System of winglets and method of improving the flying-technical characteristics of an aircraft plane

FIELD: aviation.

SUBSTANCE: winglet system for a wing contains an upper winglet and a lower winglet mounted on the wing tip. The lower winglet has a static position when the wing is subject to static loading when parking on the ground. The lower end flap is designed so that the wing deflection upward with a flight load of approximately 1g causes the lower winglet to move from the static position to the flight position, resulting in a relative increase in the span of the wing. The aircraft contains a system of winglets that are located at the intersection of the gate gap and the lumen line at pitch and roll. Method of the aircraft operation is characterized by the movement of the winglets.

EFFECT: reduction of inductive drag of the wing.

20 cl, 15 dwg

 



 

Same patents:

FIELD: transport.

SUBSTANCE: invention relates to superhigh-speed aircraft , as well as to method of air movement using superhigh-speed aircraft. Aircraft moves by means of engine system consisting of turbojet engines (TB1, TB2), aero-thermo-dynamic ducts (ST1, ST2) and rocket engine which can be streamlined by closing to lower frontal resistance during cruising. The aircraft has triangle gothic wing (A) equipped with moving small wings (a1, a2) on outer ends of triangle wing (A) rear edge.

EFFECT: lower noise.

21 cl, 21 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

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

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 // 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

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

Aircraft wing tip // 2481242

FIELD: transport.

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.

3 dwg

Aircraft wing tip // 2481241

FIELD: transport.

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.

4 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.

15 dwg

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.

3 dwg

Aircraft // 2283261

FIELD: aviation.

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.

3 dwg

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

FIELD: transport.

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

Aircraft wing tip // 2481241

FIELD: transport.

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.

4 dwg

Aircraft wing tip // 2481242

FIELD: transport.

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.

3 dwg

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

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 // 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

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