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
The invention relates to the field of modeling aircraft, mainly civil aircraft and transport aircraft.
Known wing of the aircraft, containing the frame, casing, elements of the deflection of the air flow flowing upper and lower aerodynamic surfaces . During the flightaircraft due to the differential pressure under the wing and onthe wing of the air in the front part of the wing tends to move upwards.The formation of eddies, which are blown off the counter flowair. Sliding off the wing turbulence go backas long eddy cord".
The objective of the invention is to limit the formation ofat the end of the wing vortical cord".
Technical result : taskis achieved by the fact that the wing of the aircraft, containing the frame is,lining,the elements of the deflection of the air stream, flowing top andthe lower aerodynamic surface, equipped with a mesh plate,located at its end part along the bottom dragsurface. The mesh plate is made retractable from the slot in the front-end part. Mesh plate has a triangularthe shape and size of theholes, increasing as their removal is from the front-end part.
1 shows an aircraft with "eddycords" at the end of the wings; figure 2 shows netplate fixedly mounted on the end part of the wing; 3- view And at the end of figure 2; figure 4 shows the mesh plate, retractableof the slotted holes in the front part of the wing.
Attached to the fuselage 1 of the aircraft (figure 1) wing 2 has a frame 3, a casing 4, items 5 deflection of the air flow (ailerons, flaps, and other), going around the top 6 and bottom 7 of the aerodynamic surface. End part 8 of the wing (figure 2 and 3) is provided with a rigid mesh plate 9, still located along the lower aerodynamic surface. Mesh plate made of light-resistantatmospheric corrosion material, has a triangular shape with rounded corners, smooth surfaces and the size of the holes 10, increasing as it is removed from the end part of the wing. The holes in the mesh plate can be round, square, oval or other. The edges of the holes from the lower aerodynamic surface rounded. Mesh plate can be made retractable from slot 11 front part of the wing (figure 4).
In flight conditions of the aircraft have attached to the fuselage 1 wing 2 having Karkas, the casing 4, items 5 deflection of the air stream, flowing top 6 and bottom 7 of the aerodynamic surface, the air flows occurring at the end of part 8, strive to go from the bottom up, however, dissipate mesh plate 9 in small streams, passing through numerous holes 10. This formed the "vortex cord partially eroded, it becomes unstable and disintegrates quickly. In bad conditions, mesh plate (with holes of the same or different size) retracts into the front-end part of the wing through the slot 11, for example, to protect against sediment snow and ice formation. In the implementation of preventive or repair work mesh plate handle washer fluid.
The source of information
1. Polytechnical dictionary. CH. edit ISI. - M.: Soviet encyclopedia, 1976. - S.
1. The wing of the aircraft, containing the frame, casing, elements of the deflection of the air flow flowing upper and lower aerodynamic surfaces, characterized in that the supplied mesh plate, located at its end part along the lower aerodynamic surface.
2. Wing aircraft according to claim 1, characterized in that the mesh plate is made retractable from the slot in the front-end part.
3. The wing of the aircraft so the TA according to claim 1, characterized in that the mesh plate has a triangular shape and the size of the holes, increasing as it is removed from the end part.
SUBSTANCE: aircraft comprises fuselage, takeoff-landing wings, horizontal empennage, nose horizontal fins, tail vertical fins and engines. Takeoff-landing wings are jointed to fuselage by suspension assemblies with axles of one degree of freedom arranged above fuselage centerline, along fuselage lengthwise mirror axis. Takeoff-landing wings in retracted position are located under suspension assemblies, along fuselage lengthwise mirror axis, while outer surface of said wings makes an extension of fuselage outer surface. Takeoff-landing wings in retracted position cover, at least, 30% of fuselage surface area between nose horizontal fins and empennage.
EFFECT: higher safety in operation.
5 cl, 5 dwg
SUBSTANCE: invention relates to aircraft engineering, particularly, to aircraft hardware intended for improving landing capabilities. Aircraft wing consists of outer wings. Note here that outer wings or their part turn about axis located in plan between perpendicular to aircraft axis and outer wing axis. Outer wing may turn relative to line making in plan with aircraft lengthwise axis the angle exceeding its sweep angle.
EFFECT: short landing run, efficient braking by wheels.
4 cl, 2 dwg
FIELD: aircraft engineering.
SUBSTANCE: aircraft comprises fuselage, nose horizontal empennage, tail horizontal empennage and takeoff-landing wings suspended to fuselage by suspension units with their axes located above fuselage centerline along its lengthwise axis of symmetry to turn said takeoff-landing wings. Retracted takeoff-landing wings are located under suspension units along fuselage lengthwise axis of symmetry. Outer surface of said wings makes extension of fuselage outer surface. Said wings in retracted position cover, at least, 30% of fuselage surface located between nose and tail horizontal empennages.
EFFECT: lower drag.
7 cl, 21 dwg
SUBSTANCE: invention relates to aircraft modelling. Aircraft comprises engine, fuselage made up of skin, tail assembly and alighting gear. Wing is mounted above fuselage. Wing holder with hinge is attached to fuselage for wing to swing relative the latter about lengthwise horizontal axis extending along wing bottom face across its centre of gravity. Wing swing drive is arranged in and/or on fuselage. Recess is made at wing centre on tail assembly side. Wing swing drive is arranged outside and on the side of fuselage.
EFFECT: improved maneuverability, shorter takeoff and landing distance.
10 cl, 9 dwg
SUBSTANCE: invention relates to aircraft engineering. Proposed aircraft consists of airframe two parts separated in horizontal plane and engines. Air frame parts may be separated in vertical plane to make tandem biplane. Engines are secured to air frame top section so that engine gas jet is directed tangentially to vortex flow from aircraft air frame created at its edges.
EFFECT: improved aerodynamics.
SUBSTANCE: invention relates to aircraft engineering. Proposed aircraft comprises the main convertible wing with three planes. Wing central plane is rigidly jointed to fuselage. Wing top and bottom planes are interconnected by H-like hard rods. One pair of ends of every H-like rod is articulated with top plate while opposite pair is articulated with bottom plane. With rods turning about axis of rotation, aircraft is converted from monoplane into triplane. Wing transmission drive may be made up of undercarriage extension/retraction system.
EFFECT: simplified conversion.
9 cl, 15 dwg
SUBSTANCE: invention relates to aircrafts and concerns aerodynamic configuration of unmanned aitcrafts. Modular unmanned aircraft contains body 1 of elongated form with carrying beam 2 positioned along the body 1. Suspension assemblies 3,4 are set on carrying beam 2 where rear suspension assembly 4 is combined with swivel block 6 of wing 7 of the aircraft. Semispan of the wing 7 is less than or equal to the distance between suspension assemblies 3, 4.
EFFECT: increase in reliability of start and deployment of modular unmanned aircraft wing, increase in efficiency of armament section due to better control of its opening.
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. Proposed aircraft comprises airframe and wings that can be arranged in first and second positions. Crest is attached to airframe. Wings represent ellipsoidal hollow tubes hinged to said crest on both sides along the airframe.
EFFECT: increased flight range.
SUBSTANCE: invention relates to model airplane flying, particularly to aircraft with moving wings. Proposed aircraft comprises fuselage with crew cab, passenger and/or freight compartment, landing gear, moving wings mounted on both sides of fuselage and engines. Wing wider parts end face incorporates flat/convex disk rigidly fixed therewith and arranged to turn completely/incompletely.
EFFECT: higher maneuverability of aircraft.
4 cl, 7 dwg
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
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
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
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
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
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
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
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
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
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
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