Thrust Vectoring Drone Design for VTOL

A vertical takeoff and landing (VTOL) aircraft that combines the benefits of helicopters and fixed-wing aircraft. The aircraft features a main wing with a tilting propeller system that enables both vertical and horizontal flight modes. The propellers can change angle from 0° to 90° to transition between vertical takeoff and landing, hovering, and horizontal flight. The design eliminates the aerodynamic inefficiencies and structural issues associated with traditional VTOL aircraft, enabling fast horizontal speeds, long-range flight, and all-weather operation.

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VTOL aircraft with a cylindrical fuselage and integrated cross-shaped wings, featuring five propellers: four wingtip thrusters for vertical takeoff and low-speed control, and a central propeller for high-speed horizontal flight. The design combines vertical takeoff and landing capability with high-speed flight and long-range autonomy, enabled by optimized aerodynamic coefficients and dual flight control systems.

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A free propeller assembly structure for aircraft, comprising a circular shaft, main rotor, signal transmitting device, and rotor blade assembly, where the rotor blades are mounted to blade mounting structures on the main rotor and driven by motors, and the signal transmitting device enables electronic or photonic signal transmission between the rotor blades and main rotor. The assembly is designed for vertical takeoff and landing aircraft, enabling flexible rotor blade angles and improved performance in various environments.

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A hybrid unmanned aerial vehicle (UAV) with vertical take-off and landing (VTOL) capabilities, featuring a fixed wing configuration with rotating wings for level flight. The VTOL system comprises two pairs of rotors, one pair mounted at a fixed angle above the wing and the other below, with the center of gravity located at the intersection of the rotor axes. The fixed wing configuration includes a rear horizontal stabilizer and a pair of second wings, while the VTOL system is controlled by an integrated autopilot module that calculates and applies control signals to both the rotors and fixed wing.

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A remotely controlled wireless drone that employs a rocket engine to quickly reach a desired altitude or location, with electrically-driven propellers that are stowed during rocket firing and deployed afterwards to control the drone's position and altitude. The drone's design enables rapid vertical takeoff and transition to horizontal flight, with the rocket engine providing the initial propulsion and the propellers taking over for sustained flight.

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An electrically powered rotorcraft with a rotor having a rotor hub and a pair of rotor blades mounted to the rotor hub on opposite sides thereof, the rotor being rotatably mounted on a primary drive shaft, and a rotary electric motor coupled to the drive shaft. The rotorcraft includes a limited-angle electric motor, such as a stepper motor, coupled to a common pitch-angle shaft shared by the two rotor blades, and a control system that applies cyclic response through the limited-angle motor to cause differential blade incidence. The control system receives a PWM signal from the flight control computer every 10 mS, indicating the desired position of the common blade pitch shaft, and adjusts the phase and magnitude of the cyclic response to achieve the desired thrust offset.

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VTOL aircraft with fixed wings that can hover, take off and land vertically like a helicopter and then transition to forward flight like a conventional fixed wing aircraft. The aircraft has independently tiltable proprotors mounted forward and aft of the wings. This allows all proprotors to be used in all flight modes, reducing drag during forward flight compared to fixed blades during vertical flight. The independent tilt control provides additional stability and maneuverability benefits.

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Unmanned aerial vehicle (UAV) with enhanced maneuverability and operational flexibility through a novel control system. The UAV features a single-axis power drive system with a single motor, eliminating the need for separate control systems for vertical takeoff and landing and horizontal flight. The power drive system enables simultaneous control of all four rotors, including the rear rotors, through a single transmission unit. This configuration provides increased maneuverability and simplifies operation compared to conventional UAV designs. The system also enables the UAV to maintain hover angles while operating in both vertical and horizontal flight modes.

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Device and method for controlling flight mode transitions in VTOL aircraft by dynamically locking and unlocking flight surfaces. The device enables precise control of wing position during transitions between vertical and horizontal flight modes by locking the wing in its optimal position before transition, allowing it to rotate to the correct position just prior to locking. This enables stable flight mode transitions without the need for complex flight control systems. The device can be integrated into VTOL aircraft to provide a reliable and efficient means of transitioning between flight modes.

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Aircraft with tiltable un-ducted rotors and tiltable ducted fans that transition between forward thrust and vertical lift orientations. The aircraft features two wings with tiltable ducted fans at the wingtips, and two booms with tiltable rotors and aft rotors. In vertical takeoff and landing (VTOL) mode, the rotors and ducted fans rotate in a horizontal plane, while in forward flight mode, they transition to a vertical plane.

