A remote piloted aircraft comprising a secondary flight assembly adapted to intervene in case of failure or an emergency of the aircraft, said secondary flight assembly being provided with an additional control unit configured to process flight relevant data and which includes an additional receiver configured to receive commands from the remote pilot by means of a remote control unit, in case of failure or emergency said additional control unit being configured to generate, as a response, an activation command adapted to activate a first device to expel an upper wing placed in a first compartment of the aircraft and to inflate a lower wing housed in a second compartment of the aircraft, and also to generate an interdiction command of the primary propulsion unit, said upper wing being maneuverable by means of a further remote control unit.

A remote piloted aircraft comprising a secondary flight assembly adapted to intervene in case of failure or an emergency of the aircraft, said secondary flight assembly being provided with an additional control unit configured to process flight relevant data and which includes an additional receiver configured to receive commands from the remote pilot by means of a remote control unit, in case of failure or emergency said additional control unit being configured to generate, as a response, an activation command adapted to activate a first device to expel an upper wing placed in a first compartment of the aircraft and to inflate a lower wing housed in a second compartment of the aircraft, and also to generate an interdiction command of the primary propulsion unit, said upper wing being maneuverable by means of a further remote control unit.

Devices and methods of a pod that deploys from an aircraft or vehicle and descends to safely land. The pod is configured to be attached to an aircraft or vehicle. The pod includes walls that extend around and form a contained interior space that houses one or more travelers or cargo containers. During flight of the aircraft or vehicle, the pod deploys from the aircraft or vehicle while at an elevation above ground. A landing location is determined for the pod. While the pod is descending, the pod is steered towards and lands at the landing location.

Devices and methods of a pod that deploys from an aircraft or vehicle and descends to safely land. The pod is configured to be attached to an aircraft or vehicle. The pod includes walls that extend around and form a contained interior space that houses one or more travelers or cargo containers. During flight of the aircraft or vehicle, the pod deploys from the aircraft or vehicle while at an elevation above ground. A landing location is determined for the pod. While the pod is descending, the pod is steered towards and lands at the landing location.

A parafoil system having an adjustable trim angle during flight to control glide slope and descent speed of a parafoil is provided. The parafoil system may include a pulley cluster comprising first and second variable trim pulleys, each having a different diameter. The pulley cluster may be coupled to forward and aft suspension lines of a parafoil canopy such that the pulley cluster may rotate to retract or extend the forward and aft suspension lines to adjust the trim angle during flight. The parafoil system may further include a motor for rotating the pulley cluster to extend or retract the suspension lines to adjust the trim angle during flight. By adjusting the trim angle of the canopy during flight, the glide slope and descent speed of the parafoil system may be controlled.

An aerial payload delivery system uses a cruciform parachute canopy that is connected to base by plurality of suspension lines including an adjustable control line. A control system includes an actuator to selectively adjust the length of the control line. By adjusting the length of the control line, the parachute can be selectively set to glide or descend substantially vertically subject to wind. In an embodiment, the suspension lines also include a short line and a plurality of long lines. The parachute is set to glide by adjusting the control line to be about the same length as the short line and set to vertically descend by adjusting the length of the control line to differ from the short line.

An aerial payload delivery system uses a cruciform parachute canopy that is connected to base by plurality of suspension lines including an adjustable control line. A control system includes an actuator to selectively adjust the length of the control line. By adjusting the length of the control line, the parachute can be selectively set to glide or descend substantially vertically subject to wind. In an embodiment, the suspension lines also include a short line and a plurality of long lines. The parachute is set to glide by adjusting the control line to be about the same length as the short line and set to vertically descend by adjusting the length of the control line to differ from the short line.

A system for payload delivery and drone recovery, wherein the system functions with the use of a lightweight parachute and a directional control module. The system can include a drop system for payload delivery, wherein the drop system releases the parachute and payload upon reaching a target site. The system can also include a recovery system, wherein the recovery system deploys the parachute and steers the failed drone to a target site. A lightweight ram-air parachute is used to provide a lighter steerable parachute system.

A system for payload delivery and drone recovery, wherein the system functions with the use of a lightweight parachute and a directional control module. The system can include a drop system for payload delivery, wherein the drop system releases the parachute and payload upon reaching a target site. The system can also include a recovery system, wherein the recovery system deploys the parachute and steers the failed drone to a target site. A lightweight ram-air parachute is used to provide a lighter steerable parachute system.

Systems, devices, and methods including: a latching mechanism comprising: a first latch configured to attach to a door of an unmanned aerial vehicle (UAV); a second latch configured to attach to a portion of the UAV distal from the first latch; a string connected between the first and second latch, where the string secures the door shut; at least two radio modules in communication with a ground control station; and at least two burn wires in contact with a portion of the string between the first latch and the second latch; where current from a backup battery passes to at least one burn wire when the burn signal is received, where the burn wire causes the connection between the first latch and the second latch to be broken and the door of the UAV is separated from the UAV, and where the parachute is deployed when the door of the UAV is separated from a rest of the UAV.