plan. One method involves determining a gliding trajectory for the aircraft based at least in part on a current altitude of the aircraft, providing a graphical representation of the gliding trajectory for the aircraft, identifying a plurality of landing locations within a range defined by the gliding trajectory from the aircraft, and for each landing location of the plurality of landing locations, providing a graphical representation of a respective landing location with respect to the gliding trajectory at a respective altitude associated with the respective landing location and at a respective distance with respect to a graphical representation of the aircraft corresponding to a respective geographic distance between a current location of the aircraft and the respective landing location.