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.

Provided is a drone with a multiple DOF flight mode according to the present invention. The drone may include: a fuselage in which a battery is mounted and a forward direction is set in an x-axis; a plurality of rotors disposed around the fuselage in four or more, each rotational axis of which is aligned in a z-axis direction; an x-axis tilting mechanism unit formed to tilt the plurality of rotors about an axis parallel to the x-axis; a y-axis tilting mechanism unit formed to tilt the plurality of rotors about an axis parallel to the y-axis; a first drive motor unit driving the y-axis tilting mechanism unit; a second drive motor unit guiding the x-axis tilting mechanism unit; and a control unit configured to implement a plurality of flight modes by controlling the first rotor, the second rotor, the third rotor, the fourth rotor, the first drive motor unit, and the second drive motor unit.

In some examples, a computing device receives, from an unmanned aerial vehicle (UAV), a first image from a first camera on the UAV and a plurality of second images from a plurality of second cameras on the UAV. The plurality of second cameras may be positioned on the UAV for providing a plurality of different fields of view in a plurality of different directions around the UAV. Further, the first camera has a longer focal length than the second cameras. The computing device presents, on a display, a composite image including at least a portion of the first image within a merged image generated from the plurality of second images. The presented composite image enables a user to at least one of: zoom out from the at least one first image to the merged image, or zoom in from the merged image to the at least one first image.

Provided is a control method of a drone with a multiple DOF flight mode according to the present invention. The drone may include a fuselage in which a battery is mounted and a forward direction is set in an x-axis, a plurality of rotors disposed about the fuselage in four or more, each rotational axis of which is aligned in a z-axis direction, an x-axis tilting mechanism unit formed to tilt the plurality of rotors about an axis parallel to the x-axis, a y-axis tilting mechanism unit formed to tilt the plurality of rotors about an axis parallel to the y-axis, a first drive motor unit driving the y-axis tilting mechanism unit, a second drive motor unit guiding the x-axis tilting mechanism unit, and a control unit configured to implement a plurality of flight modes by controlling the first rotor, the second rotor, the third rotor, the fourth rotor, the first drive motor unit, and the second drive motor unit.

In some embodiments, a lift augmentation system for a blown lift aircraft includes a blown lift tailplane operatively coupled to the blown lift aircraft. The blown lift tailplane may include a leading edge and a trailing edge, an upper surface and a lower surface, and a first side and a second side. The lift augmentation system may include one or more tailplane thrust-producing devices on the first side and the second side of the blown lift tailplane operatively coupled to the leading edge of the blown lift tailplane. The one or more tailplane thrust-producing devices on the first side and the second side of the blown lift tailplane may produce a plurality of slipstreams corresponding to each of the tailplane thrust-producing devices. The plurality of slipstreams corresponding to each of the tailplane thrust-producing devices may blow over the upper surface and the lower surface of the blown lift tailplane.

In a general aspect, a handheld controller device includes a housing and a trigger assembly. The housing is configured to be held in the hands of a user. The trigger assembly includes a pair of triggers extending outward from a side of the handheld controller device and configured to move along respective trigger paths. A coupling assembly is disposed inside the housing and connected to the pair of triggers. The coupling assembly is configured to transfer motion between the pair of triggers such that, when either of the triggers moves towards the housing along its respective trigger path, the coupling assembly moves the other trigger an equal distance away from the housing along its trigger path. Circuitry in the housing includes one or more sensors and a microcontroller configured to receive sensor signals and, in response, generate aircraft control data (e.g., for a flight simulation or remotely controlled flyable aircraft).

A method for turning an aerial vehicle such as a drone-type vehicle is provided, according to one embodiment. The method provides for receiving a turning input and detecting a current momentum of the aerial vehicle. The method provides for converting the turning input into a yaw command and calculating a change in yaw associated with the turning input. The method provides for calculating a roll command based on the current momentum of the aerial vehicle and based on the change in yaw associated with the turning input. Further, the method provides for executing the yaw command and the roll command in synchrony, wherein the executing the yaw command and the roll command in synchrony causes the aerial vehicle to perform a turn.

The present disclosure relates to a cargo protection method, device and system, and a non-transitory computer-readable storage medium, relating to the technical field of unmanned aerial vehicles. The method of the present disclosure includes: determining whether an unmanned aerial vehicle is in a falling state or not according to a current acceleration in a vertical direction of the unmanned aerial vehicle and a current vertical distance from the unmanned aerial vehicle to the ground; and opening at least one airbag in a cargo hold of the unmanned aerial vehicle in a case where the unmanned aerial vehicle is in the falling state to protect a cargo in the cargo hold.

A blimp includes a circular disk-shaped envelope filled with a lighter-than-air gas. A gondola is affixed to an underside of the envelope and is disposed at a region directly below a center point of the circle defined by the intersection of the envelope and the horizontal plane. The gondola includes: a horizontally-disposed elongated circuit board that functions as a structural member of the gondola; and a vertical member extending upwardly from the circuit board and having a top that is attached to the underside of the envelope. A thrusting mechanism is affixed to the gondola and is configured to generate thrust. An electronics suite is disposed on and electrically coupled to the circuit board and includes a blimp processor configured to generate control signals that control the thrusting mechanism. A battery is affixed to the gondola and provides power to the electronics suit and the thrusting mechanism.

A flight status inspection system, flight status inspection method and non-transitory computer-readable recording medium storing program inspect the flight status of a flying object (drone) capable of flying through the air. The drone has a gravitational center movement device for moving the position of the gravitational center of the entire drone. In addition, the flight status inspection system has an inspection device for acquiring and storing information about the flight status when moving the position of the gravitational center of the drone during flight, or when changing the flight details during movement of the gravitational center of the drone.