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.

A roadable VTOL flying vehicle having a road-configuration and a flight-configuration. The roadable VTOL flying vehicle includes a roadable vehicle; at least one rotor having at least one blade, the rotor is rotatably attached to an upper section of the roadable vehicle of the flying vehicle; at least one motor configured to operatively rotate the least at least one rotor; at least one angular position sensor configured to detect the angular position of each of the at least one rotor; and a vehicle control sub-system configured to affect automatic transformation of the flying vehicle from the road-configuration to the flight-configuration and from the flight-configuration to the road-configuration, wherein the vehicle control sub-system is configured bring the at least one rotor into a parking state, when in road-configuration.

A roadable VTOL flying vehicle having a road-configuration and a flight-configuration. The roadable VTOL flying vehicle includes a roadable vehicle; at least one rotor having at least one blade, the rotor is rotatably attached to an upper section of the roadable vehicle of the flying vehicle; at least one motor configured to operatively rotate the least at least one rotor; at least one angular position sensor configured to detect the angular position of each of the at least one rotor; and a vehicle control sub-system configured to affect automatic transformation of the flying vehicle from the road-configuration to the flight-configuration and from the flight-configuration to the road-configuration, wherein the vehicle control sub-system is configured bring the at least one rotor into a parking state, when in road-configuration.

Methods and apparatus are disclosed for deployable wing portions of an aircraft. An example method of deploying an aircraft includes separating the aircraft from a launch vehicle, the aircraft having a wing pivotably coupled to a fuselage, rotating, about an axis of rotation, the wing relative to the fuselage from a first rotational orientation to a second rotational orientation different from the first rotational orientation, wherein, in the first rotational orientation, the wing extends along a direction that substantially aligns with a longitudinal axis of the fuselage, and extending the wing in a lateral direction away from the fuselage in the second rotational orientation.

Methods and apparatus are disclosed for deployable wing portions of an aircraft. An example method of deploying an aircraft includes separating the aircraft from a launch vehicle, the aircraft having a wing pivotably coupled to a fuselage, rotating, about an axis of rotation, the wing relative to the fuselage from a first rotational orientation to a second rotational orientation different from the first rotational orientation, wherein, in the first rotational orientation, the wing extends along a direction that substantially aligns with a longitudinal axis of the fuselage, and extending the wing in a lateral direction away from the fuselage in the second rotational orientation.

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 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.

In one embodiment, a wing for an unmanned aerial vehicle is described. The unmanned aerial vehicle includes a first body of the wing with a first end proximate a body of the vehicle. A second end is opposite the first end. A first joint is on the first end of the first main body of the wing. The joint rotatably couples the wing to the vehicle. A second joint is on the second end of the vehicle. A second body of the wing is rotatably coupled to the first body via the second joint.

In one embodiment, a wing for an unmanned aerial vehicle is described. The unmanned aerial vehicle includes a first body of the wing with a first end proximate a body of the vehicle. A second end is opposite the first end. A first joint is on the first end of the first main body of the wing. The joint rotatably couples the wing to the vehicle. A second joint is on the second end of the vehicle. A second body of the wing is rotatably coupled to the first body via the second joint.

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.