By generating vortices (B64C23/06)

B64C23/06                     By generating vortices(68)

ethod and system of aero/hydrodynamic control of newtonian fluid flow in radial turbomachine // 2642203
FIELD: machine engineering.SUBSTANCE: method and system for aero/hydrodynamic control of newtonian fluid flow in the radial turbomachine which use conformal vortex generators is described.EFFECT: improvement of energetic efficiency and possibility to control various points in turbo-compressor or processing device for aero/hydrodynamic treatment of newtonian fluid flow.32 cl, 21 dwg

Aircraft configuration having spin resistance // 2640669
FIELD: aviation.SUBSTANCE: aircraft comprising of a fuselage, configuration with a T-tail assembly and a high wing, having a leading edge connected to the upper part of the fuselage, where the high wing comprises of the first region adjacent to the fuselage and the second region adjacent to the wing tip, with the first region being adjacent to the second region, and where, at large angles of attack, the stall element and a separate air flow, associated with it, are isolated by discontinuity at the leading edge of the wing within the first region and the air flow below the T-tail assembly in such a way as to stay away from the flight controls located within the second region and controls relating to the T-tail assembly. The wing of the aircraft contains the first region near the root of the wing and the second region near the wing tip. The first region and the second region adjoin each other along a continuous boundary. Discontinuity of the leading edge is done to form at high angles of attack aerodynamic partitions along the continuous boundary, isolating the stall element and separate air flow, associated with it, within the first region and air flow below T-tail assembly. The aircraft is characterized by the use of a wing.EFFECT: increase of spin resistance by isolating the stall element.22 cl, 6 dwg

Aircraft wingtip // 2637233
FIELD: aviation.SUBSTANCE: crescent-shaped aircraft wingtip has a front and back edges made of non-linear shape, convex along the entire length, consists of profiles with a curvature (f=0.005-0.02), which is increased in relation to the end section of the wing, with a smaller relative thickness (c=5-15%) and large negative values of the twist angles (ε=5-25%). The tail part of the tip is made with a deviation of the vertex coordinate backstream from the rear edge of the wing by a distance (0.5-0.7) bt, where bt is the tip chord of the wing.EFFECT: increased aerodynamic quality of the aircraft and improved fuel efficiency.4 dwg

Supersonic aircraft // 2613747
FIELD: aircraft engineering.SUBSTANCE: supersonic aircraft comprises fuselage, short-span wing with large sweep extension in root part, vertical fins with rudder, power plant with air intake, elevons. On wing leading edge aerodynamic tooth is installed, and on wing trailing edge fixed planes with slots along wing chord are made, comprising single aerofoil section with outer wings.EFFECT: invention is aimed at expansion of angle of attack at subsonic fight speeds.1 cl, 12 dwg

ethod of lift force creation and device for its implementation // 2601495
FIELD: physics.SUBSTANCE: group of inventions relates devices, creating lift force in viscous fluid. Proposed method of lift force creation on surface consists in creation of pressure difference, acting on opposite sides of surface by increasing circulation of viscous fluid around it. On one of side surfaces region formed, bordered by layer of particles of viscous fluid, and it is turned towards surface. Viscous fluid jet is sampled from region to form medium jet, flowing into area and accelerated therein as flowing around surface, limiting area for reduction of static pressure in it. Particles in layer of medium are whirled in intense swirl, layer of stable vortices, attached to surface is formed. Medium jet, inflowing into low pressure area and accelerated in it, is swirled in high-energy vortex bundle. Device to create lift force on surface has container, filled with viscous fluid, channels connecting said tank with top surface. Container with help of confuser channel is connected tangentially with vortex formation device, made up of cylindrical vortex chamber connected with help of shaped channels with top surface. Vortex chamber has helical shape with side tangential inlets.EFFECT: group of inventions is aimed at expansion of technical facilities.3 cl, 3 dwg

