A device for selectively trimming a tree, the device configured to aerially travel to tree limbs or tree trunks destined for trimming, the device comprising: a transporting assembly configured to aerially transport the device; a tree interface assembly on which is operatively coupled pair(s) of opposing gripping arms disposed to grip the tree therebetween, the tree interface assembly being operatively coupled to the transporting assembly; a transverse rotator comprising a rotational driver configured to rotate the device circumferentially about a tree limb or tree trunk, the transverse rotator being operatively coupled to the tree interface assembly; a cutting assembly comprising at least one cutting mechanism configured to selectively cut a tree limb or tree trunk in multiple planes; wherein the device, once secured to the tree may travel longitudinally along a tree limb or tree trunk to the desired location for trimming.

To provide an unmanned aerial vehicle that is optimized for freight purposes and that efficiently performs loading and unloading of freight and efficiently performs airframe management. This object is solved by an unmanned aerial vehicle that includes a plurality of propellers. An airframe of the unmanned aerial vehicle includes: a body having a freight chamber that is a hollow portion and that is integral with the body; and a plurality of arms supporting each of the plurality of propellers. A combination of the one arm and the one propeller or plurality of propellers supported by the one arm constitute a retractable propeller. The retractable propeller is partially or entirely storable in the freight chamber.

Transformable unmanned vehicles and related methods are disclosed. An example vehicle includes a body having, a first cap, a second cap spaced from the first cap, and a plurality of segments radially spaced relative to a longitudinal axis of the body. The segments are movable relative to the first cap and the second cap. The vehicle includes a payload supported by the first cap. An actuation system moves the segments relative to the first cap and the second cap to transform the body between a first configuration and a second configuration different than the first configuration.

The present application discloses an aircraft. The aircraft comprises a first wing and a second wing, a fuselage to which the first wing and the second wing are mounted, a first engine operatively mounted to the first wing, and a second engine operatively mounted to the second wing. The aircraft is configured to vertically take-off and land. The first engine and the second engine are used for both (i) vertical take-off and landing, and (ii) horizontal flight

The present application discloses an aircraft. The aircraft comprises a fuselage mount coupled to a first wing and a second wing via a first hinge and a second hinge via a second hinge, a fuselage detachably mounted on the fuselage mount, a first engine nacelle detachably mounted on an end of the first wing distal from the fuselage, and a second engine nacelle detachably mounted on an end of the second wing distal from the fuselage.

The present application discloses a method of assembling or disassembling an aircraft. The assembly method includes a mounting a first engine nacelle to a first wing, mounting a second engine nacelle to a second wing, causing the first wing to be extended relative to a center wing, and causing the second wing to be extended relative to the center wing.

The present application discloses an aircraft. The present application discloses a method of assembling or disassembling an aircraft. The assembly method includes mounting a first engine nacelle to a first wing, mounting a second engine nacelle to a second wing, causing the first wing to be extended relative to a fuselage mount, causing the second wing to be extended relative to the fuselage mount, and mounting the fuselage to the fuselage mount.

An apparatus includes a frame and a plurality of propellers coupled to the frame and configured to produce sufficient thrust to allow the apparatus to hover. Each propeller from the plurality of propellers having a horizontally oriented blade and a first propellor from the plurality of propellors overlapping a second propellor from the plurality of propellers in a vertical plane.

A vertical take-off and loading (VTOL) rotary aircraft or helicopter has eight propellers in a quad propeller arm configuration where each propeller arm has two counter-rotating propellers. Folding propeller arms are designed to allow storage in a single car sized garage. Each propeller may be powered by a three-phase alternating current motor. The main power plant for the aircraft is a gas combustion engine that generates electricity. If the gas engine fails, a battery backup system will safely bring the aircraft down for a controlled landing. The direct current bus is redundant in that even with a gas combustion engine failure the direct current bus battery pack will safely bring down the aircraft. Various embodiments of this invention may also include a landing gear crumple zone designed to soften a hard landing.

A bendable element is formed at least from an inflatable envelope, a first bendable, elongate base plate attached to a first face of the inflatable envelope, a second bendable, elongate base plate, attached to a second face of the inflatable envelope and shorter than the first base plate, and links connecting the first base plate to the second base plate. The links are slack when the inflatable envelope is in a deflated state. The action of inflating the inflatable envelope causes the first and second base plates to bend in a direction of curvature extending from the first base plate to the second base plate, by means of the tensioning of the links such that the links extend along radii of curvature common to the first and second base plates while keeping the second base plate centered longitudinally relative to the first base plate.