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An unmanned aerial vehicle (UAV) with vertical takeoff and landing (VTOL) capability that generates low noise levels. The UAV uses an ion thruster with asymmetrical electrodes subjected to a potential differential to produce vertical thrust, and a vector thrusting device to control roll, pitch, and yaw. The ion thruster electrodes are integrated into the primary structure of the craft, eliminating the need for separate engines or wings. A thrust vectoring system with pivoting fans enables controlled flight in any direction while maintaining low noise levels.

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Convertible aircraft for sports competition or personal air mobility, capable of switching between hovering/vertical flight and forward flight configurations. The aircraft features a pair of nacelles housing motors and rotors that rotate around a third axis, connected to the motors. The design enables high stability and reduced aerodynamic drag while overcoming traditional helicopter limitations in terms of altitude and speed.

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Flight vehicle with improved stability and maneuverability, featuring a thrust generating unit with multiple subunits, each comprising independently controllable thrust generators arranged in a line. The subunits are connected to the vehicle body through joints that permit free pivoting around a central axis, allowing for coordinated torque generation and control. The vehicle's control system adjusts thrust levels in each subunit to balance opposing torques and maintain desired angular positions, enabling precise attitude control and enhanced stability during flight.

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Surface-integrated electroaerodynamic (EAD) thrusters for aircraft propulsion that reduce drag and improve efficiency by integrating ion sources and collectors directly into the wing surface, eliminating the need for external thrusters and associated drag. The thrusters utilize a voltage differential to generate ions that collide with air molecules, producing thrust while minimizing drag. The integrated design enables reduced drag, mass savings, and simplified structural components compared to conventional EAD thrusters.

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Tail-sitter aircraft design that allows vertical takeoff and landing like a helicopter but faster, simpler, and with comparable performance to traditional airplanes. The tail-sitter has a vertical fuselage with wings that rotate from vertical to horizontal for forward flight. The key innovation is that the wings are shaped like half-wings that are flush with the fuselage in the vertical position, avoiding the large vertical surface area that limits other tail-sitter designs. By rotating the half-wings horizontally for forward flight, the tail-sitter achieves conventional aircraft performance. It lacks a tail fin or other movable surfaces beyond the rotating wings, simplifying the design.

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Convertible unmanned aerial vehicle (UAV) with tilt-rotor and tilt-wing characteristics that can switch between vertical takeoff/landing and forward flight. The UAV has a fuselage with wings mounted on rotating shafts perpendicular to the fuselage axis. The wings have detachable front and rear sections that slide together. In vertical mode, the wings rotate freely around the shafts while the rotors provide lift. In forward flight, the wings stay fixed and the rotors push the UAV. The detachable wing sections have cutouts for the rotors. This allows the wings to rotate without colliding during transitions. The UAV can convert between flight modes without disassembly.

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Flying vehicle with distributed propulsion system comprising a pair of rotor assemblies, each comprising a tilt-rotor and a stacked plurality of vertical thrust rotors, mounted on the wings to provide redundancy and efficiency during vertical takeoff and landing (VTOL) and high-speed cruise operations.

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An electric aircraft for generating a yaw force, comprising a fuselage, laterally extending elements secured to the fuselage, lift components attached to the elements, and a longitudinal thrust component configured to generate a yaw force. The aircraft includes a flight controller that determines a yaw correction based on sensor data from the lift components, enabling the aircraft to maintain stability and control in the event of a lift component failure.

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Twin-fuselage arrangement for electric tiltrotor aircraft, comprising two fuselages connected by a central section, with each fuselage housing a rotor and electric motor, enabling vertical takeoff and landing capability while maintaining a compact footprint suitable for urban air mobility applications.

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A compact, efficient, and safe vertical takeoff and landing (VTOL) UAV design that enables enhanced package delivery capabilities in densely populated areas. The UAV incorporates inboard-mounted lift rotors that provide increased vertical thrust during vertical ascents and descents, while maintaining a compact and agile form factor. This design enables VTOL operations in tight urban environments, with the added benefit of increased payload capacity compared to conventional fixed-wing designs. The inboard-mounted rotors reduce rotor blade extension beyond wing tips, while maintaining safety through reduced rotor contact with external objects. The resulting compact, efficient VTOL system enables efficient package delivery in urban areas without compromising payload capacity.

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