Retractable turbulence promoter to reduce stall speed // 2600014
FIELD: aviation.SUBSTANCE: method of bearing surface flight at low speeds includes deviation of bearing surface front edge high-lift system component, extending turbulence promoter movably connected to high-lift system component of front edge from slot the bearing surface and removal of turbulence promoter under bearing surface in response to movement of bearing surface front edge high-lift system component in nominal position. Extensible turbulence promoter comprises front edge high-lift system component attached to bearing surface, aerodynamic surface attached to bearing surface and sliding turbulence promoter connected to bearing surface, front edge high-lift system component or to both of them. Method of bearing surface controlling at low speeds of comprises enabling bearing surface flowing with flowing medium, lowering of front edge high-lift system component leading edge pivotally connected to bearing surface from nominal position into deflected position; opening of several retractable turbulators through slots in first bearing surface in response to lowering of deflected leading edge high-lift system component. Extending turbulence promoters are made with possibility of their closure under high-lift system component rear edge while front edge high-lift system component is in nominal position.EFFECT: group of inventions is aimed at high efficiency of bearing surface operation at low speed.20 cl, 10 dwg

Aircraft with aerodynamic element and method of its flying // 2597046
FIELD: aviation.SUBSTANCE: aircraft comprises aerodynamic element, compressed air source, actuator for jet blowing air and control device. Aerodynamic element has a side edge and a hole located on side edge or near it and oriented mainly in direction of flow. Actuator for jet blowing air includes a rotating element with an inner channel and a hole communicated with inner channel. Control device is configured to connect inner channel of rotating element with compressed air source, as well as to actuate rotary element so that its inner channel communicates with hole of aerodynamic element through hole in rotating element. Compressed air from source is blown from hole of aerodynamic element in series at multiple points located along length of hole of aerodynamic element at a distance from one end of hole of aerodynamic element increasing in time. Method of flying aircraft with aerodynamic element includes forming, onside edge of aerodynamic element with upper and lower surfaces, or near to side edge, a slot which during flight is oriented mainly in direction of flow; and blowing air from slot, carried out in series at multiple points located at length of slot, at a distance from one end of slot, increasing in time.EFFECT: group of inventions is aimed at reduction of intensity of cocurrent vortices and reduction of noise from aircraft.12 cl, 6 dwg

Wing tip // 2575739
FIELD: aircraft engineering.SUBSTANCE: claimed wing tip is meant for attachment to the wing outer end (401) to make the wing plane. It comprises the top wing-like element (404) extending upward relative to the wing plane and having the trailing edge, and bottom wing-like element (407) fixed relative to said top wing-like element and having the root chord (412) and trailing edge (417). Said root chord crosses the top wing-like element. Note here that the bottom wing-like element extends downward from the point of intersection. The top wing-like element features larger sizes than the bottom wing-like element. Note also that trailing edge of the bottom wing-like element abuts on trailing edge (416) of the top wing-like element at the point of intersection. Interior angle between said top and bottom elements at the point of intersection is smaller than or equal to 160 degrees. The wing comprises wing tip. Aircraft comprises said wing tip. Invention discloses also the mounting or replacing of said wing tip, updating of wing tip and operation of the wing with this wing tip.EFFECT: better flight performances.19 cl, 13 dwg

Structure reducing aerodynamic drag of body in fluid, its use, body containing such structure, flow channel, jet engine, and drive containing such body, film for such body // 2565641
FIELD: engines and pumps.SUBSTANCE: group of inventions refers to aerodynamics. Group of inventions includes the body flowed by the fluid, flow channel, jet engine, drive, film for such body, and use of structure flowed by the fluid. The fluid flowed body (10) contains a fluid (30) flown surface (12), having common shape determining main direction (14) of flow over the surface (12). The surface (12) contains structure decreasing the aerohydrodynamic drag of the body (10), that contains cavity (16.2-16.3) having cross-section essentially in form of round segment to create the fluid vortex (26.2-26.3). The structure contains input section (18.2-18.3) inclined relatively to the main direction of the flow towards the cavity (16.2-16.3), and located along the main flow direction upstream the cavity (16.2-16.3), to remove the fluid flow (24) in the cavity (16.2-16.3). The structure is made with possibility of the fluid vortex (26.2-26.3) creation inside the cavity (16.2-16.3).EFFECT: group of inventions reduces aerohydrodynamic drag of the body in fluid.16 cl, 2 dwg

ethod of concentrated vortex reduction and aircraft wing tip used to this end // 2558415
FIELD: transport.SUBSTANCE: aircraft wing has tip with small wing arranged to displace over wing end section, guide device and actuator connected with small wing to drive it in flight relative to the wing. Proposed method comprises initiation of actuator for liner displacement of small wing relative to guide device from initial fixed position whereat glove vortex is stable to the state of continuous motion. At said state said small wing is displaced to temporary auxiliary position remote from initial fixed position. It is set at the angle to the plane extending through aircraft lengthwise or crosswise axis to change the angle of attack. Continuous motion state is maintained for time interval required for destruction of said concentrated vortex. In compliance with another version, this method is intended for aircraft wings. Wing tip is adapted for application of method versions. Aircraft is provided with above described wing tip.EFFECT: decreased turbulence.14 cl, 11 dwg

