16results about "Flying saucers" patented technology

The invention discloses an unpowered landing device special for a saucer-shaped aircraft, belongs to the technical field of saucer-shaped aircrafts, and aims to solve the problems that a traditional landing device is large in occupied space, complex to operate and free of autonomous speed and direction control. The device comprises an annular umbrella cloth storage container, cylindrical umbrella cloth, a rotatable ring, a hanging ring, a flexible hanging wire, a supporting pulley, a limiting device, an air leakage opening and an arc-shaped plate. The annular umbrella cloth storage container and the outer edge of the saucer-shaped aircraft are fixed or integrally designed, the upper edge of cylindrical umbrella cloth is bonded with a rotatable ring, the lower edge is bonded with the outer side of a hanging ring, and a flexible hanging wire is connected with the rotatable ring and the inner side of the hanging ring through a limiting device; the rotatable ring is supported by more than three supporting pulleys, is connected with an external power device through a clutch mechanism, and can drive the cylindrical umbrella cloth to be spirally stored; after the external power is cancelled, the gravity of the hanging ring drives the cylindrical umbrella cloth to unfold without jamming, and the opening and closing degree of the air outlet are adjusted in cooperation with the arc-shaped plate, so that the falling speed and the drifting direction are autonomously controlled. The device is high in adaptability, high in reliability and suitable for unpowered safe landing of the saucer-shaped aircraft in the vertical non-straight-through airflow state of the saucer body.

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.

The invention relates to the technical field of low-altitude unmanned aerial vehicles, in particular to a new energy saucer-shaped aerostat which comprises a saucer-shaped shell, air bags and ducted fans, the saucer-shaped shell is of a flat disc-shaped structure, the air bags are filled in the saucer-shaped shell, and the air bags comprise at least two independent air bags; at least one air bag is filled with helium, and the helium in the air bag provides lift force for the aerostat; at least one air bag is filled with air, the volume of the air bag can be adjusted by inflating and deflating the air, and then the aerostat is controlled to ascend and descend through the volume change of the air bag; eight ducts are arranged in the air bag and evenly distributed in the front direction, the rear direction, the left direction and the right direction, the inner ends of the eight ducts are communicated, the outer ends of the eight ducts are led to the outside of the air bag, a ducted fan is installed in each duct, and the eight ducted fans cooperatively control the aerostat to move front, back, left and right in the horizontal direction. The invention provides the new energy unmanned aerial vehicle which is high in maneuverability, long in endurance, large in load and low in noise.

A method for obtaining both the lift and thrust required for the horizontal flight of a vertical take-off and landing aircraft while maintaining the horizontal flight stability of the aircraft, achieved by drawing in air into an internal cavity formed between coaxially mounted multi-blade turbines (2,18), the upper and lower of which rotate in opposite directions and remove air outwards below the aircraft, the conical turbines mounted in opposing directions on a wide circular base, which is mounted on double-sided fixed bearings (4,16) along the contour edge of an outer ring (12), which is attached from the inside by means of distance spacers (13) to a central housing (6), which is formed in a conical shape and to which both turbines (2,18) are attached using linear drives from the side of the smaller base. The air that accumulates under pressure in the inner cavity is removed to the outside of the outer ring (12) using motive nozzles (15A, 15B, 15C, 15D) installed circumferentially on the inner ring to reach the thrust required for horizontal flight, or stabilizing nozzles (14A, 14B) used to maintain the required rotational stability of the middle ring (6).The invention is also an airplane used to achieve the method.

The invention discloses a saucer-shaped aircraft with a buffer assembly, and provides the following scheme that the saucer-shaped aircraft comprises a saucer-shaped aircraft body and the buffer assembly installed at the bottom of the saucer-shaped aircraft body, a driving structure is installed at the bottom of the saucer-shaped aircraft body, and an adjusting structure is arranged on the driving structure; by arranging a buffer assembly and an elastic structure, under the acting force of a first spring, the saucer-shaped aircraft body is protected to a certain degree, when the saucer-shaped aircraft body takes off and a buffer plate rotates to the position, close to a mounting cabinet, of a mounting frame at the end of the buffer plate, resistance of an adjusting frame to a movable plate is remarkably reduced, and at the moment, the saucer-shaped aircraft body is prevented from falling off. When the saucer-shaped aircraft takes off, the first spring releases accumulated energy and quickly pushes the movable plate to be far away from the fixed block, in the process, storage of the buffer plate is accelerated, initial lift assistance is provided for the saucer-shaped aircraft body through the elastic force effect, the saucer-shaped aircraft can quickly complete the take-off action, and energy consumption can be reduced.

