(57) Abstract:Usage: devices to modify the characteristics of the aircraft and the stabilizing surfaces that are installed on the wings.The inventive vertical aerodynamic surfaces are rigidly interconnected and are located on the ends of the chord of the wing with the possibility of longitudinal movement. When failure of the main on-Board electrical system of the aircraft shafts generators, which are cross-shaped aerodynamic surfaces automatically disinhibited, vertical surfaces move back to horizontal surfaces and together they begin to work as an air turbine, including the operation of emergency generators electrical system of the aircraft. Effect: reduction of induced drag of the wing and increase the level of safety. 9 Il. The invention relates to aircraft, and more specifically to methods and devices for modifying the aerodynamic characteristics of the aircraft and stabilizing surfaces, mounted on the wings.Known aircraft with diffusers war the wing on its end chord 
This solution serves to reduce the magnitude of the inductive resistance of the bearing surface.The disadvantage of this aircraft is its narrow function, increasing safety, for example, failure of on-Board electrical system.The closest technical solution is known for the development of the consortium Airbus industry design for wide-bodied aircraft, a-330 and a-340 limit the aerodynamic surfaces of the rear end of the chord of the wing, reducing its inductive resistance in flight. Failure of on-Board electrical system these cross aerodynamic surfaces disinhibited and working as an air turbine, result in rotation of the rotors of the generators of the emergency electrical system of the aircraft, and the generators are located in the wing tips 
However, this solution is characterized by the lack of reduction in induced drag of the wing due to the removal end of the aerodynamic surfaces of the main place of education a powerful end vortices formed near the toe end of the chord of the wing. This is evidenced by conventional, proven practices, the installation location of the limit kr is the solution induced drag of a wing of an aircraft.The objective is achieved by the fact that in the proposed aircraft containing the wing and located on the ends of the chord of the wing power generators, on the shafts which are installed crosswise aerodynamic surface, motionless in normal flight and automatically rastormazhivanie failure of on-Board electrical system, forming in this case, the air turbine, vertical aerodinamicheskoi surface are movable in the longitudinal direction, rigidly connected to each other, equipped with a closed hydraulic system and Bolotnikova switch that interacts with the brake device, and a guide for longitudinal movement of the vertical aerodynamic surfaces is a groove in the shaft of the generator, which communicates connecting a jumper between the two vertical aerodynamic surfaces.In Fig.1 shows the device in normal flight, the vertical aerodynamic surfaces are in the front position, top view; Fig.2 is the same, with the failure of on-Board electrical system, vertical aerodynamic surfaces are in the rear position and work as an air turbine, a top view; Fig. 3 is the same, rear view in the first section of the shaft of the generator and the lodgments in section; in Fig.5 the front part of the fairing on the tail of the wing chord with the proposed device (upper trim panel fairing conditionally withdrawn and aerodynamic surfaces not shown), a top view; Fig.6 section a-a in Fig.5; Fig.7 section b-B in Fig.5; Fig.8 brake device with stopper and Bolotnikova the switch in the normal flight; Fig.9 is the same, in the position of the failure of on-Board electrical system, i.e. in the position of the air turbine.Aircraft wing contains 1, at the end chord of which is fixed the inner 2 and outer 3 horizontal aerodynamic surfaces and interconnected by jumpers 4 upper 5 and lower 6 vertical aerodynamic surfaces, made with a possibility of longitudinal movement of the latter along the end of the chord of the wing. Horizontal aerodynamic surfaces 2 and 3 are installed in the cavity of the tip chord of the wing at its rear edge. In stationary front part of the fairing 7 is an electric generator 8, the brake disc 9 which is rigidly fixed on a hollow shaft 10 of the electric generator 8. In the nose of the fairing 7 pinned cylinder 11, the piston rod of which is pivotally attached to the crosspiece 4 between the vertical aerod is cumulator 12, located in the cavity of the wing 1 and the slide switch 13. Inside the front part of the hollow shaft 10 is the piston rod of the hydraulic cylinder 11, and in the rear part of the shaft 10 is made a groove 14 for moving the jumper 4. The tail section of the shaft 10 is rigidly attached to the rear part of the fairing 7, separated from the front, and horizontal aerodynamic surfaces 2 and 3. In the front part of the fairing 7 rigidly fixed two lodgement 15, in which is located the shaft 10 of the electric generator 8. The braking device comprises two solenoid 16, attached to the fairing 7. Located in the solenoids 16 cores 17 is attached through a spring 18 to the design of the fairing 7. By the end of the core 17 by a clamp attached to the lever to move the valve spool of the switch 13. On facing the brake disc 9 to the end of the core 17 made the space 19 with the brake Shoe 20, and the inside of the groove in the core 17 is spring-loaded latch 21 that communicates with a transverse slot 22 in the brake disk 9. To the inner surface of the brake pads 20 is attached a friction strip 23, which interacts with the brake disc 9. The length of the groove 14 in the shaft 10 corresponds exactly to the sum of the length of the lintel 4 and length required PE the existing way.During normal operation in-flight on-Board electrical system of the aircraft all four aerodynamic surface using clamps 21 included in slotted brake disc 9, retarded. Aerodynamic surfaces 2 and 3 are located somewhat to the rear of the wing 1 horizontally and work as normal, but additional bearing surface, and the vertical aerodynamic surfaces 5 and 6 with a closed hydraulic system, the hydraulic cylinder 11 and the spool switch 13, directing the slurry on retraction of the rod are located in the front position. Thus the top 5 and bottom 6 of the aerodynamic surface of the work, known as leaf wings, greatly reducing induced drag of the wing 1, effectively preventing the formation of a powerful vortices on the wing 1 (one of the variants of "wings of Witcombe"). Lower effect and horizontal aerodynamic surfaces 2 and 3, which is associated with some remove them from the zone of origin of the powerful vortices at the wing tips. Failure of on-Board electrical system, such as failure of engines, de-energized solenoids