In some embodiments, an aircraft includes a flying frame having an airframe, a propulsion system attached to the airframe and a flight control system operably associated with the propulsion system wherein, the flying frame has a vertical takeoff and landing mode and a forward flight mode. A pod assembly is selectively attachable to the flying frame such that the flying frame is rotatable about the pod assembly wherein, the pod assembly remains in a generally horizontal attitude during vertical takeoff and landing, forward flight and transitions therebetween.

In some embodiments, an aircraft includes a flying frame having an airframe, a propulsion system attached to the airframe and a flight control system operably associated with the propulsion system wherein, the flying frame has a vertical takeoff and landing mode and a forward flight mode. A pod assembly is selectively attachable to the flying frame such that the flying frame is rotatable about the pod assembly wherein, the pod assembly remains in a generally horizontal attitude during vertical takeoff and landing, forward flight and transitions therebetween.

A VTOL aircraft (1), including: a fuselage (2) for transporting passengers and/or load; a front wing (3) attached to the fuselage (2); an aft wing (4) attached to the fuselage (2), behind the front wing (3) in a direction of forward flight (FF); a right connecting beam (5a) and a left connecting beam (5b), which connecting beams (5a, 5b) structurally connect the front wing (3) and the aft wing (4), which connecting beams (5a, 5b) are spaced apart from the fuselage (2); and at least two propulsion units (6) on each one of the connecting beams (5a, 5b). The propulsion units (6) include at least one propeller (6b, 6b′) and at least one motor (6a) driving the propeller (6b, 6b′), preferably an electric motor, and are arranged with their respective propeller axis in an essentially vertical orientation (z).

A VTOL aircraft (1), including: a fuselage (2) for transporting passengers and/or load; a front wing (3) attached to the fuselage (2); an aft wing (4) attached to the fuselage (2), behind the front wing (3) in a direction of forward flight (FF); a right connecting beam (5a) and a left connecting beam (5b), which connecting beams (5a, 5b) structurally connect the front wing (3) and the aft wing (4), which connecting beams (5a, 5b) are spaced apart from the fuselage (2); and at least two propulsion units (6) on each one of the connecting beams (5a, 5b). The propulsion units (6) include at least one propeller (6b, 6b′) and at least one motor (6a) driving the propeller (6b, 6b′), preferably an electric motor, and are arranged with their respective propeller axis in an essentially vertical orientation (z).

An aircraft capable of carrying at least 400 pounds of payload, has four rotors systems, each of the rotor systems being independently driven by an electric motor or other torque-producing source. Each of the rotor systems provide sufficient thrust such that the aircraft is capable of controlled vertical takeoff and landing, even if one of the variable pitch rotor is inoperable. An electronic control system is configured to control the rotational speed and pitch of at least one of the rotor systems in each of the first and second rotor pairs. The rotors may be arranged in coaxial stacks or maybe otherwise configured.

A method of delivering heavy payload using an autonomous UAV able to deliver supply by way of airdrop with more precision and at a lower cost. The UAV is equipped with two movable wing systems that rotate from a stowed position to a deployed position upon jettison of the UAV from a mothership. The UAV can be controlled remotely or it can operate autonomously and the movable wings can include ailerons to effectuate flight control of the UAV. The UAV can be reusable or can be an expendable UAV.

A method of delivering heavy payload using an autonomous UAV able to deliver supply by way of airdrop with more precision and at a lower cost. The UAV is equipped with two movable wing systems that rotate from a stowed position to a deployed position upon jettison of the UAV from a mothership. The UAV can be controlled remotely or it can operate autonomously and the movable wings can include ailerons to effectuate flight control of the UAV. The UAV can be reusable or can be an expendable UAV.

The lifting, stabilizing and propelling arrangement for vertical take-off and landing aircraft, uses rotating wings, turbines or lift fans, propellers and stabilizers on the trailing edges of the wings and empennages, centrifugal or tangential turbines applied on the sides of the fuselage, on the inlet and outlet edges of the wings, or centrifugal or tangential turbines on the sides of the fuselage and inside the wings, those that carry the fuselage are fixed and produce only lift and those that go in the wings they rotate with them and produce lift during vertical flight and propulsion during horizontal flight, add some horizontal stabilizing fans at the tips of the wings and others for direction in the vertical empennage.

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.

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.