An air transport vehicle that capitalizes on the strengths and complexities of a fixed and rotary winged aircraft. The air transport vehicle comprises a body aerodynamically designed to avoid substantial drag. The vehicle has a plurality of rotors configured to generate vertical thrust with a rear rotor configured to generate forward thrust. Additionally, each of the rotors are connected to the fixed wing elements and the fixed wing is positioned about the center of mass of the fuselage. Furthermore, each of the rotors are positioned at a fixed tilt angle such that the stability of the vehicle is maintained in a number of different flight configurations.

A helicopter includes a propulsion system, gimbal assembly, and a controller. The propulsion system includes a first and second rotor assembly, wherein the first rotor assembly comprises a first motor coupled to a first rotor, the first rotor comprising a plurality of first fixed-pitch blades and the second rotor assembly comprises a second motor coupled to a second rotor, the second rotor comprising a plurality of second fixed-pitch blades. The second rotor is coaxial to the first rotor and is configured to be counter-rotating to the first rotor. The controller is communicably coupled to the gimbal assembly and is configured to provide instructions to at least one of the first or second gimbal motors in order to orient the plurality of first and second fixed-pitch blades into a position that permits wind to rotate the first and second fixed-pitch blades and thereby charge the power source.

An unmanned aerial vehicle is described having a support frame, a sensor arrangement consisting of a sensor array including at least one sensor, the sensor array having a limited detection field of up to approximately 90 degrees. The at least one sensor is fixedly mounted to the support frame. The at least one sensor is arranged in a flight direction of the unmanned aerial vehicle. The unmanned aerial vehicle further includes a holding structure having a camera holder. The holding structure is mounted to the support frame. The holding structure is configured to provide a continuous 360 degree movement of the camera holder. The unmanned aerial vehicle further includes a first circuit configured to receive sensor data from the at least one sensor. The first circuit is further configured to determine obstacle avoidance data based on the sensor data. The unmanned aerial vehicle further includes a second circuit configured to receive image data from a camera mounted in the camera holder. The second circuit is further configured to determine holding structure control data to control movement of the holding structure based on the image data.

Systems, apparatuses, and methods are provided herein for stabilizing an unmanned aerial system. An apparatus for stabilizing an unmanned aerial system comprises a ring member and a pair of attachment members each having a first end and a second end, the first end being configured to attach to a multicopter and a second end being coupled to the ring member. Wherein the pair of attachment members holds the ring member such that a plane of a circumference of the ring member is generally parallel to blades of the multicopter.

A method for controlling a landing gear of an unmanned aerial vehicle (UAV) includes detecting whether a relative-to-ground height of the UAV is greater than a height threshold, where the relative-to-ground height is a vertical height of the UAV with respect to an object; and in response to the relative-to-ground height being not greater than the height threshold and the UAV having not lowered the landing gear, adjusting the relative-to-ground height to the height threshold or above, and lowering the landing gear.

An aerial vehicle having a single wing is configured for vertical-flight and forward-flight operations. The wing has a substantially high aspect ratio. The aerial vehicle includes tilt motor assemblies disposed at a forward end and an aft end of a fuselage. The tilt motor assemblies are configured to orient motors and rotors vertically, horizontally, or at any angle between vertical and horizontal. A pair of parallel booms are mounted beneath the wing on either side of the fuselage. Each of the booms has at least one vertically oriented motor and rotor associated therewith, and a vertical fin extending thereunder. Additionally, a forward tilt motor assembly includes a rotatable extension that is deployed when the motor assembly is configured for vertical flight, enabling the aerial vehicle to land on the vertical fins and the landing rotatable extension.

A transformable apparatus includes one or more components configured to be movable relative to another component of the transformable apparatus, a trigger mechanism configured to initiate a transformation of the transformable apparatus between a vehicle configuration and a handheld configuration at least in part by causing a movement of the one or more components relative to the other component, and one or more propulsion units configured to effect self-propulsion of the transformable apparatus when the transformable apparatus is in the vehicle configuration. The transformable apparatus is configured to be held by a human hand when in the handheld configuration.

A method for destroying enemy's targets is disclosed which comprises the following steps: (a) carrying a multicopter drone in a backpack of a first soldier; (b) removing the multicopter drone from the backpack, unfolding, and coupling a missile to the multicopter drone; (c) remote controlling the multicopter drone to search for the enemy' targets using a remote control; and (d) launching the missile from the multicopter drone when the enemy' targets are detected.

A method for destroying enemy's targets is disclosed which comprises the following steps: (a) carrying a multicopter drone in a backpack of a first soldier; (b) removing the multicopter drone from the backpack, unfolding, and coupling a missile to the multicopter drone; (c) remote controlling the multicopter drone to search for the enemy' targets using a remote control; and (d) launching the missile from the multicopter drone when the enemy' targets are detected.

Provided is a flight device that can surely perform transformation operations of legs supporting a fuselage base in landing. A flight device 10 includes: a fuselage base 14; a first leg 26 provided on the fuselage base 14 and transformable between a flight state and a landing state; a second leg 27 provided on the fuselage base 14 as a separate body from the first leg 26 and transformable between the flight state and the landing state; a first drive unit 281 and a second drive unit 282 configured to drive transformation operations of the first leg 26 and the second leg 27; and an operation interconnecting mechanism 16 configured to interconnect the first leg 26 and the second leg 27 in terms of operation.