cores 16 and 17 by means of springs 18 away from the brake disc 9 and removed from the slots 22, the latches 21. The shaft 10 is given in the front of the cylinder 11. The slurry from the rear side of the cylinder 11 extends through a nozzle of small bore, campfire efforts cylinder 11 and the drag of the aerodynamic surfaces 5 and 6, making their movement back smooth and bumpless. The cradle 15, interacting with the crosspiece 4, does not result in the movement to turn back the aerodynamic surfaces 5 and 6 to complete the transition jumper 4 in the tail part of the fairing 7. After moving all cross aerodynamic surfaces 2, 3, 5 and 6 under the influence of powerful trailing vortices generated at the wing tips, start to rotate, turning in the air turbine, operate the generator 8 is connected electrically with the emergency electrical system of the aircraft.In the case of recovery in the air of the main on-Board electrical system of the aircraft are powered solenoids 16, the lever slide switch 13 perepuskat slurry in the rear part of the cylinder 11. At this time, the shaft 10 of the electric generator 8 is retarded and is fixed in the initial position, and the vertical aerodynamic surfaces 5 and 6 come forward smoothly to its original position for normal flight.When polnogo energy-intensive equipment or devices, set in this flight on Board the aircraft, possibly temporary remote power energy generators 8.Use this emergency generators 8 eliminates the use of additional sources of supply for such additional, temporarily installed on-Board equipment.In addition, the use of generators 8 airborne allows you to set the propulsion engines are less powerful generators that reduces their drive fuel.The application of the proposed device allows to reduce the induced drag of the wing in flight, to increase the range, gain fuel savings and other positive effects. AIRCRAFT containing the wing and located on the ends of the chord of the wing power generators, on the shafts which are installed crosswise aerodynamic surface, motionless in normal flight and automatically rastormazhivanie failure of on-Board electrical system forming this air turbine, characterized in that, in order to reduce induced drag of a wing flying apparatus is sealed between them equipped with a closed hydraulic system and Bolotnikova switch channels, interacting with the brake device, and a guide for longitudinal movement of the vertical aerodynamic surfaces is a groove in the shaft of the generator, which communicates middle connecting a jumper between the two vertical aerodynamic surfaces.
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
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
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.
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.
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.
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
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
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
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
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
FIELD: aeronautical engineering; various flying vehicles.
SUBSTANCE: proposed tip has end plate and is provided with additional swept aerodynamic surface of low aspect ratio with sharp leading edge mounted on the outside of end plate. Trailing edge of additional aerodynamic surface is combined with trailing edge of end plate. Nose is located on leading edge of end plate below level of trailing edge; sweep ranges from 60° to 85°.
EFFECT: enhanced aerodynamic efficiency at high subsonic speeds.
FIELD: power plants for auxiliary-purpose flying vehicles.
SUBSTANCE: proposed system includes panel of lifting surface of flying vehicle with device for localization of overflow of airflow; this device includes flow-through nacelle, power loop and air-jet engine with exit nozzle. Axis of nacelle lies in way of motion of lifting surface of flying vehicle; inlet part is made in form of side inlet window located on lower part of lifting surface panel. Power loop includes at least one wind wheel with at least one electric power generator which are arranged inside flow-through nacelle in parallel with inlet window. Engine is mounted in outlet part of flow-through nacelle.
EFFECT: extended field of application; enhanced safety of flight.
SUBSTANCE: proposed aircraft has fuselage, engines, landing gear and control cabin. Aircraft is provided with trough-shaped wing, vertical fins with rudders, stabilizer and elevons. Wing is mounted on fuselage which has no tail section. Vertical fins with rudders are mounted underneath the wing. Stabilizer and elevons are mounted on trailing edge of wing.
EFFECT: reduced mass; reduced drag; improved aerodynamic properties.
FIELD: aircraft control and stability devices.
SUBSTANCE: proposed device is made in form of stall fences mounted on lower surface of wing or on tail section of aircraft symmetrically relative to longitudinal plane of symmetry of aircraft. Stall fences begin at distance not exceeding 2 B and end at distance of 0.3-1.0 B from respective leading edge; their maximum height reaches 0.3 B, where B is aerodynamic chord of wing at area of mounting the stall hence.
EFFECT: facilitated going out of spin.
3 cl, 10 dwg
SUBSTANCE: invention relates to aircraft engineering. Device for adaptive control over aerodynamic characteristics of wing element 1 whereto small wing is attached to turn thereabout. Small wing 2 or its sections can turn about element 1 so that angle between rotational axis 7 and main direction of wing element panel 6 is other than 90°. Method and device is characterised by the use of above described device. Said device is proposed to be incorporated with aircraft.
EFFECT: reduced fuel consumption.
21 cl, 10 dwg
SUBSTANCE: invention relates to aircraft engineering. 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. 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. Angle between end plate and aerofoil makes 175-180 degrees. Wing tip is arranged at 2 to 3 degrees to wing tip chord.
EFFECT: higher aerodynamic efficiency, reduced fuel consumption.
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. Aerodynamic surface trailing edge is aligned with end plate rear edge. Tip is located at end plate front edge, below rear edge while sweep make 60-85 degrees. There is lower vertical aerodynamic surface of small elongation coupled with end plate so that its leading edge coincides with leading edge of end plate aerodynamic surface. Angle between end plate aerodynamic surface and lower vertical aerodynamic surface makes 125-30 degrees.
EFFECT: higher aerodynamic efficiency, decreased fuel consumption.
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