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 fixed-wing aerial underwater vehicle includes a shell component, a flight component and a pneumatic buoyancy component. The flight component includes a fixed wing and rotors, and the fixed wing and the rotors are mounted in the shell component. The pneumatic buoyancy component includes an air bladder and an inflation and deflation portion, and the inflation and deflation portion can inflate and deflate the air bladder. The air bladder is installed on the shell component, a containing space is formed in the shell component, and the inflation and deflation portion is partially or entirely installed in the containing space. Each rotor includes a rotor supporting rod, a motor base, a motor and a propeller, which are sequentially connected. A control method for the fixed-wing aerial underwater vehicle mentioned above is further provided.

An unmanned vehicle (UV) navigation system is provided. The UV navigation system comprises a processor, a communication interface for communicating with a remote station, and a non-transitory memory device storing machine-readable instructions that, when executed by the processor, causes the processor to navigate the UV. The processor is configured to receive data from sensors, camera or data line for UV processor analysis, determine that a link-free trigger event has occurred, and autonomously navigate the UV in response to the trigger event.

A main body of an unmanned vehicle is provided. The main body comprises a propulsion-receiving module having a mount point for removably mounting a propulsion source, a payload-receiving module having a mount point for removably mounting a payload, and a damper interposed between the payload-receiving module and the propulsion-receiving module to inhibit transmission of vibrations from the propulsion-receiving module to the payload-receiving module when the payload-receiving module and the propulsion-receiving module are in mechanical communication.

An aircraft capable of vertical takeoff and landing, stationary flight and forward flight includes a closed wing that provides lift whenever the aircraft is in forward flight, a fuselage at least partially disposed within a perimeter of the closed wing, and one or more spokes coupling the closed wing to the fuselage. One or more engines or motors are disposed within or attached to the closed wing, fuselage or spokes. Three or more propellers are proximate to a leading edge of the closed wing or the one or more spokes, distributed along the closed wing or the one or more spokes, and operably connected to the one or more engines or motors. The propellers provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight, and provide thrust whenever the aircraft is in forward flight.

An agricultural unmanned aerial vehicle (UAV) is provided. The UAV includes a central frame, a control circuit, a left arm group, a right arm group and a spraying system. The left and right arm groups each includes a front arm assembly including a second rotor assembly, a rear arm assembly including a third rotor assembly, and a middle arm assembly including a first rotor assembly. In an output direction of downwash flow fields of the left and right arm groups, a height of a rotation plane of the first rotor assembly is lower than heights of rotation planes of the second and third rotor assemblies. The spraying system includes nozzle assemblies. The control circuit is configured to control the left and right arm groups to adjust flight attitude of the UAV. The left and right arm groups output the downwash flow fields in a direction towards the nozzle assemblies.

Disclosed is a drone configured for multiple uses. The drone may include a body and a sensor configured to be attached to the body. Further, the drone may include a plurality of arms configured to be attached to the body. Further, a first end of an arm of the plurality of arms may be attached to the body at a first movable joint. Further, the arm may include a first part connected to the first movable joint. Further, the arm may include a second part attached to the first part at a second movable joint. Further, the arm may include a powered rotor including a shaft configured to provide rotatory motion. Further, the powered rotor may be attached to one or more of the first part and the second part. Further, the drone may include a plurality of propeller blades attached to the shaft.

An unmanned aerial system includes an elongated fuselage having first and second rotational degrees of freedom. A forward propulsion assembly is disposed at the forward end of the fuselage. The forward propulsion assembly includes a forward rotor hub assembly rotatably coupled to the fuselage and reversibly tiltable about a first gimballing axis to provide a first moment on the fuselage in the first rotational degree of freedom. An aft propulsion assembly is disposed at the aft end of the fuselage. The aft propulsion assembly includes an aft rotor hub assembly rotatably coupled to the fuselage and reversibly tiltable about a second gimballing axis to provide a second moment on the fuselage in the second rotational degree of freedom. The first gimballing axis is out of phase with the second gimballing axis to control the orientation of the fuselage.

Disclosed is a remotely controlled wireless drone which employs a solid fuel rocket engine to propel it quickly to a desired or location. More specifically, an unmanned vehicle including a fuselage and a propulsion unit engaged with the fuselage, the propulsion unit being operable to bring the unmanned vehicle to a desired altitude or location, generally during a launch stage. The fuselage also includes multiple rotors pivotally engaged with the fuselage and a rotor positioning system operable to pivot the multiple rotors between stowed and deployed positions. The stowed position of the propellers minimizes drag and instability during the launch stage, and the deployed position allows the multiple rotors to control the position and altitude of the unmanned vehicle after the fuel of the rocket engine is spent. Submersible/amphibious and other embodiments are also described.

The technology described herein relates to autonomous aerial vehicle technology and, more specifically, to autonomous unmanned aerial vehicle with folding collapsible arms. In some embodiments, a UAV including a central body, a plurality of rotor arms, and a plurality of hinge mechanisms is disclosed. The plurality of rotor arms each include a rotor unit at a distal end of the rotor arm. The rotor units are configured to provide propulsion for the UAV. The plurality of hinge mechanisms mechanically attach (or couple) proximal ends of the plurality of rotor arms to the central body. Each hinge mechanism is configured to rotate a respective rotor arm of the plurality of rotor arms about an axis of rotation that is at an oblique angle relative to a vertical median plane of the central body to transition between an extended state and a folded state.