According to various embodiments, there is provided a multi-rotor aircraft for a multiple payload delivery comprising a morphing mechanism having an airframe and at least three support arms coupled to the airframe wherein each support arm is configured for rotating about a vertical axis of the aircraft relative to the morphing mechanism. The aircraft further includes a payload bay coupled to the morphing mechanism for engaging and disengaging a plurality of payloads and a control system communicatively coupled with the morphing mechanism and the payload bay, wherein the control system is configured to cause each of the support arms to rotate by a predetermined angle about the vertical axis of the aircraft, wherein the predetermined angle is determined based on a change in distance between a neutral point and a centre of gravity of the aircraft.

A thruster controller is used in a flying device that has at least two thrusters and a main controller that outputs an instruction value to the thruster for controlling a thrust of the thruster. The thruster controller includes an instruction value obtainer and an instruction value generator. The instruction value obtainer obtains an instruction value that is output from the main controller to the thruster based on an assumption that a propeller pitch is fixed. The instruction value generator outputs, to a pitch changing mechanism of the thruster, a propeller pitch instruction value generated from the obtained instruction value for setting the propeller pitch, and outputs, to a motor, a corrected rotation number instruction value for setting a rotation number of the motor by correcting the instruction value based on the propeller pitch instruction value.

Systems and methods related to passive variable pitch propellers are described. For example, an aerial vehicle may include one or more passive variable pitch propellers, and such propellers may include one or more passively movable propeller blades having respective hinges, flexible joints, or torsionally flexible joints. Based at least in part on current flight configurations, required thrust, and/or desired advance ratios, the passively movable propeller blades may modify their coning angles and/or pitches, such that the passive variable pitch propellers may operate with improved efficiency in two or more flight configurations. For example, in a VTOL flight configuration, the passive variable pitch propellers may have increased coning angles and decreased pitches, whereas in a horizontal flight configuration, the passive variable pitch propellers may have decreased coning angles and increased pitches.

The present invention provides an unmanned aerial vehicle that can maintain stability by changing positions of rotating rotors when one of the rotating rotors malfunctions, and a method for controlling stability of the unmanned aerial vehicle. The unmanned aerial vehicle includes: a main body; a plurality of support bars that are arranged while forming an angle with each other along a circumferential direction of the main body and extended to an outer side from the main body; a plurality of rotating rotors that are respectively provided to the support bars and generate thrust; motors that are respectively connected to the rotating rotors to drive the rotating rotors; drivers that change positions of the respective rotating rotors along the circumferential direction of the main body by moving the support bars with respect to the main body; and a controller that maintains horizontal stability of the main body by controlling the drivers.

The present technology is directed to a remotely controlled aircraft that can be transported without the risk of damaging certain components, such as the arms and/or propellers. In one non-limiting example, the remotely controlled aircraft technology described herein provides a housing that allows the arms of the remotely controlled aircraft to extend and/or retract through openings in the housing. When retracted, the arms and propellers are protected within an area of the structure of the housing, and when extended, the arms and propellers are operable to make the remotely controlled aircraft fly.

An aircraft, a method of controlling the aircraft, and a control system for the aircraft has a fuselage and tilt-wing movable relative to the fuselage. A plurality of main propulsors coupled to main propellers that is coupled to the tilt-wing, which are configured to provide a first maximum amount of thrust. A plurality of auxiliary propulsors coupled to auxiliary propellers that are spaced apart from the tilt-wing, which are configured to provide a variable amount of thrust. A controller signals the main propulsors to operate at the first maximum amount of thrust when the tilt-wing moves from the cruise position to the transition position, and signals the auxiliary propulsors to operate at the variable amount of thrust when the tilt-wing is in the transition position in which the first maximum amount of thrust and the variable amount of thrust together provide an overall thrust to descend and land the aircraft.

Inter alia, the invention relates to an aerial device (10), comprising at least one rotor (12, 12a, 12b) that generates lift forces that, using a controller (18), can be addressed by a drive (16, 16a, 16b), wherein the drive (16, 16a, 16b) comprises an electromotively-driven rotor drive shaft (29). The particular feature of the invention is, among other things, that the drive (16, 16a, 16b) comprises a plurality of electric motors (25, 26, 27) that jointly drive the rotor drive shaft (29).

An aircraft (40a) is provided that includes a plurality of arms (41, 42, 43, 44) with selected arms having the ability to either adjust their length, have arm segments operative to move about an articulated joint in two or three dimensions, or have one arm operative to adjust an angle between the one arm and another arm, or any combination of the foregoing. Thrust generators are repositionably mounted on selected arms, and a control system enables automated, onboard, or remote control of the thrust generators, repositioning of the thrust generators on the arms, adjustment in the length of the selected arms, the movement of selected arms about the articulated joints, and adjustment of the angle between two or more arms, all while maintaining directional control of the aircraft in flight or on the ground. The aircraft has operational capabilities that exceed existing designs and facilitates manned and unmanned delivery of cargo and transportation of passengers.

An aircraft has a fuselage, an engine disposed within the fuselage, a rotatable wing disposed above the fuselage and selectively rotatable about a wing rotation axis, and a plurality of interconnect driveshafts disposed within the rotatable wing, and at least one drive system component that is connected between the engine and the interconnect driveshaft is disposed along the wing rotation axis.

The present disclosure relates to an autonomous, electric, vertical takeoff and landing (VTOL) aircraft that is low-noise, safe, and efficient to operate for cargo transportation over relatively long ranges. A VTOL aircraft includes a fuselage, a plurality of arms, a tail, and a plurality of propulsion systems mounted on the arms and the tail. The plurality of arms have parts that are rotatable and the tail has a part that is rotatable for transitioning the VTOL aircraft between a forward-flight configuration and a hover configuration.