8results about "Flying saucers" patented technology

The present invention is applicable in the technical field of aircraft and provides a saucer-shaped aircraft comprising an aircraft body. The aircraft body is provided with a saucer-shaped wing, and functional vanes that are rotatably connected to the aircraft body and can be unfolded downwards for cushioning in the process of landing are arranged below the saucer-shaped wing. The functional vanes are arranged in numbers, and the functional vanes are arranged around a center of the aircraft body. The aircraft body is further provided with a drive control mechanism for driving the functional vanes to rotate. Each of the functional vanes has an upper end in connection with the aircraft body through a rotating structure, which is located below the saucer-shaped wing and near an outer edge of the saucer-shaped wing. The aircraft body is provided with a locking device for locking the functional vanes when folded up.

A peripheral propulsion system having a propulsion unit (3), an upper section (36), and a lower section (37). The propulsion unit (3) has a motor (31), a motor engagement section (34), an extension (32) coupled to the motor engagement section (34), and two or more blades (33) coupled to the extension (32). The extension (32) is located between the upper section (36) and the lower section (37). The output section (22) is located about at least a portion of the lower section (37), and the two or more blades (33) are located outside a periphery of the vehicle (7). When the motor (31) is running, the two or more blades (33) are capable of drawing fluid from about the periphery of the vehicle (7) and through the output section (22).

The disc-shaped manned aircraft is mainly formed by combining a plurality of turbine shaft engine devices and a turbine fan engine, each turbine shaft engine drives a propeller blade fan and a turbine fan of the turbine shaft engine and is provided with an anti-collision net and a disc-shaped wind collecting disc, and the appearance of the disc-shaped manned aircraft integrally forms a flying saucer shape; according to the saucer-shaped aircraft, the aerodynamic layout of an existing saucer-shaped aircraft is improved, a flight control device is optimized, and the flight safety is improved; the flying saucer is reasonable in structural design, easy to manufacture, low in cost and safe and reliable to use, has novelty and creativity, and shows the basic structure of the Chinese type flying saucer and the development direction of the flying saucer in the future.

A flying platform in the shape of a disc with at least four electric motors for maneuvering and a concave dome with current-harvesting tips for collecting atmospheric, solar and electrical energy, characterized in that an internal energy storage system consisting of supercapacitors and / or high-performance batteries is provided, at least one electrical discharge tube for controlled pulse delivery and a magnetic docking module for transferring energy to external aircraft or spacecraft.

The method of obtaining both, lifting force and thrust, required for horizontal flight of the vertical take-off and landing flying machine while maintaining horizontal flight stability of the machine which is realized due to suction atmospheric air to the inner cavity formed between coaxial mounted, multi-blade turbines (2, 18), the top and the bottom, which are counter-rotating relatively to each other, and remove the air outside under the machine; the conical turbines are mounted with the direction of wider, circular bases facing in front of them and which are mounted on the double-sided fixed bearings (4, 16) alongside the contour edge of the external ring (12), which is mounted using the distance spacers (13) form the inner side to the central housing (6) which is formed with the conical shape and which is the base where the both turbines (2, 18) are mounted using linear drives from the side of their smaller bases. The air which is accumulated under the pressure at such inner cavity is removed outside of the external ring (12) using drive nozzles (15A, 15B, 15C, 15D), which are installed circumferentially at the inner ring, to achieve thrust required for the horizontal flight or stabilization nozzles (14A, 14B), which are used to maintain required rotational stabilization of the central ring (6). The subject of the invention is also the machine used to achieve this way.

The invention discloses a three-section type modularized pure electric intelligent flying saucer aircraft, belongs to the technical field of low-altitude manned aircraft and new energy high-end equipment manufacturing, and solves the technical problems that an existing low-altitude aircraft is poor in aerodynamic layout, short in endurance, single in safety protection and complex in control. The disc-shaped bionic design is adopted, and the whole machine is of a three-section modular structure which is composed of an upper-section panoramic wind shielding cabin cover, a middle-section panoramic cabin and disc wing body and a lower-section concentric circle nested type power pod. The lower-section power pod adopts a three-layer nested layout, a sealed battery cabin is arranged in the center, a plurality of brushless motors are annularly distributed, and an outer ring is matched with a folding annular air bag; the middle disc wing carries a conformal flexible photovoltaic film, a hollow wind guide bearing framework and a solid helium storage auxiliary lift module, so that composite lift and auxiliary energy supply are realized; the whole machine is provided with a five-layer progressive safety protection system and is purely electrically driven, and a flight control system is simplified and easy to use. The unmanned aerial vehicle is excellent in aerodynamic performance, longer in endurance, high in safety level, modularized, easy to maintain and suitable for low-altitude short-distance manned travel, emergency rescue and other scenes, and conforms to the national green low-altitude economic development policy.

A peripheral propulsion system having a propulsion unit, an upper section, and a lower section. The propulsion unit has a motor, a motor engagement section, an extension coupled to the motor engagement section, and two or more blades coupled to the extension. The extension is located between the upper section and the lower section. The output section is located about at least a portion of the lower section, and the two or more blades are located outside a periphery of the vehicle. When the motor is running, the two or more blades are capable of drawing fluid from about the periphery of the vehicle and through the output section.

A peripheral propulsion system comprises a propulsion unit (3), an upper section (36) and a lower section (37). The propulsion unit (3) comprises an engine (31), an engine engagement portion (34), an extension portion (32) connected to the engine engagement portion (34), and two or more rotor blades (33) connected to the extension portion (32). The extension (32) is located between the upper section (36) and the lower section (37). The output section (22) is disposed about at least a portion of the lower section (37) and the two or more rotor blades (33) are located outside the periphery of the vehicle (7). When the engine (31) operates, the two or more rotor blades (33) can suck fluid from the periphery of the carrier (7) and flow through the discharge section (22).