Device for improvement of aircraft lifting properties // 2556745
FIELD: aviation.SUBSTANCE: device for improvement of aircraft (A) lifting properties is a vortex generator designed as a lining pad installed on internal section of a slat. The device is designed as a profiled section of the slat continued to the wing fillet with a hull, it is formed along two sections of the wing leading edge: the first section - the internal plane of the slat; the second section - crossing of the part of the wing fillet leading edge with the hull and the plane parallel to the aircraft symmetry plane. The section is taken so that it continues the internal plane of the slat along the wing span without break. The device span size cover about 75% of the distance between the internal plane of the slat and the aircraft hull. The device has a cut in the lower part. The cut has a shape of semi-parabola limited by the plane parallel to the plane of an internal end face of the device, the cut is formed by crossing of internal and external surfaces of the device. The cut height is 34% from the dimensional height of the device.EFFECT: improvement of aircraft lifting properties at near-critical angles of attack.7 dwg

Aircraft wing // 2551829
FIELD: transport.SUBSTANCE: invention relates to aircraft engineering. Said wing represents a flat plate with thickness equal along the profile and sharpened front tip. Aircraft wing comprises inner bearing carcass, top and bottom envelopments, flaps and ailerons. Said wing makes in plan a cubic parabola with axis installed parallel about fuselage axis. Wing top skin is provided with vortex whirling comb composed of three nozzles to convert oncoming laminar airflow into turbulent whirling shroud.EFFECT: decreased drag.3 dwg

Aircraft wing // 2537348
FIELD: aircraft engineering.SUBSTANCE: aircraft wing comprises triangular body secured to fuselage and furnished with vertical oncoming airflow splitters arranged at body edge each having leading and trailing sections. Leading section is arranged ahead of body edge parallel about vertical plane extending along fuselage. One of trailing edges is attached to top airfoil and bent aside from fuselage. Another trailing section is secured to bottom airfoil and bent towards fuselage. Angle of the bend of splitter trailing section secured to top airfoil makes 5-15 degrees. Angle of the bend of splitter trailing section secured to bottom airfoil makes 5-15 degrees.EFFECT: increased lift.3 cl, 5 dwg

Device for improvement of aircraft lifting properties // 2537076
FIELD: aviation.SUBSTANCE: device for increase of lifting properties of an aircraft is designed as a flat ridge with the rounded leading edge, leading edge sweep angle near fuselage is 40°÷50°. By means of smooth rounding the leading edge passes into a lateral edge forming with the fuselage surface an angle 5° maximum. Trailing edge is straight and forms with the lateral edge a sharp angle 60°÷75°. The device length amounts 10÷15% of the chord of the near-board section wing of the aircraft. The device height amounts 20÷25% of its length. The central part of the device is of constant thickness. The device is installed on the fuselage as a vortex generator.EFFECT: increase of wing lift coefficient.4 dwg

Aircraft wing tip // 2525335
FIELD: aircraft engineering.SUBSTANCE: invention relates to aircraft engineering. Proposed wing tip has end plate with aerodynamic sweep of light elongation and sharp leading edge arranged at end plate end outer side. Tailing edge of extra aerofoil is aligned with rear edge of end plate while nose flap is located at leading edge of end plate under the level of tailing edge, sweep making 60-85 degrees. Leading edge sweep makes 60-85 degrees. Extra aerodynamic sweep of light elongation has extra sharp leading edge made at end plate inner side to make with leading edge outside end plate outer side the sweep of 76-87 degrees.EFFECT: higher aerodynamic efficiency of wing.3 dwg

