The disclosure relates to an unmanned aerial vehicle, wherein a fuel cell system component provides a structural component of the vehicle. In some instances propulsion modules affixed to wings are oriented so as to provide airflow to plates of a fuel cell via air inlets for each fuel cell provided at the forward surface of each wing, a fuel cell system component forming a portion of the body and wherein the air inlets are unblocked during flight, each propulsion module is configured to provide air as an oxidant to a fuel cell via the air inlets.

A lighter than air airship (1) comprising a gas-filled flexible hull (2) which is elongate with a longitudinal axis (1′) and with a front end (4) and a rear end (5), wherein a harness-structure (3) is abutting an outer side of the hull (2) and not perturbing the hull and not extending through the hull, the harness-structure (3) is made of a bendable material and carries a propeller engine (10) for forward thrust of the airship (1), rechargeable batteries (11) for providing electrical power to the propeller engine (10), and a solar panel for providing electrical power to recharge the batteries (11).

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.

Various aspects provide for a solar assembly. The solar assembly may be a mechanical structure that allows many small solar cells to be integrated into the wing design of an aircraft without placing them on the surface area of the wing or the vehicle. Additional aspects may provide for an adjustable solar assembly. The adjustable solar assembly may be configured to be installed into a structure having a structural profile. When installed, the solar assembly may conform to the structural profile such that the structural profile is maintained. The solar assembly may further comprise an adjustable carrier system comprising a plurality of solar cells attached thereto. The adjustable carrier system may be configured to dynamically adjust the orientation of the solar cells so as to maintain an optimal angle with respect to an external light source.

An aeronautical car includes a ground-travel system including a drivetrain; an air-travel system including a detachable portion configured to house a propulsion device configured to provide thrust and to be driven by the drivetrain when the detachable portion is connected to the aeronautical car, and at least one flight mechanism configured to provide lift once the aeronautical car is in motion; and a weather manipulation device. The weather manipulation device may be configured to manipulate at least one aspect of a weather condition while the aeronautical car is in the air.

A manned or unmanned aircraft has a main body with a circular shape and a circular outer periphery. One or more rotor blades extend substantially horizontally outward from the main body at or about the circular outer periphery. In addition, one or more counter-rotation blades extend substantially horizontally outward from said main body at or about the circular outer periphery, but vertically offset from the main rotor blades.

An autonomous unmanned aerial vehicle detecting system for monitoring a geographic area includes an unmanned blimp adapted to hover in air, at least one camera mounted on the blimp to scan at least a portion of the geographic area, a location sensor to determine a location of the blimp, and a controller arranged in communication with blimp, the at least one camera, and the location sensor. The controller is configured to position the blimp at a desired location in the air based on inputs received from the location sensor, and monitor the geographic area based on the images received from at least one camera. The controller is also configured to detect a presence of an unmanned aerial vehicle within the geographic area based on the received images, and determine whether the detected unmanned aerial vehicle is an unauthorized unmanned aerial vehicle based on the received images.

A High Altitude Pseudo Satellite (HAPS) aircraft is disclosed, the aircraft including at least one aeroelastic span loaded fixed wing, an aspect ratio greater than 15 and wing loading less than 6 kg/m.sup.2, where the at least one wing has a plurality of spoilers distributed across the span of the wing and each spoiler being chordwise located adjacent the centre of pressure of the wing. The HAPS aircraft further includes a control system for controlling the spoilers, sensors which allow at least one of the quantity or quantities selected from the group comprising the amount of lift at points or regions along the wing span the pitch and roll at points or regions along the wing span, the bending and torsional strain at points or regions along the wing span, or the net speed and roll and pitch angle of the wing to be determined by the control system, and the spoiler being activatable to reduce the lift experienced by the wing in the location of the spoiler in response to the quantities determined by control system.

An insulation application assembly for applying insulation to a power line employs an open-ended enclosure to partly surround a segment of the power line. The assembly employs an insulation material conveying mechanism to move insulation material from insulation storage to the insulation material applicator connected to the interior surface of the open-ended enclosure.

An external power assist system for an eVTOL aircraft having one or more onboard batteries includes a subsurface power source and a power transfer interface electrically coupled to the subsurface power source. The power transfer interface is movable between various positions including a deployed position and a stowed position. The power transfer interface is configured to transfer power to the onboard batteries of the eVTOL aircraft in the deployed position. The power transfer interface is moved at least partially subsurface in the stowed position.