The invention provides a flying saucer fuselage, and belongs to the technical field of aircrafts, the flying saucer fuselage comprises a saucer-shaped fuselage body, a cabin is arranged on the saucer-shaped fuselage body, a riding device is hung in the cabin, a ventilation channel is formed in a rubber pad, and the density of the saucer-shaped fuselage body is smaller than that of water, so that the saucer-shaped fuselage body can float on the water; the saucer-shaped fuselage body is hollow, the lower portion of the cabin is of a closed design, a plurality of motor mounting holes are formed in the periphery of the cabin, and a plurality of airflow channels are formed in the periphery of the motor mounting holes. The flying saucer has the beneficial effects that when a person walks on the cabin sand by logging in a corridor and the wind is blown by the flying saucer in the driving process, firstly, due to the special shape of the flying saucer, the flying saucer has a very good streamline shape, the wind resistance in all directions is relatively small, and the cockpit is hung inside, and when strong wind attacks, the flying saucer is prevented from being blown by the wind due to the inertia effect; the cockpit can shake in the direction opposite to the strong wind direction, and part of acting force of the strong wind is counteracted.

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 fluid acting synergy device based on double ducts and rotor rotation gain. The fluid acting synergy device is suitable for multiple fields of flight, suspension, ship navigation and the like. The core structure comprises a rotor, a fixed shell surface, a magnetic suspension device, an inclined flow guide baffle and a ducted fan or a propeller. A first duct is formed by a space formed by the rotor and the fixed shell face in a parallel and opposite mode, and annular negative-pressure flow suction blades are arranged on the bent and curled portion of the outer edge of the rotor and can suck in fluid such as air or water. The inclined flow guide baffle in the first duct converts fluid into spiral centripetal vortex, and acts on the flow baffle on the rotor to drive the rotor to rotate, so that the kinetic energy and the aggregation degree of the fluid are enhanced, and it is ensured that the fluid entering the second duct is in the highest energy density state. A second duct is arranged on the inner edge of the first duct and provided with a ducted fan or a propeller to serve as an active energy source, fluid kinetic energy is further improved after the high-energy vortex conveyed by the first duct is received, and finally the fluid is sprayed out at a high speed through a functional nozzle to do work outwards. The magnetic suspension device is arranged at the position where the rotor abuts against the fixed shell face, mechanical friction is reduced, an energy recovery module can be integrated, and the energy efficiency of the device is improved. The device effectively optimizes the hydrodynamic performance through double-duct cooperation and rotor autorotation gain, and has remarkable practical value and industrial prospect in the scenes of low-altitude logistics, disaster rescue, manned flight, ground and water surface suspension carriers, ship navigation and the like.

According to the saucer-shaped aircraft with the double ducts and the rotor autorotation gain, the rotor is in non-contact connection through the permanent magnet-electromagnetic hybrid suspension device, namely, the suspension device, and is matched with the integrated damping compensation and energy recovery module, so that the problem of friction loss of traditional mechanical transmission is effectively solved, and the reliability of the saucer-shaped aircraft is improved. Annular air suction fan blades designed on the bending and curling portion of the outer edge of the rotor achieve air suction on the upper portion of the edge and are matched with the angle-adjustable oblique flow guide baffles in the disc-shaped duct to achieve the synergistic effect, efficient spiral centripetal vortexes are formed, power is provided for rotation of the rotor, the overall lift performance is greatly improved, and the lift coefficient exceeds 1.0. The pod expansion dish-shaped shell surface not only increases the effective load space, but also enhances the stability of the aircraft in special environments such as the water surface. And the protection device on the periphery of the rotation rotor provides reliable safety protection guarantee and supporting effect for the rotation rotor. And the solar power generation device is mounted on the dish-shaped shell surface at the upper part of the main cabin, so that the cruising ability of the dish-shaped aircraft is further improved.

The invention discloses a vertical offset aircraft, and relates to the technical field of aircrafts, the vertical offset aircraft comprises a shell, the shell is arc-shaped, a first wind gathering barrel, a controller, an offset box, a set of engines, a cockpit and hidden driving wheels are arranged in the shell, a power assembly is arranged in the first wind gathering barrel and is used for realizing lifting of the aircraft, and the controller is arranged in the first wind gathering barrel. The controller is arranged at the tail of the interior of the offset box, the offset box is arranged on the lower portion of the interior of the shell and arranged on the outer side of the bottom of the first air gathering barrel in a penetrating mode, an offset power source electricity storage box, a connecting assembly and a transmission assembly are arranged in the offset box, and the connecting assembly is used for guaranteeing the moving stability of the offset power source electricity storage box. According to the device, the gravity center of the aircraft can be inclined through the arrangement of the internal structure of the offset box, and the advancing, retreating and steering state adjustment of the aircraft is achieved.

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).