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Method of creating lift for cargo lifting and transfer in air (version of russian logic - version 2) Invention relates to devices for lifting and transfer in air. Proposed method consists in application of the main disc with flexure at its edge and serial identical-orientation helical ribs located abode the main disc surface to create lower pressure at drive rotation. Main disc central part has flexed bore to ensure drive stiffness and clamping while extra disc is arranged there above and locked at the drive rotary part. For joint rotation, said ribs are locked and have slits made at their bottom part to receive one or several serial sliding plates to reciprocate perpendicular to and over main disc surface, on the entire length of said helical rib. |
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Method of creating lift for cargo lifting and transfer in air (version of russian logic - version 3) Invention relates to lifting force generation technique. Method of lifting force generation for cargo lifting and transfer in air includes location of two main disks at sides of transport body with possibility of vertical turn. Over each main disk there are spiral sequences of ribs of the same orientation to generate under-pressure above their surfaces though rotation by additional disk which is placed over central part of the main disk with corresponding hole for rotation drive of additional disk with spiral ribs. Opposite to location of spiral ribs on surface of main disks a gear drive is fixed which is functionally connected with gearhead, and several pairs of restraining rollers are fixed. Between the rollers the inner flat-topped reinforcement rib with toothed surface of ground transfer wheel the diameter of which is made greater than main disk diameter. The gear drive is functionally linked with toothed surface of reinforcement rib of ground transfer wheel for its rotation. |
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Airborne vehicle of "flying saucer" type Invention relates to VTOL aircraft. The airborne vehicle contains frame of axially symmetric shape, fuel tank, instrument compartment, gas-turbine engine including compressor, combustion chamber, turbine, adjustable guide vein including nozzle blades installed with possibility to be rotated, and jet nozzle. Gas-turbine engine is installed along vertical axis of frame. Combustion chamber is made multisectional with fuel systems including fuel governors for each section. Each nozzle blade is equipped with drive. Number of nozzle blades is equal to number of combustion chamber sections. Nozzle blades are fitted between sections of combustion chamber. Compressor is made centrifugal with axial inlet and axial outlet. Fuel tank is installed inside the gas-turbine engine. Emergency landing engine is installed inside the jet nozzle. |
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Invention relates to flying belts. Proposed flying belt comprises cylinders with compressed gas, gas distributor, hoses, headband and belts. Gas cylinders are secured on holder to communicate via gas distributer and fixed gas duct with revolving propeller with jet drive fitted above headband and, via fixed tube, with horizontal ejector fixed on tail arm on the side opposite said headband. Gas distributor communicates via hoses with separate elements feeding gas to propeller and ejector. |
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Computer-controlled aircraft take-off, piloting and landing complex Proposed complex, apart from computer-controlled aircraft (CCA), comprises one or several remote control boards of pilot in command, one or several airfields and one or several useful load remote control boards, all above listed components being integrated by common info field. There can be used also air-traffic-control service with communication system that incorporates air traffic control hardware. Said useful load can represent photo- and video cameras, containers with medicines, items of mail, mobile communication hardware, atmosphere contamination pickups etc. Proposed complex allows operating traditional CCA in whatever zones, on whatever airfields and in airports equipped with air traffic control hardware. It helps relay service info to not only CCA pilot in command but to other CCAs and dispatchers, and transmit flight zone underlaying surface image and other data from onboard useful load to useful load remote control boards, as well as reveal conflict aircraft and avoid them in both automatic and semi-automatic operating conditions. It allows also CCA space flight training. |
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Invention relates to aircraft engineering and can be used in designing new flight vehicles. Proposed flight vehicle consists of dome-shaped compartment, partition, power plant, reduction gear, rotor, vertical shaft, bearing support, coil and three bearing wheels. A build-up ring-like wing has its fixed wing attached power plant, right below aforesaid partition ceiling. The said build-up movable wing is integrated with the rotor. Note that it has its ribs rigidly fixed to the hub and articulated with rotor blades. |
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Portable air-based optical visual monitoring complex Proposed complex includes remotely piloted flying vehicle and ground control terminal for information processing. Ground terminal is provided with processor with monitor, autonomous navigational system equipped with radio range-finder, barometer and antenna module with compass mounted on swivel unit and provided with drive, transceiver and control channel antenna. Flying vehicle has fuselage, flight support system, transceiving equipment and video information collection system. Mounted on fuselage are screw propeller, servo actuators for control of heading and pitching, emergency parachute landing system and radio beacon. Onboard flight support system is provided with processor, sensors, automatic return system phase meter and servo actuators. Sensors include micromechanical three-dimensional angular velocity and acceleration pickups, three-dimensional electronic compass, optical horizon sensor mounted on fuselage external surface and two barometers located in instrumentation compartment of fuselage; one barometer is connected with Pitot tube. Onboard transceiving equipment includes video signal transmitter with antenna and additional onboard range-finder and additional antenna for receiving the control signals. Video information collection system has two TV video cameras: observation camera and monitoring cameras. Proposed complex makes it possible to extend range of functioning due to use of aircraft-type self-contained platform at simultaneous low requirements to operator's qualification in pilotage. |
