An aerial vehicle of a box wing design adapted for vertical takeoff and landing using mounted thrust producing elements. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle uses one or more thrust producing elements on both of the right and the left sides. The aerial vehicle may have one or more front thrust producing elements and one or more rear thrust producing elements on both of the right and the left sides of a main vehicle body.

An aircraft having a high efficiency forward flight mode. The aircraft includes an airframe having at least one wing. A distributed propulsion system is attached to the airframe and includes a first plurality of propulsion assemblies and a second plurality of propulsion assemblies. A flight control system is operably associated with the distributed propulsion system and is operable to independently control each of the propulsion assemblies. The aircraft is configured for thrust-borne lift in a vertical takeoff and landing flight mode and wing-borne lift in the forward flight mode. In the vertical takeoff and landing flight mode, each of the propulsion assemblies is configured to generate vertical thrust. In the forward flight mode, the propulsion assemblies of the first plurality of propulsion assemblies are configured to generate forward thrust and the propulsion assemblies of the second plurality of propulsion assemblies are configured to shut down.

An aircraft having a high efficiency forward flight mode. The aircraft includes an airframe having at least one wing. A distributed propulsion system is attached to the airframe and includes a first plurality of propulsion assemblies and a second plurality of propulsion assemblies. A flight control system is operably associated with the distributed propulsion system and is operable to independently control each of the propulsion assemblies. The aircraft is configured for thrust-borne lift in a vertical takeoff and landing flight mode and wing-borne lift in the forward flight mode. In the vertical takeoff and landing flight mode, each of the propulsion assemblies is configured to generate vertical thrust. In the forward flight mode, the propulsion assemblies of the first plurality of propulsion assemblies are configured to generate forward thrust and the propulsion assemblies of the second plurality of propulsion assemblies are configured to shut down.

A lift rotor arrangement (100) for a VTOL aircraft (200). The lift rotor arrangement (100) comprises: a fairing (6) mounted on a wing segment (10); and first and second rotor blades (17, 18) mounted on a first shaft (4) extending vertically from the fairing (6). The first shaft (4) is movable between an extended position in which the first and second rotor blades (17, 18) are vertically spaced above the wing segment (10) and are rotatable to provide vertical lift, and a retracted position in which the first and second rotor blades (17, 18) are rotationally-fixed with the first rotor blade (17) stowed within the wing segment (10). The blades (17, 18) may be rotatable around an axis substantially perpendicular to the axis of the respective first shaft (4) so as to act as ailerons/elevons in the retracted position.

An unmanned aerial vehicle (UAV)-assisted hanging ring robot for live installation and grounding includes a hanging tray, a wire hanging bracket, a hanging wire, an overturning stay wire, an overturning frame, a support, an electric lock, a walking wheel, a driving motor, a workbench, a clamp seat, a puncture clamp, a tightening mechanism, a remote controller, and a controller. The hanging tray is installed at the bottom of a UAV, one end of the overturning stay wire is connected to the overturning frame, the other end thereof hangs on ground, the driving motor is installed on the overturning frame, the walking wheel is connected to the driving motor, the puncture clamp is installed on the clamp seat, the tightening mechanism is installed on the workbench, and connected to the puncture clamp, and the electric lock, tightening mechanism, driving motor, and remote controller are connected to the controller.

An unmanned aerial vehicle (UAV)-assisted hanging ring robot for live installation and grounding includes a hanging tray, a wire hanging bracket, a hanging wire, an overturning stay wire, an overturning frame, a support, an electric lock, a walking wheel, a driving motor, a workbench, a clamp seat, a puncture clamp, a tightening mechanism, a remote controller, and a controller. The hanging tray is installed at the bottom of a UAV, one end of the overturning stay wire is connected to the overturning frame, the other end thereof hangs on ground, the driving motor is installed on the overturning frame, the walking wheel is connected to the driving motor, the puncture clamp is installed on the clamp seat, the tightening mechanism is installed on the workbench, and connected to the puncture clamp, and the electric lock, tightening mechanism, driving motor, and remote controller are connected to the controller.

Improved closed wing aircraft design and configuration with three wings on either side of the fuselage wherein at least one closed frame is established between the 1st wing (65) and the 2nd wing (67), by using at least one bracing entity. A separate closed frame is established between the 2nd wing (67) and the 3rd wing (71), by using at least one bracing entity. Each of said closed frames defines its own aerodynamic channel. The framework is strong and stiff, the mutually supported parts level out the stress, the load per wing is low. The fuselage is lifted in three points. It is possible to build a very large aircraft of composite materials. The Aspect Ratio is high and the wingspan is relatively short but there are embodiments wherein the 3rd wing has an extended folding tip section.

An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements and a set of tail mounted rotors for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle uses different configurations of its wing mounted rotors and propellers to reduce drag in all flight modes.

Described is an apparatus and method of an aerial vehicle, such as an unmanned aerial vehicle (“UAV”) that can operate in either a vertical takeoff and landing (VTOL) orientation or a horizontal flight orientation. The aerial vehicle includes a plurality of propulsion mechanisms that enable the aerial vehicle to move in any of the six degrees of freedom (surge, sway, heave, pitch, yaw, and roll) when in the VTOL orientation. The aerial vehicle also includes a ring wing that surrounds the propulsion mechanisms and provides lift to the aerial vehicle when the aerial vehicle is operating in the horizontal flight orientation.

A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one tad conduit is fluidly coupled to the generator. First and second fore ejectors are coupled to the main body and respectively coupled to a starboard side and port side of the vehicle. The fore ejectors respectively comprise an outlet structure out of which fluid flows. At least one tail ejector is fluidly coupled to the tail conduit. The tail ejector comprises an outlet structure out of which fluid flows A primary airfoil element includes a closed wing having a leading edge and a trailing edge. The leading and trailing edges of the closed wing define an interior region. The at least one propulsion device is at least partially disposed within the interior region.