The present invention relates to a method for replacing a signal controlling an actuator in a remote-controlled flying device with another signal. A flight controller supplies control signals to a safety device, and the signal to be replaced may be a signal to be transmitted by the safety device to a speed controller of at least one motor, or to a servo unit controlling the same, or the signal to be replaced may be a signal to be transmitted from the safety device to a servo unit controlling legs, a camera rack, a camera, a stabilizing system or an electric motor of the flying device. A replacement signal is a signal stored in a memory of the safety device. The replacement signal may be capable of controlling the speed controller directly or via the servo unit, in such a way that power transmission to said motor/motors is stopped or reduced, and this motor is/these motors are switched off or its/their rotation is decelerated, or the replacement signal may be capable of controlling said servo unit in such a way that said actuator is moved to a second position. The replacement signal may be a signal to be transmitted from a receiver past a flight controller, capable of controlling the speed controller or servo unit of the motor in such a way that power transmission to the motor is stopped or reduced, or to control said actuator in such a way that this actuator is moved to another position.

The present disclosure relates to a rotorcraft. The rotorcraft according to the present disclosure has a parachute mechanism for releasing a parachute in a predetermined direction and an attitude control means for setting the aircraft to a specific attitude when releasing said parachute. According to such a configuration, the parachute can be deployed in an attitude suitable for its deployment, thereby reducing damage, etc., that may occur when the flying vehicle falls.

The present disclosure relates to a rotorcraft. The rotorcraft according to the present disclosure has a parachute mechanism for releasing a parachute in a predetermined direction and an attitude control means for setting the aircraft to a specific attitude when releasing said parachute. According to such a configuration, the parachute can be deployed in an attitude suitable for its deployment, thereby reducing damage, etc., that may occur when the flying vehicle falls.

The present invention relates;—to a drone comprising a fuselage (1) provided with a carrying means (11, 12) capable of allowing a belly-to-ground flight position and an inverted flight position, at least one propulsion means (2), autonomous navigation instruments and an axial compartment (10) forming a recess incorporated into an upper part of the fuselage in order to receive a parachutist (h) in the lying position, avionics provided with programmable control means coupled to the autonomous navigation instruments and means for releasing said parachutist controlled by said avionics, characterised in that said release means are designed and intended to ensure the release of said parachutist in the inverted flight position, and,—to a piece of airborne intervention equipment.

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.

This invention relates to the use of an automatic safety parachute deployment system for drones (UAVs), which utilizes an airflow trigger that deploys one or more parachutes under certain aerodynamic conditions from the upward airflow during a flight malfunction. The system is mechanically activated without the use of electronics, batteries or an ejection spring which reduces the complexity and weight.

A multicopter (100) having a plurality of propellers (1) is configured to be electrically operated. The multicopter (100) is provided with electric motors (2), at least one main battery (3), a generator (4), an engine (5), and a battery condition detecting section (71). The electric motors (2) drive the propellers (1). The main battery (3) is a first electric power source that supplies the electric power to the electric motors (2). The generator (4) is a second electric power source that supplies the electric power to the electric motors (2). The engine (5) drives the generator (4). The battery condition detecting section (71) detects abnormality of the main battery (3). When the battery condition detecting section (71) detects the abnormality of the main battery (3), the generator (4) supplies the electric power that has been converted from motive power from the engine (5) directly to the electric motors (2).

An automated aircraft recovery system is disclosed. In various embodiments, the system includes an interface configured to receive sensor data; and a control mechanism configured to: perform automatically a recovery action that is determined based at least in part on the sensor data. In various embodiments, the control mechanism may determine an expected state of an aircraft, determine whether a state of the aircraft matches the expected state, and in the event the state of the aircraft does not match the expected state, perform the recovery action.

Various embodiments of the present disclosure relate to a parachute deployment system for an unmanned aerial vehicle (UAV). In some examples, the parachute deployment system includes a base attached to the unmanned aerial vehicle, a deployment tray mechanically connected to the base, an acceleration mechanism for propelling the deployment tray away from the base, a parachute cover releasably secured over the deployment tray, a parachute stowed between the deployment tray and the parachute cover, and a triggering mechanism. Upon activation of the triggering mechanism, the parachute cover is released and the deployment tray is propelled away from the base, which rapidly deploys the parachute away from the UAV.

Systems, apparatuses and methods for recognizing or detecting obstacles are provided. Passive infrared (PIR) sensors may be coupled to movable objects, such as unmanned aerial vehicles (UAVs). PIR sensors may detect and recognize obstacles such as humans and determine or calculate a distance to the obstacles. Based on the distance from the movable object to the obstacle, one or more flight response measures such as collision avoidance maneuvers may be effected or implemented.