Nonplanar wing tip for airplane wing and wing containing such tip // 2521458
FIELD: transport.SUBSTANCE: tip (W; W1, W2) of wing (T; 10a, 10b) contains base (E1) and vertex (E2). Local dihedral angle of wing tip (W; W1, W2) is continuously increasing or decreasing from base (E1) to vertex (E2). Local sweep along rear edge (50) is continuously increasing in its propagation from wing tip (W; W1, W2) base (E1) to vertex (E2). Local sweep along front edge (60) is continuously increasing in propagation of front edge (60) from the base (E1) to the first intermediate point (61a), is continuously decreasing from the first intermediate point (61a) to the second intermediate point (62a) and continuously increasing from the second intermediate point (62a) to the area forward of vertex (E2) of wing tip (W; W1, W2). Wing contains tip.EFFECT: improved aerodynamic characteristics.10 cl, 6 dwg

Aircraft wing // 2513344
FIELD: aircraft engineering.SUBSTANCE: aircraft wing has top and bottom airfoils and elements to deflect stream-down airflows composed of flaps and ailerons. Said elements to deflect stream-down airflows feature edge curves made in plates attached to said elements. Edge curve is shaped to sinusoid or asymptote.EFFECT: simplified design.5 dwg

Aircraft wing // 2506200
FIELD: transport.SUBSTANCE: invention relates to aircraft engineering. Aircraft comprises fuselage with wings secured thereto and furnished with deflectors of flow over top and bottom airfoils, and elongated sharp-ends body and equipped with blades secured thereto radially. Said blades are arranged in helical line and feature variable height increasing in direction opposite oncoming airflow.EFFECT: limited vortex flows nearby wing end.3 dwg

Aircraft wing // 2494920
FIELD: transport.SUBSTANCE: invention relates to aircraft engineering. Aircraft comprises fuselage with wings secured thereto and furnished with deflectors of flow over top and bottom airfoils, tail unit, engine and undercarriage, and elongated sharp-ends body with pressure nozzle with its side secured to wing end faces. Said elongated body is shaped to polygon with variable-height vanes attached vertically to faces. Said vanes at said faces are inclined relative to axial line of said elongated body. Pressure nozzle is located at the end of elongated body along its axial line.EFFECT: constricted vortex flow nearby wing end face.3 cl, 3 dwg

Aircraft // 2494919
FIELD: transport.SUBSTANCE: invention relates to aircraft engineering. Aircraft comprises fuselage with wings secured thereto and furnished with deflectors of flow over top and bottom airfoils, tail unit, engine and undercarriage. Mesh plate arranged parallel with vertical plane extending along fuselage is attached to the end of every wing. Said mesh plate is shaped to trapezium and has openings increasing in size in direction from said top and bottom airfoils.EFFECT: constricted vortex flow nearby wing end face.2 cl, 3 dwg

Aircraft wing // 2494918
FIELD: transport.SUBSTANCE: invention relates to aircraft engineering, particularly, to civil and transport aviation craft. Aircraft wing comprises carcass, skin, and deflectors flow over top and bottom airfoils. This wing is provided with mesh plate arranged nearby end face along bottom airfoil. Said plate slides from slot-like opening at the wing end face. Said mesh plate is shaped to trapezium and has openings increasing in size in direction from said top and bottom airfoils.EFFECT: constricted vortex flow nearby wing end face.3 cl, 4 dwg

End airfoils with recesses and appropriate systems and methods // 2492111
FIELD: transport.SUBSTANCE: invention relates to end airfoils including surfaces with recesses and to method of rag reduction. Aircraft system comprises wing and end airfoil (winglet, end plates, Whitcomb endplate) connected with wing end outer section. End airfoil has first surface facing fuselage side and second surface directed outward. First surface comprises area with recess. Note here that the wing includes airfoil sections located from wing inner area to outer area. End airfoil is used with the wing that features no changes on common shapes of airfoil sections located nearby wing outer area.EFFECT: decreased influence of interferences caused by flows at wing-end airfoil transition, reduced drag.13 cl, 13 dwg

Leading edge flap and method of its flowing // 2487051
FIELD: aircraft engineering.SUBSTANCE: aircraft leading edge flap coupled with main wing and including streamlined surface comprising tail lower edge. Part of said rail lower edge is shaped with even wavy line or wavy line with angular points along wing span. Proposed method consists in using proposed aircraft leading edge flap.EFFECT: lower aerodynamic noise in takeoff and landing.4 cl, 7 dwg

