RU2539440C1 - Aircraft wing - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: aircraft wing comprises carcass secured to fuselage, top and bottom airfoils with air inlets to inner spaces, jet engines communicated with the latter and airflow deflectors. Said top and bottom flat airfoils converge at acute angle on oncoming flow side while engine jet nozzles are arranged in line to make a slot. Top airfoil is located horizontally while bottom airfoil is inclined. Openings in airfoil walls feature equal size from the side of said top and bottom airfoils.

EFFECT: decreased drag, higher lift.

3 cl, 5 dwg

Description

The invention relates to the field of modeling high-speed, including supersonic, manned and unmanned aerial vehicles for civil purposes with a direct and triangular-shaped wing.

Known wing of the aircraft, containing a frame attached to the fuselage, upper and lower aerodynamic surfaces bounded by the walls of the cavity, located between the upper and lower aerodynamic surfaces, elements of the deflection of air flows, jet engines [1]. To reduce aerodynamic drag to the incoming air flow, the upper and lower aerodynamic surfaces can be made converging at an acute angle.

The objective of the invention is to reduce the aerodynamic drag of the wing, increase its lift.

The technical result of the solution of the problem is achieved by the fact that in the wing of the aircraft containing the frame attached to the fuselage, the upper and lower aerodynamic surfaces converging at an acute angle from the side of the incoming air flow, bounded by the walls of the cavity located between the upper and lower aerodynamic surfaces, deflection elements air flows, jet engines, jet engines are installed between the upper and lower aerodynamic surfaces, and their suction e nozzles communicate with cavities having openings for air inlet in the walls, and jet nozzles are located on the side of the air flows flowing from the upper and lower aerodynamic surfaces. The total area of the holes in the walls of the cavities is greater than the total area of the suction nozzles. The holes in the walls are made from the upper aerodynamic surface. The holes in the walls are made both from the upper aerodynamic surface and from the lower aerodynamic surface, and the total area of the holes from the upper aerodynamic surface is greater than the total area of the holes from the lower aerodynamic surface. The jet nozzle has an oval / rectangle shape. Jet nozzles are located “in line” with the formation of a gap.

Figure 1 shows an aircraft with a direct wing having openings on the side of the upper aerodynamic surface; figure 2 shows a section of figure 1 by the plane R; figure 3 shows the possible shape of the holes in the wall of the cavity; figure 4 shows the possible shape of the jet nozzles embedded in the wing of the jet engines; figure 5 shows a fragment of the wing, a view along a in figure 1.

The wing 1 of the aircraft (aircraft, Fig. 1) contains a frame 3 with a skin attached to the fuselage 2, upper 4 and lower 5 aerodynamic surfaces, elements 6 deviation of air flows (flaps, ailerons and more). The upper and lower aerodynamic surfaces are made as flat as possible, converging at an acute angle α = 2-4 ° from the side of the incoming air flow (figure 2). Between the horizontal upper and inclined lower aerodynamic surfaces are cavities 7, bounded by walls 8 above and below, and jet engines 9. Jet engines are built into the wing on both sides of the fuselage. The number of jet engines located on one side of the fuselage is one or more, for example three. The walls of the cavities are made breathable with holes 10 for the passage of air. The holes in the wall (Fig. 3) may have the shape of a circle (a), an ellipse (b); oval (c); square (d) or other, for example the shape of the holes in the grater. The holes in the walls are made from the upper aerodynamic surface. An embodiment is possible in the walls of the holes of the same or different size both from the upper aerodynamic surface and from the lower aerodynamic surface, and the total area of the holes from the upper aerodynamic surface is larger than the total area of the holes from the lower aerodynamic surface. The suction nozzles 11 of the jet engines communicate with the cavities, and the total area of the holes in the walls is greater than the total area of the suction holes of the nozzles. Jet nozzle 12 (figure 4) at the outlet of the gas stream may be in the form of an oval (e), a rectangle (f), or another. Jet nozzles of jet engines can be installed along the length of the wing at a distance from one another or are located "in line" with the formation of a gap 13 (figure 5).

In addition to low aerodynamic drag, such a wing has additional lifting force generated due to 100% air intake from the upper aerodynamic surface or predominant, for example, 80% air intake from the upper aerodynamic surface and 20% air intake from the side lower aerodynamic surface.

A model (experimental sample) of an aircraft (Fig. 1) is made of titanium and aluminum alloys with straight wings 1 attached to the fuselage 2, made in the form of a rigid frame 3 with skin, containing upper 4 and lower 5 aerodynamic surfaces with cavities 7 between them, airflow deflection elements 6. To reduce aerodynamic drag, the horizontal upper and inclined lower aerodynamic surfaces of the wings are converging at an acute angle α = 4 ° (FIG. 2). In the walls 8 bounding the cavities, openings 10 are made from above or from above and from below (FIG. 3, a, b, c, d), for example, openings in the form of a circle with a diameter of 50 mm with rounded edges. Jet engines 9, for example, in the amount of three units, are installed in each wing between the upper and lower aerodynamic surfaces, so that their suction nozzles 11 communicate with the cavities, and the jet nozzles 12 (Fig. 4, e, f) communicate with the atmosphere. To obtain the effect of a “flat” gas jet emanating from the jet nozzles, the nozzles are placed “in line” with the formation of a gap 13 (Fig. 5). To change the speed mode in flight conditions, jet engines can be turned on or off in pairs. When the aircraft is parked in the open air at the aerodrome, the holes in the wall from the upper aerodynamic surface are closed, for example, with a tarp, to prevent atmospheric precipitation from entering the wing cavity.

An equivalent technical solution is the implementation of an aircraft with a wing of a triangular shape.

The invention reduces the aerodynamic drag of an aircraft wing, increases its lift.

Information sources

1. Polytechnical dictionary. Ch. ed. I.I. Artobolevsky - M .: Soviet Encyclopedia, 1976. - P.435 (Civil Aircraft).

Claims (3)

1. The wing of the aircraft, containing the frame attached to the fuselage, upper and lower aerodynamic surfaces having openings in the walls for air to enter the cavities bounded by the walls, jet engines in communication with the cavities, airflow deflection elements, characterized in that the upper and lower aerodynamic surfaces made flat, converging at an acute angle from the side of the incoming air flow, and the jet nozzles of the engines are arranged in line with the formation of a gap. 2. The wing of the aircraft according to claim 1, characterized in that the upper aerodynamic surface is horizontal and the lower aerodynamic surface is oblique. 3. The wing of the aircraft according to claim 1, characterized in that the holes in the walls have different sizes from the upper and lower aerodynamic surfaces.

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