A multi-axis amphibious copter for flying and cruising at high speeds. The multi-axis amphibious copter includes six propulsion points i.e., four propellors oriented vertically, a coaxial rotor oriented vertically, and a mini turbine thruster on the rear of the aircraft body and configured to propel the multi-axis amphibious copter forward. The multi-axis amphibious copter can land and take off vertically from congested places and can fly at cruising speeds.

Flying body including body portion and a plurality of propellers radially disposed to be laterally symmetrical from body portion is provided with: a plurality of motors respectively rotating the plurality of propellers; a plurality of power storage packs respectively supplying currents to the plurality of motors; and sub power storage pack connected to the plurality of power storage packs by power wirings, respectively. The same number of motors of the plurality of motors are installed on each of the left and right sides, and the same number of power storage packs of the plurality of power storage packs are installed on each of the left and right sides. Sub power storage pack is installed on a lateral center line of body portion.

An aircraft that can improve cruising speed by making the body shape of the airframe (especially, multicopter) into a shape that has less unnecessary positive lift force by the main body and less drag in the cruising posture of the airframe. An aircraft equipped with a plurality of rotary blades including a propeller and a motor, wherein the aircraft comprises a main body with an inverted airfoil shape. The main body has an attack angle that does not generate a lift force or produces a negative lift force during cruising. The main body has a positive attack angle of 12 degrees or less. Further, it is provided with a mounting unit on which a mounted object can be mounted. The mounting unit is connected to the main body via the connection unit.

Various embodiments of a vision-guided unmanned aerial vehicle (UAV) system to identify and collect foreign objects from the surface of a body of water are disclosed herein. A vision system and methodology has been developed to reduce reflections and glare from a water surface to better identify an object for removal. A linearized polarization filter and a specularity-removal algorithm is used to eliminate excessive reflection and glare. A contour-based detection algorithm is implemented for detecting the targeted objects on water surface. Further, the system includes a boundary layer sliding mode control (BLSMC) methodology to reduce and minimize position and velocity errors between the UAV and object in the presence of modeling and parameter uncertainties due to variation in a moving water surface.

An unmanned aerial vehicle (UAV) a fixed frame and a rotating arm pivotably coupled to the fixed frame at a central axis. The fixed frame includes peripheral propellers and corresponding motors for flying the UAV, and a central electronics enclosure for housing electronics used to control the UAV. The rotating arm is between the propellers and configured to rotate with respect to the fixed frame about the central axis. The rotating arm includes magnetic feet at a first end of the rotating arm and configured to perch and magnetically attach the UAV to a ferromagnetic surface, a docking station at the first end and configured to release and dock a releasable crawler, and a battery at a second end of the rotating arm opposite the first end and configured to supply power to the motors and the housed electronics, and to counterbalance the first end about the central axis.

An aircraft is provided. The aircraft includes a ducted wing portion and a fan chamber. The fan chamber is attached to a bottom of the ducted wing portion. A fan assembly is provided in the fan chamber and is operative to blow air through the ducted wing portion. The ducted wing portion is configured to direct air blown by the fan assembly down to provide lift for the aircraft.

An aeronautical vehicle that rights itself from an inverted state to an upright state has a self-righting frame assembly has a protrusion extending upwardly from a central vertical axis. The protrusion provides an initial instability to begin a self-righting process when the aeronautical vehicle is inverted on a surface. A propulsion system, such as rotor driven by a motor can be mounted in a central void of the self-righting frame assembly and oriented to provide a lifting force. A power supply is mounted in the central void of the self-righting frame assembly and operationally connected to the at least one rotor for rotatably powering the rotor. An electronics assembly is also mounted in the central void of the self-righting frame for receiving remote control commands and is communicatively interconnected to the power supply for remotely controlling the aeronautical vehicle to take off, to fly, and to land on a surface.

Systems, methods, and apparatuses for an aerial vehicle (AV). The AV can include a frame structure comprising an upper frame, a lower frame, and bridges connecting the upper frame and the lower frame. The upper frame can include a housing for electrical components. The AV can include a duct extending from the upper frame to the lower frame. The AV can include a motor to rotate the propeller. The AV can include guides located between the bridges and the duct. A portion of the guides can include a non-linear path. The AV can include actuators. The AV can include flaps, coupled to the guides and the actuators, configured to protrude from the lower frame or retract into the frame structure. The flaps can curve along at least one of a horizontal axis or a vertical axis of the flaps. The flaps can overlap with each other when protruded.

A helicopter includes a propulsion system, gimbal assembly, and a controller. The propulsion system includes a first rotor assembly and a second rotor assembly. The first rotor assembly comprises a first motor coupled to a first rotor and the second rotor assembly comprises a second motor coupled to a second rotor. The second rotor is coaxial to the first rotor and is configured to be counter-rotating to the first rotor. The gimbal assembly couples a fuselage of the helicopter to the propulsion system. The controller is communicably coupled to the gimbal assembly and is configured to provide instructions to the gimbal assembly in order to weight-shift the fuselage of the helicopter, thereby controlling movements of the helicopter.

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.