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.

Landing pads for a drone. One of the landing pads can include a landing area with a first surface configured to receive a second surface of a landing gear of a drone; a docking area i) with a first end adjacent to the landing area and a second opposite end and ii) a docking surface configured to contact the second surface of the landing gear of the drone; a fixed member i) with a third surface adjacent to the second end of the docking area and ii) configured to contact an end of the landing gear of the drone; a moveable member configured to i) move the landing gear across the first surface of the landing area onto the docking surface and ii) secure the landing gear of the drone in place between the docking surface of the docking area and the third surface of the fixed member.

A patient transfer device. According to one embodiment, there is provided a patient transfer device: a support part including a patient seating surface on which a patient is supported; a plurality of propeller parts, connected to the support part, for moving the support part; a power supply unit to be transported while being borne by the user, the power supply unit serving to supply power to the plurality of propeller parts; and a connection member connecting the power supply unit and the support part, wherein the support part is configured to move to follow the power supply unit.

An unmanned aircraft system 100 built off of a purpose-built transmission infrastructure 300 with a power collector 400 riding along the infrastructure 300 connected to a tether 500 that is electrically connected to both the infrastructure 300 through the power collector 400 and also connected to an unmanned aircraft carrying associated electronics that are powered through the tether.

A fan, and a silencer that silences a sound generated by the fan are provided, in which the silencer has a resonance characteristic, the silencer is disposed at a position connected to a sound field space of the sound generated by the fan, and a sum of an absorbance and a reflectivity of the silencer at a resonance frequency is 10% to 43% and a standardized half-width of the silencer is more than 0.05 and 0.25 or less.

An aircraft includes a fuselage airframe and a wing airframe that is subject to flight loads. The fuselage airframe includes fore/aft floor beams having a plurality of floor intercostals laterally extending therebetween and fore/aft roof beams with a plurality of roof intercostals laterally extending therebetween. Each of a plurality of cabin frames extends generally vertically between respective floor and roof beams. The wing airframe includes forward and aft wing spars with a plurality of wing ribs extending therebetween. At least one fuel tank, that is configured to contain a pressurized fuel such as pressurized hydrogen fuel, integrally forms at least a portion of one of the beams, the intercostals, the frames, the spars and/or the ribs such that the fuel tank is subject to the flight loads.

A convertible ducted fan engine and mounting system. The convertible ducted fan engine has a shroud encircling a mechanical fan. The convertible ducted fan engine includes a fluid-propulsion configuration in which the mechanical fan rotates freely with respect to the shroud to produce thrust through fluid flow, and a drive-wheel configuration in which the shroud rotates about the rotational axis. The mounting system includes at least one gimbal ring and may include a circular track system thereby enabling the convertible engine to be oriented in any direction.

An unmanned aerial device having cleaning function includes a fuselage, a washing assembly and two propulsion assemblies. The washing assembly is disposed at a head of the fuselage. The propulsion assemblies are connected to two opposite sides of the fuselage. The two opposite sides are connected to the head. The propulsion assemblies each have an axial direction, and the axial direction is parallel to a direction from a bottom of the fuselage to a top of the fuselage.

Systems, devices, and methods for stopping the rotation of propellers used in unmanned aerial vehicles (UAV) such as drones are disclosed. The propellers are stopped in response to detecting when beams of light adjacent the propellers are blocked.

The present invention relates to rotating equipment, and more specifically, to high efficiency rotating equipment which generates thrust through contra-rotating or produces electricity. The rotating equipment includes: a plurality of propeller modules (10, 20) including a plurality of blades (11, 21) installed inside along a circumferential direction; and a rotary module (40) which rotates the plurality of propeller modules (10, 20) or is rotated.