An unmanned aerial vehicle includes multiple rotor arms; a rotor disposed at an end of each of the multiple rotor arms; and an adjustment component configured to enable a first rotor arm to move relative to a second rotor arm.

A folding wing tip system of an aircraft includes a latch pin actuator having a primary mechanical lock and a secondary hydraulic lock. The mechanical lock may include a lock cam movable between a lock position, in which the lock cam engages the latch pin, and an unlock position, in which the lock cam is disengaged from the latch pin, and a first lock actuator mechanically coupled to the lock cam and configured to provide a bias force pushing the lock cam toward the lock position. The hydraulic lock may be disposed in an unlatching hydraulic line and has an initial state, in which fluid flow through the unlatching hydraulic line is blocked thereby to hold the latch pin in the latched position, and an open state, in which fluid flow through the unlatching hydraulic line is permitted thereby to permit retraction of the latch pin to the unlatched position.

Disclosed herein is one embodiment of a thrust system that includes at least one modular thrust unit and at least one control module. The at least one modular thrust unit includes a base that is made from structural members that are inter-connectable in a plurality of different structural configurations. The at least one modular thrust unit further includes at least one thrust generator coupleable to the base in a thrust configuration and at least one power source operable to deliver power to the at least one thrust generator. The at least one control module is coupleable to the at least one modular thrust unit and operable to control at least one of the at least one thrust generator and the at least one power source.

A fact checking system utilizes social networking information and analyzes and determines the factual accuracy of information and/or characterizes the information by comparing the information with source information. The social networking fact checking system automatically monitors information, processes the information, fact checks the information and/or provides a status of the information, including automatically modifying a web page to include the fact check results. The fact checking system is able to be implemented utilizing a drone device.

According to various embodiments, there may be provided a monocopter. The monocopter may include a body chassis. The monocopter may further include a wing structure extending from the body chassis, the body chassis being at a root of the wing structure. The wing structure may include a plurality of rigid wing segments distributed along a spanwise direction extending between the root and a tip of the wing structure. The wing structure may further include a plurality of flexible wing segments, each flexible wing segment adjoining a pair of adjacent rigid wing segments of the plurality of rigid wing segments. The monocopter may further include a propulsion unit coupled to a rigid wing segment of the plurality of rigid wing segments between a midspan of the wing structure and the tip of the wing structure.

According to various embodiments, there may be provided a monocopter. The monocopter may include a body chassis. The monocopter may further include a wing structure extending from the body chassis, the body chassis being at a root of the wing structure. The wing structure may include a plurality of rigid wing segments distributed along a spanwise direction extending between the root and a tip of the wing structure. The wing structure may further include a plurality of flexible wing segments, each flexible wing segment adjoining a pair of adjacent rigid wing segments of the plurality of rigid wing segments. The monocopter may further include a propulsion unit coupled to a rigid wing segment of the plurality of rigid wing segments between a midspan of the wing structure and the tip of the wing structure.

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.