Aerodynamic Design of Drone Propulsion Systems

A lift generating device for an aircraft that improves the reliability and safety of vertical takeoff and landing (VTOL) aircraft by utilizing a ducted jet stream system. The system includes an inlet duct, a jet stream generator, and a curved duct that guides the high-velocity jet stream along a curved surface to generate lift. The duct design incorporates a straight section to maintain constant centrifugal force and a curved section with a specific angle to optimize lift generation. The system also employs a Coanda effect to draw in surrounding air and increase the flow rate of the jet stream.

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A system and method for rotor management in electric aircraft to reduce drag during cruise flight. The system determines a drag minimization axis for each rotor and positions it in a halting point where the first end points in one direction of the axis and the second end points in the opposite direction. The system uses magnetic elements to halt and position the rotors, and continuously updates the halting point based on sensor feedback. The system can also utilize machine learning models to determine optimal halting points.

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Ground-effect aircraft with enhanced lift and efficiency through novel aerodynamic principles. The aircraft features a base case lifting body enhanced with lift-span technology and cross-over propulsor, which work together to optimize lift generation and pressure retention. The design incorporates a variable pitch lift span, a crossover propulsor, and a unique fence system that maintains close clearance ratios while minimizing drag. The aircraft achieves higher lift and L/D efficiency by leveraging the ground to block pressure dissipation, rather than relying on traditional wing curvature.

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Engine for a vertical take-off and landing aircraft, comprising an aerodynamic component with a movable aerodynamic element that defines an aerodynamic surface in contact with an airstream passing through the engine. The aerodynamic element is configured to move between a first position and a second position in response to the engine's movement between a hover position and a cruise position, thereby adapting the aerodynamic conditions within the engine to optimize performance in both operating modes.

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Ducted fan device for VTOL aircraft with improved thrust and noise reduction. The device features a cylindrical larger duct and multiple smaller ducts surrounding fans, with the smaller ducts positioned outside the larger duct on the upstream side. The smaller ducts are arranged at equal angular intervals and have a specific length-to-diameter ratio to optimize airflow and prevent Coanda effect interference. This configuration controls air separation at the larger duct's lip portion, enhancing thrust and quietness during transition modes and crosswind conditions.

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A drone design that generates lift through aerodynamic wing-like propeller guards rather than traditional propeller guards. The guards, which are part-annular in shape, extend radially from the drone's body and are strategically positioned to intercept the propellers' airflow. By optimizing the guard's angle and shape relative to the propellers' path, the drone achieves lift while maintaining stability and minimizing drag. The guards are integrated into the drone's aerodynamic system, eliminating the need for separate safety features while maintaining safety performance.

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Controllable vectored thrust in propulsion assemblies for aircraft that allows for vertical takeoff, hovering, and landing capability like a helicopter, but also provides forward flight speed and range like a fixed-wing aircraft. The propulsion assembly has a rotor system that can swivel about a fixed pivot axis. By changing the angle of the rotor axis relative to the aircraft, it allows shifting the center of gravity and direction of thrust vectors. This provides benefits like reducing thrust requirements when an engine fails, improving stability and maneuverability in hover, and allowing forward/aft and side translation without changing attitude.

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A structure for an electric aircraft featuring a single-piece wing with an integrated airfoil, and a boom system comprising a central joint attached to the wing and two segments extending from the joint to support a propulsor. The boom joint is designed to provide a stable and rigid connection between the wing and the propulsor, enabling efficient and reliable propulsion of the electric aircraft.

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Aircraft with a boom supporting multiple VTOL rotors in a non-linear array, where the boom is curved in the lateral direction to accommodate the rotor layout, and features a specially designed shape to reduce aerodynamic drag during cruise operations.

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A vertical takeoff and landing (VTOL) aircraft with pivoting thrust units that transition from vertical to horizontal thrust during flight. The units feature stowable propellers that nest within the nacelles during forward flight, eliminating drag and optimizing efficiency. The propellers are powered by electric motors that rotate with the units, eliminating the need for gimbal systems or torque drives. The aircraft achieves VTOL capabilities through the pivoting thrust units, which can be fully stowed during forward flight.