Aircraft and wing, wing tip and set of parts there for // 2472674
FIELD: transport.SUBSTANCE: aircraft comprises wing 5 with positive dihedral angle, edge and wing edge device 7 secured in the area of edge. Wing edge device extends, generally, downward and has area 7d beveled at more than 180°C. Area 7d serves to create lift in flight. Said area 7d beveled at more than 180°C may be arranged at distal end 11 of wing edge device 7. Part of wing edge device located in proximal end has no area beveled at more than 180°C. Wing edge may be swept and elastically strained in flight.EFFECT: higher operating performances.15 cl, 12 dwg

Aircraft with inductive drag reducer // 2437800
FIELD: transport.SUBSTANCE: aircraft comprises fuselage, two wings arranged in symmetry on fuselage sides, and jet engine nacelle secured by means of pylon 18 to every wing. Every said pylon is provided with shaped bearing housing 20, 30 arranged to create resultant propulsion by oblique airflow. Housing 20, 20 extends from end 20a, 30a secured on jet engine pylon 18 toward elongation inclined for 30° with respect to wide wing top surface.EFFECT: lower drag.8 cl, 7 dwg

Aircraft aerodynamic flap with stall affecting device // 2428354
FIELD: transport.SUBSTANCE: invention relates to aircraft engineering. Proposed flap 11 incorporates stall affecting device arranged on flap side edge with wing sections 13 extending along wing span to form air passages for incoming air to pass there through. High-efficiency flap comprises channel extending onto flap side edge through which compressed air may be fed into noise-generating vortex. Stall affecting device comprises compressed air feed device, side edge outlet channel and jointing element.EFFECT: reduced noise.18 cl, 5 dwg, 2 tbl

Aircraft drag flap // 2425780
FIELD: transport.SUBSTANCE: aircraft drag flap arranged either atop wing or on fuselage is fitted at angle to airflow flowing there over. Flap 20 comprises free edge 21 arranged at angle is shifted from aircraft outer skin create wing-tip vortex in said airflow. Said free edge 21 comprises some separate sections 22 with their edges dividing edge vortex into some partial vortices and are formed with the help of recesses on free edge 41 of drag flap 40 that do not penetrate thought flap.EFFECT: reduced noise.6 cl, 3 dwg

Aircraft with improved central fairing // 2424157
FIELD: transport.SUBSTANCE: invention relates to aircraft engineering. Aircraft 10 comprises fuselage 12, two wings 14, 16 whereto engine nacelles are attached, each being secured by central fairing 18, 20 to fuselage on its both sides. Said central fairing comprises two opposed surfaces jointed to wing upper and lower surfaces arranged along fuselage. One of said surfaces has local deformation of shape geometry to create aero dynamical lateral disturbances of airflow from central fairing to wing to control airflow over wing surface.EFFECT: perfected aircraft design.14 cl, 21 dwg

System and device to reduce turbulence in aircraft wake // 2399556
FIELD: transport.SUBSTANCE: set of inventions relates to aircraft engineering. Proposed system comprises a device secured to aircraft tail part to periodically rotating about the axis located at, approximately, right angle to flight direction. Said device is arranged on wing upper surface 4 and comprises stationary element 6 and first 7, 9 and second 8, 10 wing elements pivoted behind said stationary element 6 and can be spaced apart along flight direction. Method is distinguished by using aforesaid device that prevents swirling of airflow nearby outer wing in swinging about axis of rotation.EFFECT: reduced turbulence in aircraft wake.5 cl, 10 dwg

Aircraft wing tip and its vortex generator // 2389649
FIELD: transport.SUBSTANCE: invention relates to aircraft engineering. Aircraft wing tip comprises generator of vortex with direction of rotation originating at wing and casing. Vortex generator represents nacelle with inlet and outlet swirlers. Casing represents a thin-wall structure with constant-radius inner surface extending along wing end chord with unclosed cross section that forms lengthwise cutout. Swirler is furnished with diffuser. Said casing lengthwise cutout is made so that cutout top edge forms central angle on casing axis, while its bottom edge forms that on casing axis. Inlet device can have confuser deflected from wing chords lane downward, while casing tail end is inclined upward.EFFECT: higher aerodynamics and ring load bearing properties.10 cl, 7 dwg

