An insect-like jumping-flying robot is provided, which includes a flying module, a driving module and biomimetic bouncing legs. The flying module provides flying power via a propeller and a miniature model airplane motor, and front wings and rear wings provide lift, and moment required for attitude change. The driving module provides power with high power density via a brushless motor and is provided with two stages of deceleration to amplify the torque provided by the brushless motor. The first stage of deceleration is performed by a synchronous wheel set, and the second stage of deceleration is performed by a gear set. A driving push rod is used to transmit the power provided by the brushless motor to the biomimetic bouncing legs.

Piston Wings has high lift airfoils mounted on a linear reciprocal motion mechanism for a propeller driven propulsion engine. Piston Wings, in linear reciprocal motion shuttling back and forth in a generally horizontal plane, has airfoils oriented at optimum angle of attack to generate maximum lift forces; and the lift forces, when vectored, are turned into variable thrust forces for takeoffs, landings, and flights of vehicles. Piston Wings in flight has the appearance of legendary magic or flying carpets.

A rigid-flexible coupled unmanned aerial vehicle (UAV) morphing wing and an additive manufacturing method thereof are disclosed. A shape memory alloy (SMA) strip/wire for controlling the wing upward deformation and an SMA strip/wire for controlling the wing downward deformation are arranged alternately, and a plurality of reinforcing ribs are arranged at intervals on the SMA strips/wires for controlling the wing upward deformation and the SMA strips/wires for controlling the wing downward deformation. The SMA strips/wires for controlling the wing upward deformation and the SMA strips/wires for controlling the wing downward deformation are arranged on a flexible substrate, and are wrapped with an insulating covering. The SMA strips/wires for controlling the wing upward deformation and the SMA strips/wires for controlling the wing downward deformation each are provided with an electric heating element.

The present disclosure relates to a flying vehicle comprising an annular hollow outer body having an outer circumferential open portion and an inner circumferential open portion; a blade system disposed in the outer body and configured to allow air flow from the outer circumferential open portion to the inner circumferential open portion; a first magnetic system configured to enable the blade system to be kept to have a clearance with the annular hollow outer body and to be kept in a floated state using a first magnetic force; a second magnetic system configured to allow the blade system to rotate using a second magnetic force; and a steering system configured to allow air discharged from the inner circumferential open portion via the blade system to flow upwardly or downwardly.

A flying machine includes: a flying machine body that includes a rotor blade; a protective member that forms a frame shape inside which the rotor blade is disposed, that is rotatably fixed to both end portions of the flying machine body, and that is pipe shaped; and a connecting wire that passes through an inner portion of the protective member to connect the flying machine body and an external device together.

The present invention provides a propulsion system for an aircraft. The system includes one or more thrust producing portions, wherein the one or more thrust producing portions include one or more duct means. The duct means are at least partially formed or defined by two or more substantially parallel wall members. At least one flapping or waving wing member is provided, at least partially located or positioned substantially within the one or more duct means, wherein the flapping or waving motion of the at least one wing member creates thrust, enabling the aircraft to fly in use.

A device for controlling thrust vectoring of a cyclorotor includes a control cam positionable relative to a drive shaft of a cyclorotor along each of a first axis and a second axis, where the drive shaft is rotatable about a third axis. The device may further include a frame having a plurality of sides, where the frame is disposed at least partly around the drive shaft of the cyclorotor, a first positioning assembly disposed on a first side of the frame, where the first positioning assembly is structurally configured to move the frame along the first axis, and a second positioning assembly disposed on a second side of the frame, where the second positioning assembly is engaged with the control cam and structurally configured to move the control cam relative to the frame along the second axis.

A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one tail conduit is fluidly coupled to the generator. First and second fore ejectors are coupled to the main body and respectively coupled to a starboard side and port side of the vehicle. The fore ejectors respectively comprise an outlet structure out of which fluid flows. At least one tail ejector is fluidly coupled to the tail conduit. The tail ejector comprises an outlet structure out of which fluid flows. A primary airfoil element includes a closed wing having a leading edge and a trailing edge. The leading and trailing edges of the closed wing define an interior region. The at least one propulsion device is at least partially disposed within the interior region.

The present invention provides a propulsion system for an aircraft. The system includes one or more thrust producing portions, wherein the one or more thrust producing portions include one or more duct means. The duct means are at least partially formed or defined by two or more substantially parallel wall members. At least one flapping or waving wing member is provided, at least partially located or positioned substantially within the one or more duct means, wherein the flapping or waving motion of the at least one wing member creates thrust, enabling the aircraft to fly in use.

A device for controlling thrust vectoring of a cyclorotor includes a control cam positionable relative to a drive shaft of a cyclorotor along each of a first axis and a second axis, where the drive shaft is rotatable about a third axis. The device may further include a frame having a plurality of sides, where the frame is disposed at least partly around the drive shaft of the cyclorotor, a first positioning assembly disposed on a first side of the frame, where the first positioning assembly is structurally configured to move the frame along the first axis, and a second positioning assembly disposed on a second side of the frame, where the second positioning assembly is engaged with the control cam and structurally configured to move the control cam relative to the frame along the second axis.