An air-charging unmanned aerial vehicle set is provided, including a charging unmanned aerial vehicle and a functional unmanned aerial vehicle. The charging unmanned aerial vehicle includes a first unmanned aerial vehicle body, a plurality of first propeller units, a rotation stage, a first battery slot and a second battery slot. The first propeller units are disposed on the first unmanned aerial vehicle body. The rotation stage is disposed on the first unmanned aerial vehicle body. The first battery slot and the second battery slot are disposed on the rotation stage. The functional unmanned aerial vehicle includes a second unmanned aerial vehicle body, a plurality of second propeller units, a third battery slot and a battery cover. The second propeller units, the third battery slot and the battery cover are disposed on the second unmanned aerial vehicle body.

A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.

A drone with extendable and rotatable wings and a multiple accessory securing panel is provided. The extendable wings help increase the lift of the drone and reduce the air drag on the drone. The multiple accessory securing panel allows various tools and objects to be temporarily and selectively secured to the drone. The multiple accessories may be secured to the drone by a ground based rotating delivery unit. The drone may have a removable front nose and legs which receive power from a power unit.

A drone with extendable and rotatable wings and a multiple accessory securing panel is provided. The extendable wings help increase the lift of the drone and reduce the air drag on the drone. The multiple accessory securing panel allows various tools and objects to be temporarily and selectively secured to the drone. The multiple accessories may be secured to the drone by a ground based rotating delivery unit. The drone may have a removable front nose and legs which receive power from a power unit.

An aircraft is described with both VTOL (vertical takeoff and landing) capabilities and convention airplane capabilities. A preferred embodiment comprises a fuselage and fixed wing, with one boom on either side of the fuselage. Each boom comprises a tilt rotor on a fore end and a fixed rotor on the aft end. Both rotors can be directed vertically for VTOL capability. During cruise the tilt rotors can be directed forward for thrust and the fixed rotors can be stopped and directed along the boom axis, minimizing drag. The described embodiments have advantages in weight savings and maneuverability compared to other VTOL aircraft.

An aerial vehicle may include a fuselage; and one or more propellers coupled to the fuselage, wherein the aerial vehicle may have at least a taking off or landing state and a cruise state. In response to the aerial vehicle being in the taking off or landing state, an angle between a longitudinal axis of the fuselage and a horizontal plane may be within a first angular range and in response to the aerial vehicle being in the cruise state, an angle between the longitudinal axis of the fuselage and the horizontal plane may be within a second angular range. A maximum value of the second angular range may be less than a minimum value of the first angular range. In response to the aerial vehicle switching between the takeoff or landing state and the cruise state, the fuselage and the propellers may tilt as a whole.

An aerial vehicle may include a fuselage; and one or more propellers coupled to the fuselage, wherein the aerial vehicle may have at least a taking off or landing state and a cruise state. In response to the aerial vehicle being in the taking off or landing state, an angle between a longitudinal axis of the fuselage and a horizontal plane may be within a first angular range and in response to the aerial vehicle being in the cruise state, an angle between the longitudinal axis of the fuselage and the horizontal plane may be within a second angular range. A maximum value of the second angular range may be less than a minimum value of the first angular range. In response to the aerial vehicle switching between the takeoff or landing state and the cruise state, the fuselage and the propellers may tilt as a whole.

A system includes a detector attachment member and a communication system. The detector attachment member includes a first end configured to be coupled to an unmanned aerial vehicle; a second end configured to be coupled to a detector; and a body extending between the first end and the second end, the body of a length selected such that an interference of the unmanned aerial vehicle at the detector is less than an interference threshold. The detector attachment member also includes a lift system coupled to the body. The communication system is coupled to the detector attachment member and is configured to provide communication between the unmanned aerial vehicle and the detector.

A system includes a detector attachment member and a communication system. The detector attachment member includes a first end configured to be coupled to an unmanned aerial vehicle; a second end configured to be coupled to a detector; and a body extending between the first end and the second end, the body of a length selected such that an interference of the unmanned aerial vehicle at the detector is less than an interference threshold. The detector attachment member also includes a lift system coupled to the body. The communication system is coupled to the detector attachment member and is configured to provide communication between the unmanned aerial vehicle and the detector.

An unmanned aerial vehicle (UAV) adapted for transit in and deployment from a projectile casing is provided. The UAV includes a wing assembly coupled to the projectile casing and the wing assembly moveable between a closed position and a deployed position. The UAV further includes a propulsion system including at least one rotor disposed on the wing assembly to generate lift, wherein in the closed position, the wing assembly is substantially integral with the projectile casing and in the deployed position, the wing assembly is extended outwards from the projectile casing.