Aircraft wing tip // 2385265
FIELD: transport.SUBSTANCE: invention relates to aircraft engineering. Aircraft wing tip comprises channel with inlet and outlet holes. Inlet hole represents an air intake arranged on lower front surface and communicated with conical channel with end cross section with diametre of 0.05 to 0.2 of the length of chord of wing tip section and is located at the distance of 0 to 0.2 of chord length from rear edge along flow direction. Channel axis is located on 0 to 0.2 of chord length above the plane of chords. Channel midsection accommodates disk-like rotary flap with its axis perpendicular to channel axis. Flap can be rotated by airflow.EFFECT: higher lift and reduced drag.3 cl, 7 dwg

Device to control vortex street generated by aircraft control surface elongated element // 2377160
FIELD: aircraft engineering.SUBSTANCE: device to control vortex street comprises control device (8) mounted on clamping element (11) of elongated element (5) and on control surface (4) so that its base (12) comes in contact with front edge (6) of its aforesaid control surface. Said control device (8) features triangular shape in the plane perpendicular to its lengthwise axis and having two adjacent sides forming lateral surfaces interconnected by rounded edge. Aircraft incorporates vortex street control device.EFFECT: reduced drag.6 cl, 6 dwg

Friction reduction method for axisymmetric body and related device // 2357893
FIELD: mechanics; aircraft construction.SUBSTANCE: inventions relate to aeromechanics, mainly to friction reduction method for axisymmetric body and related devices. Toroidal vortex with controlled parametres is generated in a boundary layer of axisymmetric body by periodic air flow blowing/suction through the circular slot available in axisymmetic body wall. The related device includes periodic vibrations source coupled with flow running over axisymmetric flow. The above mentioned circular slot in the wall of axisymmetric body is made so that it is directed to the longitudinal axis x at a negative angle. The longitudinal axis x is directed along generatix of axisymmetric body, wherethrough air is blown/drawn off at controlled amplitude and frequency by means of periodic vibrations source, for example dynamic loud-speaker.EFFECT: reduced effect of superficial friction component in axisymmetric body by controlling vortex by frequency and intensity.4 cl, 4 dwg, 1 ex

ethod and device for varying lift // 2332330
FIELD: transport.SUBSTANCE: invention relates to aviation. The method of varying the lift of a body in flowing medium consists in affecting the flow by one or several flexible tape-like spaced elements extending from the body surface flown over by the said medium. The device is also proposed incorporating one or several flexible tape-like spaced elements extending from the body surface flown over by the flowing medium.EFFECT: reduction of drag.9 cl, 2 dwg

Configuration of aircraft with improved aerodynamic characteristics // 2302975
FIELD: aviation.SUBSTANCE: aircraft (10) has fuselage (12) connected with wings, air intake (46), nose section (52) of fuselage of varying cross section and vortex generation control unit (72) located on leading-edge wing extension whose shape makes it possible to make symmetrical break of vortices on said extension and medium and large angles of attack; it is engageable with tail sections (44 and 38) spaced apart so that leading edge (36) of vertical fin (38) gets beyond trailing edges of each wing for maintenance of stability in transversal direction. Ratio of area of leading edge extension and height of vortex generation control unit is equal to 2.35 m and tolerance range changes from +100% to -50% of this magnitude.EFFECT: improved aerodynamic properties at large angles of attack.8 cl, 18 dwg

ethod of flight operations organization // 2296084
FIELD: aerodynamics; designing of flying vehicles, organization of aircraft motion in water.SUBSTANCE: proposed method consists in forming regular structures for finding the conditions when axis of natural vortices is directed not in way of flow but at any angle required by conditions of flow. Infinite sequence of artificial vortices is similar to roller bearing located between body and medium. Proposed method provides for creating the lifting force for flying vehicle on base of proposed model of flowing around solid bodies by continuous media. Proposed method consists in forming the determined vortices on upper surface of wing which are directed to overwing flap where they are broken. Vortices rolling over upper surface of wing without sliding increase in size. Their destruction within overwing flap results in increase of pressure, thus creating lifting force for aircraft.EFFECT: enhanced efficiency.8 cl, 8 dwg

