RU2436709C2 - Aircraft wing - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering. Aircraft wing has front edge, curvature of flat surfaces, rear edge and flaps. Said wing is divided longitudinally into top and bottom sections joined by webs to form inner space. Through slot is made along wing front section to direct airflow long wing high-pressure zone top inner space via rear edge. Inlet slot is arranged at an angle to top wall so that airflow follow through spaces along top wall, forced thereto by centrifugal force, to shut it off by movable flap. Rear edge has outlet slot with flaps to shut it off. Winglets are arranged along sidewalls to prevent overflow of air from top wall to bottom wall along sidewalls. Top edge of said winglets is located level with bottom boundary of airflow in said space.

EFFECT: reduced sizes higher lift.

3 dwg

Description

Application area

The invention relates to the field of aircraft and can be used in aircraft (LA) such as aircraft and helicopters to reduce the size of the wing and increase the lifting force of the wing.

State of the art

In the prior art, a wing is known (RU 95110187), consisting of spars, ribs, sheathing, mechanization means, characterized in that it is split, consisting of two main parts: an upper fixed part having a convex-concave profile, a lower part having a biconvex profile, the upper part of which enters the concave cavity of the upper part of the wing; both parts of the wing are interconnected pivotally by trapezoid with ball joints, ensuring the release of the lower part of the wing down and to the side of the aircraft axis by the length of the trapezoid.

The closest solution is an airplane wing (RU 97106853), or an aggregate blade having a leading edge, curvature of flat surfaces, a trailing edge and mounted on power elements of the suspension to the body of an aircraft or other machine, characterized in that they leave along the leading edge of the wing or blade a through slit, the cavity of which is brought along the wing plane and brought into the high-pressure region, i.e. under the wing or at the propeller blade — backward in the direction of the air or water being thrown off by the screw when the screw rotates, thus the wing is divided longitudinally into two wings - the front lower and rear upper, the main ones, which are fastened with jumpers, the “sharpening” angle of the front edges of both wing parts is made sharp, the front sub-wing is suspended on hinges and rotated, changing the angle of attack of the front sub-wing relative to the angle of attack of the rear sub-wing by the drive. A disadvantage of the known solutions is that the air flow will be inhibited due to friction against the side walls of the wing and flow along them into the rarefaction region, which negates all the advantages of bringing the high pressure region under the wing.

In addition, when typing high-speed aircraft, the lifting force created by the cavity may become superfluous and slow down its flight.

Effect: provides an increase in take-off weight with a constant drag or a decrease in wing size with a constant take-off weight; eliminates the influence of the internal cavity at high speeds of the aircraft; wing braking capabilities are enhanced during flight and landing.

The implementation of the invention

The claimed technical result is achieved due to the fact that the wing of the aircraft, having a leading edge, curvature of flat surfaces, a trailing edge, flaps, is divided longitudinally into two parts - the lower and upper, which are fastened with jumpers, and form a cavity inside, and along the front edge of the wing a through slit is made with a function of the direction of flow along the upper inner cavity of the wing of the high-pressure region through the trailing edge, characterized in that the entrance slit is located at an angle to the upper wall so that the air flow passes the cavity along the upper wall, pressing against it under the action of centrifugal force, with the possibility of overlapping it with a movable flap, and at the trailing edge there is an exit slit with flaps that can overlap the exit slit, and winglets are installed along the side walls, by the function which is to prevent air from flowing from the upper wall to the lower along the side walls, and the upper edge of the winglets is located approximately at the level of the lower boundary of the air flow passing through the cavity.

Brief Description of the Drawings

Figure 1 shows the structural device of the wing, a side view in section (a is a view of the wing with an open slit; b is a view of the wing with a closed slit), where 1 is the lower part of the wing, 2 is the upper part of the wing, 3 is the internal cavity of the wing, 4 - entrance slit, 5 - flaps, 6 - exit slit, 7 - streamlined air damper, 8 - air flow directions. Figure 2 shows the constructive location of the winglet in the wing, side view (a - with the wing flaps raised, b - with the wings down), where 9 are winglets, 10 is the aircraft fuselage.

Figure 3 shows the constructive location of the winglet in the wing (a is a top view in section, b is an end view in section), where 11 are partitions forming independent internal cavities inside the wing.

The implementation of the invention

Inside the wing (see Figure 1) between the upper (2) and lower (1) its planes form a cavity (3). Part of the oncoming air flow (8) flows around the wing along the outer planes (1, 2), creating a lifting force, like a conventional wing. The other part, contracting in the entrance slit, and then expanding, passes through the internal cavity (3). The entrance slit (4) is located at a certain angle to the upper plane (2) of the wing. Therefore, the flow passes through the cavity along the upper plane (2), clinging to it under the action of centrifugal force and creating some pressure on the upper plane. Tearing off the lower plane of the entrance slit, the flow passes through part of the cavity without touching the lower plane (1). Also, the flow, due to the ejection effect, sucks air from the lower plane, creating a vacuum there. As a result, additional lifting force appears. Thus, one wing works like two wings, without increasing drag (see Figure 1 (a), Figure 2 (a, b)). This allows you to increase the take-off weight of the aircraft or reduce the size of the wing. The air flow will be inhibited due to friction against the side walls and along them enter the rarefaction region, reducing it. To eliminate this effect, winglets (9) are installed at the side walls (see Figure 2). The upper edge of the winglets is at the level of the lower boundary of the stream. The air flowing along the side walls rises to the upper edge of the winglets, from where it is carried away by the stream.

A wing with one cavity (3) and two winglets (9) can be used in ultralight aircraft with a small wingspan. For larger aircraft in the wing, you can place several cavities (3) (see Figure 3), identical to one cavity. These cavities due to the additional lifting force will reduce the take-off and landing speed of the aircraft. Cavities (3) are separated from each other by partitions (11), which are the part connecting the upper and lower parts of the wing.

At high speeds, the lifting force created by the cavity may become superfluous. The lift generated by the outer planes will be enough. Therefore, when flying high-speed aircraft, the flaps (5) are closed, closing the exit slit (6), and the entrance slit is closed by a movable flap (7). As a result, an ordinary wing is formed directly in flight (see Fig. 1 (b)).

The lowering force and the lifting force of the wing are formed in the usual way: by lowering (see Figure 2 (b)) and raising the flaps (5) (see Figure 2 (b)), respectively. The braking effect, in contrast to the traditional principle, which can only be used when landing an aircraft, for example an airplane, by lowering the flaps and forming a reverse, in the claimed device, braking can be achieved by spreading the flaps (5) in different directions to the maximum angle. There is a parachute effect, which can be used during the flight, if necessary, to drastically reduce the speed of the aircraft, which allows you to strengthen the braking capabilities of the wing, not only during landing, but also during the flight.

Claims (1)

The wing of the aircraft having a leading edge, curvature of flat surfaces, a trailing edge, flaps, and the wing is divided longitudinally into two parts - the lower and upper, which are fastened with jumpers, and form a cavity inside, and a through slit is made along the wing leading edge with a function of the direction of flow along the upper inner cavity of the wing of the high-pressure region through the trailing edge, characterized in that the inlet slit is located at some angle to the upper wall so that the air flow passes the cavity along the upper walls of it, clinging to it under the action of centrifugal force, with the possibility of overlapping it with a movable flap, and at the trailing edge there is an exit slit with flaps that can overlap the exit slit, and winglets are installed along the side walls, the function of which is to prevent air from flowing from the upper wall to lower along the side walls, and the upper edge of the winglets is located approximately at the level of the lower boundary of the air flow passing through the cavity.

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