The invention relates to an aircraft (1). Said aircraft (1) is characterized by a wing (2) which, viewed in section, is delimited on one side by a first profiled surface (4), which is at the bottom when the aircraft (1) is operated as intended, and on the other side by an upper second profiled surface (5), which merges at an aerofoil transition point (6) with the first profiled surface (4), wherein the first profiled surface (4) surrounds at least one air inlet opening (7), and the second profiled surface (5) surrounds at least one air outlet opening (8), and the aircraft (1) comprises a drive apparatus (12) with an air delivery apparatus (1), which is provided and designed for sucking air through the at least one air inlet opening (7) and for discharging the intake air through the at least one air outlet opening (8), wherein the at least one air outlet opening (8) is overlapped at least in part by a deflecting element (15) which, together with the second profiled surface (5), delimits an air outlet gap (16) which is flow-connected to the air outlet opening (8). The invention also relates to a method for operating an aircraft (1).

One embodiment is an aircraft including at least one propulsion assembly; a cargo area for receiving payload to be transported by the aircraft; and a control system for determining characteristics of the received payload; automatically determining optimal control gains for operating the aircraft including the payload based on the determined payload characteristics; and providing control signals to at least one of the at least one propulsion assembly and a control assembly of the aircraft to control operation of the at least one propulsion assembly in accordance with the determined optimal control gains.

An apparatus configured with two subsystems comprising a torus tube, linear flow, and turboplant assemblies that form of cavity for externally supplied and rotating subsonic working fluid. The working fluid rotation is provided by turboplant assemblies with throttle control. The rotating working fluid inside the cavities will conserve angular momentum. As a result of the conservation of angular momentum, poinsot flow fields are seen within the working fluid. A stable, resultant force is generated from the pressure and area forces inside the cavity. The apparatus usage is either with manual operation or as an unmanned, autonomous vehicle.

A ring-shaped airfoil aircraft capable of taking off and landing vertically, and hovering, comprising: a fuselage, a cockpit; a passenger cabin, a power bay, a tapered tail rudder, a ring-shaped airfoil; a flight controller. The ring-shaped airfoil aircraft has the flying abilities for vertical takeoff and landing and hovering at a fixed altitude of multiaxial rotary wing powered aircraft, but compared with multiaxial rotary wing powered aircraft, its flight attitude is hardly in by air side flow, the flight attitude is more reliable. In addition, it can implement the airspeed of fixed wing ducted aircraft, and the flight energy consumption is much less than the existing fixed wing ducted aircraft, and its takeoff and landing are free of runways. The ring-shaped airfoil aircraft can obtain the lift for aircraft, reduce the drag to aircraft and enhance its flight safety performance.

Whether an internal defect is present in an inspection target is readily judged. Provided is an inspection method for an inspection target that is a layered structure including an FRP material and/or a structure made of resin, the method including the steps of: tapping, with a tapping tool, an inspection target area on a surface of the inspection target; detecting, by an accelerometer mounted to the tapping tool, an acceleration signal corresponding to acceleration of the tapping tool due to reaction force against the tapping; recording waveform data about the detected acceleration signal; creating a contour map corresponding to the inspection target area, based on the recorded waveform data; displaying the contour map on a display unit; and judging whether an internal defect is present in the inspection target, based on the contour map displayed on the display unit.

A disc-type vertical take-off and landing aircraft includes the following. A skirt widens toward the bottom. A disc-shaped rotor is positioned on a lower side of the skirt and rotates with relation to the skirt. A plurality of blades are provided standing on an upper surface of the rotor and are positioned radially from a center of the rotor. A cutout is formed in each of the plurality of blades. When the rotor rotates, centrifugal force causes an airflow along the blade rotating with the rotor, the airflow swirls in a spiral by a flow of air flowing over the cutout of the blade in a direction substantially orthogonal to the blade, the airflow flows in a radial direction of the rotor along the blade while swirling in the spiral, and the airflow ejected downward by the skirt causes ascending.

The present disclosure relates to a drone with a wind guide, including a body, a single central inlet unit accommodated in the body, and configured to introduce wind therein, at least two pairs of wind guides, and at least four connecting ducts. Each wind guide is spaced apart from the body, and each connecting duct is connected with a respective wind guide of the at least two pairs of wind guides. The connecting duct is configured to transmit the wind introduced from the single central inlet unit to the connected respective wind guide.

This disclosure describes a configuration of an aerial vehicle, such as an unmanned aerial vehicle, in which one or more of the propellers are positioned within a duct that includes an active airflow channel within the interior of the duct. The active airflow channel actively moves within the duct so that it remains aligned with the tips of the blades of the propeller within the duct. As the propeller and the active airflow channel rotate, at least some of the airflow structures (e.g., vortices) shed from the blades of the propeller are collected by the active airflow channel and channeled away from the propeller so that a following blade of the propeller does not pass through the collected airflow structures.

A vehicle includes a propulsion system using one or more impellers as opposed to propellers. The impellers impart circumferential and radial velocity components to the working fluid, which may be air or water. The air is deflected by counter-vortex chambers in a shroud to convert the circumferential and radial velocity to an axial velocity aligned with the axis of rotation of the impeller.

The Flying Machine will be capable of flying and balancing with Automatic Balancing control system to keep itself flying while in motion or stationary using gyroscopes and computers, and propelled by motors and vector jets to be able to fly supersonic or subsonic depending on the designee needs, speed or carrying weights and able to fly or come to a complete stop without losing its balance using sensors so that the ground reaction force exactly balance all the other internal and external forces it experiences, such as gravitational if leaning, inertial or centrifugal