Provided is an actuator apparatus including a positioning actuator device configured to position a first carrier member of the actuator apparatus. The positioning actuator device includes a first hydraulic fluid actuator having a first clamping means and a second hydraulic fluid actuator having a second clamping means, wherein the first and second hydraulic fluid actuator are configured to alternately clamp around a guide arrangement for moving the positioning actuator device along the guide arrangement. The first carrier member is provided with a first coupling member configured to be releasable coupled to the positioning actuator device. A method of positioning a first carrier member by means of the positioning actuator device is provided.

Systems, devices, and methods including an unmanned aerial vehicle (UAV); one or more inner wing panels of the UAV; one or more outer wing panels of the UAV; at least one inboard propeller attached to at least one engine disposed on the one or more inner wing panels; at least one tip propeller attached to at least one engine disposed on the one or more outer wing panels; at least one microcontroller configured to: determine an angular position of the at least one inboard propeller; and send a signal to halt rotation of the at least one inboard propeller such that the at least one inboard propeller is held in an attitude that provides for clearance of the propeller blade to the ground upon landing.

Systems, devices, and methods including an unmanned aerial vehicle (UAV); one or more inner wing panels of the UAV; one or more outer wing panels of the UAV; at least one inboard propeller attached to at least one engine disposed on the one or more inner wing panels; at least one tip propeller attached to at least one engine disposed on the one or more outer wing panels; at least one microcontroller configured to: determine an angular position of the at least one inboard propeller; and send a signal to halt rotation of the at least one inboard propeller such that the at least one inboard propeller is held in an attitude that provides for clearance of the propeller blade to the ground upon landing.

A vehicle comprising a morphing wing and a body is disclosed. The aircraft is configured to transform from a first configuration into a second configuration for ascent or descent of the aircraft. The drag force and lift force on the aircraft in the second configuration are less than in the first configuration. Transforming from the first to the second configuration comprises: contracting the wing within a geometric plane defined by the wing, and rotating the outer edge of the wing downwards, out of the geometric plane.

A vehicle comprising a morphing wing and a body is disclosed. The aircraft is configured to transform from a first configuration into a second configuration for ascent or descent of the aircraft. The drag force and lift force on the aircraft in the second configuration are less than in the first configuration. Transforming from the first to the second configuration comprises: contracting the wing within a geometric plane defined by the wing, and rotating the outer edge of the wing downwards, out of the geometric plane.

Systems, devices, and methods including an unmanned aerial vehicle (UAV); one or more inner wing panels of the UAV; one or more outer wing panels of the UAV; at least one inboard propeller attached to at least one engine disposed on the one or more inner wing panels; at least one tip propeller attached to at least one engine disposed on the one or more outer wing panels; at least one microcontroller configured to: determine an angular position of the at least one inboard propeller; and send a signal to halt rotation of the at least one inboard propeller such that the at least one inboard propeller is held in an attitude that provides for clearance of the propeller blade to the ground upon landing.

Systems, devices, and methods including an unmanned aerial vehicle (UAV); one or more inner wing panels of the UAV; one or more outer wing panels of the UAV; at least one inboard propeller attached to at least one engine disposed on the one or more inner wing panels; at least one tip propeller attached to at least one engine disposed on the one or more outer wing panels; at least one microcontroller configured to: determine an angular position of the at least one inboard propeller; and send a signal to halt rotation of the at least one inboard propeller such that the at least one inboard propeller is held in an attitude that provides for clearance of the propeller blade to the ground upon landing.

A flying vehicle with a flight part connected to a plurality of rotor wing parts and a main wing, wherein the main wing is configured such that the lift produced by the main wing during landing is reduced compared to the lift produced by the main wing during cruising. Furthermore, the main wing is fixed at a forward tilt with respect to the flight part. Furthermore, the rotor wing is connected at an angle that produces propulsion and lift during cruise. Furthermore, the rotor blades are connected at an angle that generates propulsive force during cruise.

A flying vehicle with a flight part connected to a plurality of rotor wing parts and a main wing, wherein the main wing is configured such that the lift produced by the main wing during landing is reduced compared to the lift produced by the main wing during cruising. Furthermore, the main wing is fixed at a forward tilt with respect to the flight part. Furthermore, the rotor wing is connected at an angle that produces propulsion and lift during cruise. Furthermore, the rotor blades are connected at an angle that generates propulsive force during cruise.

Present invention relates to a lift assembly (300) in an aerial vehicle. The lift assembly (300) comprises a wing (102) and at least a vertical rotor (118) disposed below the wing (102). A vertical axis (121) of the vertical rotor (118) is positioned within a wing span of the wing (102). The vertical rotor (118) is operational during forward flight of the aerial vehicle. A placement distance (122) between the leading edge (108) and the vertical axis (121) of the vertical rotor (118) is a factor of RPM of the rotor (118), angle of attack (116) of the wing, and a wing chord (117). The lift assembly (300) produces enhanced lift higher than the sum of lift produced by the wing (102) and the rotor (118) individually, which enables the provision of small wings and hence incur reduced drag.