ethod of control of flow around flying vehicle // 2283794
FIELD: aeronautical engineering; rocketry and space engineering; technology of control of flow around flying vehicle.SUBSTANCE: proposed method consists in delivery of gas to incoming flow in front of nose section of flying vehicle. Density of this gas is lesser than density of medium; gas is fed to points of aerodynamic drag of flying vehicle where porous coat is formed; pores of this coat are open to surface; scale of these pores is lesser than that of vortex generation. Gas is delivered at periodicity of generation of turbulent vortices to turbulence generation zone at phase shifted by 45-135 degrees. In realization of this method coat may be formed at points where shock wave is formed. It is good practice to feed gas to porous coat from reservoir containing sorbent separating gas till gas desorption temperature has been attained. Gas is mainly fed to upper edge of wing. It is good practice to make coats from catalytically active heat-accumulating material and to realize endothermic process during passage of gas through it. Front surfaces of wings and nose sections of flying vehicles may be covered with coats of low electron emission energy from the following series: barium oxide, titanium carbide, zinc oxide, copper oxide rare-earth metal oxide and n-semiconductors.EFFECT: possibility of changing aerodynamic properties in turbulence generation zone.16 cl

Engine // 2270785
FIELD: devices for creation of aero- or hydrodynamic forces for transport facilities with the aid of rotating members.SUBSTANCE: proposed engine has housing and two cones with surfaces rotating in opposite directions. Rotating surfaces are provided with cells in form of tooth spaces and teeth. Teeth on surface of front cone are bent in way of flow around the cell and teeth on surface of rear cone are bent towards incoming flow which is circular in shape and is caused by rotation of surfaces of cones. Surface of each tooth space has form of question-mark in section. As a result, reduced pressure is built-up in cells of rotating surface of front cone and increased pressure is built-up in cells of rotating surface of rear cone, thus creating the thrust along axis of rotation of cones.EFFECT: extended field of application of thrust creating devices for various vehicles running in air and water media.6 dwg

Device for airflow control of hypersonic flying vehicle // 2268847
FIELD: rocketry and space engineering.SUBSTANCE: proposed device has nose section 1 and central and additional aerodynamic needles 3 made in form of thin cylindrical rods which are stowed in special passages made in nose section of flying vehicle. One passage is located along axis of symmetry and other passages are located at some distance from axis of symmetry smoothly over circumference whose center lies at axis of symmetry. Each passage is provided with mechanism for delivery of aerodynamic needles towards incoming flow; provision is made for extension of each needle through definite length for forming special configuration of set of needles which is necessary for their joint operation in airflow control.EFFECT: possibility of obtaining constant coordinate of center of pressure of hypersonic flying vehicle; reduced force of drag; possibility of forming control forces and moments for manoeuvring in atmosphere.4 dwg

Device and method of reduction of vortices behind aircraft // 2268844
FIELD: reduction of vortices behind aircraft.SUBSTANCE: aircraft has starboard and port wings for forming lifting force; wings are provided with landing flaps for forming considerable lifting force. Vortex generator for forming controllable disturbance vortex is made in form of additional flap whose base is located in area of 10-% semispan to the right and to the left from external end of landing flap and beginning at 60% of depth of lifting wing profile. During flight, additional flap is kept in extended position; it may be retracted in wing when not in use. Controllable vortex is formed with this device.EFFECT: reduction of vortices behind aircraft at landing approach.15 cl, 9 dwg

Device for producing propulsion // 2253514
FIELD: aircraft.SUBSTANCE: device comprises vortex pipe with a scroll for supplying and accelerating air and cold and hot end sections. The cold end section of the vortex pipe is provided with a ring plate. The diameter of the inner opening in the plate should be chosen to allow it to be fit on the vortex pipe with interference for increasing the area of the face of the cold section. The vortex pipe can be mounted in the guiding member which defines the inclination of the vector of the propulsion to the horizon. The hot section of the vortex pipe should be provided with a valve.EFFECT: improved design.3 cl, 2 dwg

The wing tip of the aircraft with a vortex flow generator // 2233769
The invention relates to the field of aviation

The active system to the early destruction of cascading eddies // 2223892
The invention relates to the field of aviation

The method of forming the lifting force, the airplane, the takeoff and landing // 2223891
The invention relates to the field of air transport

Wing // 2207967
The invention relates to the field of aviation

A device for weakening vortex trail mechanized wing (options) // 2174483
The invention relates to aviation

A method of reducing drag of a moving object and a device for its implementation // 2173658
The invention relates to the field of aerodynamics

Hypersonic aircraft // 2172278
The invention relates to aviation

Aircraft with a carrying case // 2168446
The invention relates to aviation
 
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