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Proposed tail unit includes streamlined planes located in lower section of fuselage and rotating around axes perpendicular to helicopter longitudinal axis passing through " point of application of lifting force + helicopter CG + point of securing the tail unit to fuselage". For horizontal motion of flying vehicle from steady vertical hovered flight position, bearing is mounted at point of attachment of tail unit to fuselage in such way that free rotation of tail unit around helicopter longitudinal axis is ensured. Respective turn of streamlined planes of tail unit shall exclude spontaneous rotation of tail unit around longitudinal axis for forming the horizontal force for horizontal motion. |
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Flying vehicle-convertiplane-amphibian (versions) According to first version, proposed flying vehicle has star-shaped wings which are spaced apart in each crossing vertical planes at even number of rays. Mounted on tips of wings in engine nacelles are power plants forming rigid structure in each crossing plane. Wings are provided with adaptive control surfaces for activation of them according to required modes of operation of power plants and counteraction to external disturbing factors in accordance with objective synergetic laws of unity of adaptation and control processes. Lower parts of engine nacelles have extension displacement-type alighting gears of changeable volume for retraction into internal cavities of engine nacelles. According to second version, flying vehicle is provided with even number of detachable aerodynamic wings of optimal aspect ratio. Their outer panels are secured on fuselage in between planes of star-shaped wings, thus forming different aerodynamic configurations. According to third version, each power plant of flying vehicle is provided with at least two coaxially independent drives with air screws in thrust ring. Each alighting gear may be made in form of folding corrugated cylinder and sphere. Interior of this cylinder is divided into two cavities by elastic transversal partition fitted with reducer valve. Envelope of sphere may be retracted into end cavity of cylinder. Its end face is provided with swivel tabs of fairing. Alighting gears may be provided with splittable doors with inflated ballonets secured in their cavities. |
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Method of creating lifting force for vertical takeoff flying vehicle Proposed method includes suction of air from upper surface of wing by means of impeller of centripetal fan and directing this air flow under lower surface of wing with the aid of centrifugal fan impeller. Air flow formed in radial direction relative to annular wing having asymmetric profile creates lifting force due to difference in pressures on lower and upper surfaces of wing. |
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Proposed method is used for forming flow over propeller blades at thickness ratio of 4-6% by increase of rotational speed of lifting propeller to magnitude of tip speed exceeding the sonic speed. Aero-space system includes aircraft stage 1, space stage 2 and alighting column with swivel brackets. Fuselages of stages are interconnected by means of coupling unit 3. Aircraft stage 1 has fuselage, wing 4, high-lift devices, power plant 7 and coaxial propeller. Each blade of coaxial propeller is mounted in hub by means of flexible spar 9 wound on drum which is connected with hub by means of clamp and lag hinge. Fuselage is provided with swivel stops of alighting gear. Space stage 2 has payload container, elevator and rudder. |
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Method of landing unmanned aerodynamic flying vehicle Prior to flight, electronic guidance equipment is mounted on board and ground landing equipment is placed on landing field. Horizontal flight and landing approach are carried out in aircraft mode with the aid of satellite radio navigational system. At final landing section, self-guidance of flying vehicle on landing field is performed by means of on-board electronic guidance equipment and ground landing equipment with the aid of one algorithms of correlation extremal navigation; soft landing is carried out by killing the kinetic energy of flying vehicle motion. Specific feature of proposed method as compared with known methods consists in decreasing flight speed after beginning of self-guidance of flying vehicle on landing field by means of power plant and aerodynamic control members and increasing angle of attack to critical magnitudes ensuring auto-rotation of flying vehicle at precession relative to direction of speed vector of its translational motion. Then, speed of its vertical motion relative to Earth is reduced by means of aerodynamic control members of flying vehicle to magnitudes ensuring complete killing of kinetic energy and soft landing on landing field. |
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Vertical takeoff and landing flying vehicle Proposed flying vehicle is provided with jet power plant located in center of flat wing round in plan. Power plant includes turbocompressors 13, bypass valves 14, receiver 15, adjusting valves 16 and four-section jet engine used for forming circular radially diverging air jet. Sections 17 of engine are designed for independent control during operation and are separated from one another by receiver. Upper part of body is designed for performing function of wing round in plan. |
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Proposed rotoroplane has fuselage located between two rotors with wings whose longitudinal axes are located in horizontal planes, wing angle-of-attack control mechanism and engine. Each wing consists of separate thin-profile blades; the profile is symmetrical relative to chord; blades are mounted at spaced relation and are connected into integral wing by means of ribs on which semi-axles are mounted; these axles are received by holes in struts rigidly connected with rotor shaft. Reflecting board-wing is mounted after each rotor in parallel with axis of its shaft on framework secured on tail boom; this board-wing is directed to rotor whose section is made from deformable material. Wing angle-of-attack control mechanism has hub with rings mounted on cylindrical surface of its free end; these rings are connected with tenon on rib of each wing by means of rod. Other part of hub is located in ports of vertical and horizontal slide blocks moved simultaneously with hub relative to axis of shaft of rotor passing inside this hub. End part of rotor shaft is provided with ring for elimination of action of gravity load; this ring is rigidly connected with strut on tubular part of rotor shaft; its cylindrical surface is received by grooves secured on fuselage. |
Another patent 2513644.