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An unmanned aerial vehicle (UAV) with a ducted fan propulsion system, comprising a ducted body with a vertical axis, a fan motor, and a fan positioned within the duct. The fan motor is electronically connected to a flight controller that controls the fan motor for thrust generation and an actuator for lid control, enabling roll and pitch control.

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A louvered lift fan cover for vertical takeoff and landing (VTOL) aircraft that enables efficient transition between hover and forward flight modes. The cover features a plurality of louver devices positioned at the inlet opening of the fan duct, with each louver device having a fixed and movable portion. As the cover moves between open and closed positions, the curvature profiles of the airflow channels between adjacent louver devices change, reducing flow separation and turbulence during transition. The louver devices are designed to rotate through different limited ranges, with the forward-most louver device having the smallest range and the rear-most louver device having the largest range. This design enables smooth airflow control during mode transition, minimizing drag and vibration.

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A rotorcraft design with circular wings underneath the rotors that provide lift and stability benefits. The rotors generate the primary lift, but the circular wings with convex upper surfaces create Coanda effects that generate additional lift. The airflow over the wings is deflected downward by the curvature, providing a third source of lift. This reduces the overall size and weight of the rotorcraft compared to traditional designs that rely solely on the rotors for lift. The circular wings also improve stability during ground taxiing and reduce the center of gravity by allowing components like wheels and batteries below the rotors.

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Wing design for aircraft with improved aerodynamic performance. The wing has a fixed lift generating portion and a moveable lift modifying portion connected to it. The moveable portion can pivot along the wing's extension direction and contains propulsion devices to generate thrust. This allows the wing tips to move and create lift modification while also providing thrust. The concave wingtip shape reduces vortices compared to conventional wings. The moveable wingtips extend rearward and have inclined rear edges. The fixed wingtips can also have inclined edges. This configuration improves lift and reduces drag compared to fixed wingtips with gaps.

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An electric vertical takeoff and landing (eVTOL) aircraft with underwing ducted fans featuring specially shaped rotor blades with zero sweep leading edges and elliptical trailing edges. The aircraft's wings have an undercambered lower surface, and the ducted fans are mounted to this surface. The rotor blades have flat tips and are attached to a hub with a defined pitch angle. The ducted fan configuration includes a larger fan array, an outer fan array near the wing tip, and an inner fan array between the larger and outer arrays.

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An electric aircraft with integrated distributed ducted fans, comprising a wing with a ducted fan power unit, where the ducted fan power unit includes multiple ducted power units, each comprising a duct, a propeller rotatably fixed within the duct, and an electric motor drivingly connected to the propeller. The wing includes an inner wing section with a flap receiving portion and an inner wing flap that can move between an extended and retracted position, and an outer wing section with an outer wing flap that can move between an extended and retracted position. The aircraft also includes a fuselage, a tail section, and a landing gear system.

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An air mobility device that increases flying range through Coandă effect enhancement and reduces noise through distributed propulsion. The device features a main body with compression motors, rotatable wings with open spaces, and blowers that utilize compressed air to generate additional propulsion. The wing design incorporates asymmetric streamlined shapes to optimize airflow and enhance the Coandă effect, while the distributed propulsion system minimizes noise generation.

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An air mobility system with a foldable wing that reduces air resistance during vertical takeoff and landing. The wing features a deployable section that overlaps with the main wing during vertical flight, and deploys during cruising to improve efficiency. An actuator and controller enable controlled folding and deployment of the wing section.

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A variable toroidal propeller for air and water applications that combines the efficiency and quiet operation of toroidal propellers with the pitch control of variable pitch propellers. The propeller features a toroidal blade that deforms in response to actuator activation, allowing for adjustable pitch and optimized performance across different operating conditions.

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A distributed propulsion system for aircraft that stows propulsors within a leading-edge compartment when not in use. The system features a moveable slat that extends from the wing to expose the propulsors, which are then operated during takeoff and landing to provide increased power and lift. The slat retracts to enclose the propulsors when not in use, eliminating parasitic drag and maintaining the aircraft's aerodynamic profile during cruise.

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