RU2534480C1 - Method of increase of aircraft wing lift - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: method is based on airflow formation above the upper planes at the expense of using the upper planes of a louvers arranged so that the air cavities inside the wing are connected through the shutters (controlled synchronously with the louvers) with the suction cavities of jet turbine engines, which sucks airflow through the louvers, forming mobile air mass above the wings of non-moving aircraft. Rear wings are designed so that the air suction through the louvers is provided using the ejection method at the expense of suction action of exhaust gases through controlled shutters between air cavities of back wings and exhaust zone.

EFFECT: increase of aircraft wing lift.

2 dwg

Description

The invention relates to the field of aviation and, above all, to carrier-based aviation of the Navy.

From the moment of the creation of the first to the appearance of supersonic aircraft, little has changed in the principle of creating wing lift. The modern public Internet about this problem speaks the language of theories of the late nineteenth century.

It is known that the lifting force of an airplane wing is created under the influence of two factors: the first of them is the effect of a kite, when the lower plane of the wing of an airplane is set and held by the air rudders at a certain angle to the direction of movement, while the air flow flowing around the wing deviates down from horizontally, creating a vertical component of the triangle of forces emanating from the drag of the wing and, accordingly, the traction of the engines; the second factor is the effect of flow around the upper plane of the wing (due to its convexity) with a greater air velocity than the lower plane of the wing. In two high-speed flows, according to the laws of hydro- and aerodynamics, different static pressures are created. By the Bernoulli equation for horizontal flow, the equality

$$\frac{\rho {\mathrm{<figure-callout\; id="2"\; label="\nu "\; filenames="00000005.png"\; state="\{\{state\}\}">\nu </figure-callout>}}^2}{2}+P=const\left(\text{one}\right)$$

характеризует скоростной напор воздушного потока. «Физика» Б.В. Федосеев, стр.108, «Справочник по физике», Яворский и Детлаф, стр.323.where ρ is the air density in kg / m ³ , ν is the speed of air flow around the wing in m / s, and P is the static pressure inside the air stream. Component $$\frac{\rho {\nu }^{}}{}$$$$\frac{{}^2}{2}$$

characterizes the high-pressure air flow. “Physics” B.V. Fedoseev, p. 108, “Handbook of Physics,” Yavorsky and Detlaf, p. 323.

Due to the difference in the velocity of flow around the wing, due to the different curvature of the planes, the pressure inside the upper stream will be lower than in the lower one, and atmospheric pressure, again, will affect the wing from the bottom up, raising the plane. To enhance the factor of a kite during take-off, ailerons are installed on the wings, reinforcing the angle of attack of the wing. They are used when landing, dropping to the runway with a minimum speed.

The essence of the invention is as follows: the upper plane of the wing of the aircraft is made in the form of blinds with a controlled air flow passing through them and the internal cavity of the wing into the suction cavity of a turbojet engine. Between the internal wing cavity and the engine air intake, a controlled shutter synchronized with the blinds is installed, which smoothly covers the air flow from the air intake with the gradual opening of the blinds before the aircraft lands and in the reverse order perform these actions before take-off; similar wings proportional to part of its weight are installed in the rear part of the aircraft, and two turbojet engines are installed between the main and rear wings and below them on the sides of the aircraft so that, in the upper part of the exhaust nozzle, under the rear wings, controlled shutters between air cavities of the rear wings and exhaust nozzles, which when opening with their surfaces partially narrow the exhaust channels, increasing the speed of the exhaust gas flow in this section, and they create an ejector effect for sucking air through the rear louvres from the upper planes of the rear wings, while the ailerons are installed in the rear of the wings, and the keel and course rudder are installed on the rear of the aircraft.

Figures 1 and 2 show a top and side view of the proposed method of increasing the lift force of an airplane wing, where 1 is the fuselage of the airplane, 2 are the front and rear wings, 3 are the blinds, 4 are the ailerons, 5 and 6 are turbojet engines, 7 is the cabin pilots, 8 - air damper synchronized with the blinds, 9 - air intake, 10 - air cavity inside the wing, 11 - keel, 12-course steering wheel, 13 - damper between the exhaust nozzle and the air cavity in the rear wings, 14 - pilot light.

кг/м², отсюда составляющая Р статического давления в потоке снизится до 0,93 атм.The system works as follows: after the engines are started and ready to start, the shutter 8 is moved to the “closed” position, while the shutters are opened at the optimum angle synchronously with it, and along the still fixed wing, above its upper plane along the surface of the shutters and along the direction of the arrows a stream of air flowing around the upper plane of the wing. We calculate according to the Bernoulli equation the effectiveness of the forces inside the air stream. Let’s take the speed of air flow around the wing surface to be 360 km / h, which is 100 m / s. The air density is ρ = 1.29 kg / m ³ , then the first part of equation (1) will be equal to $$\frac{1.29\ast {\mathrm{one\; hundred}}^2}{2}\frac{\mathrm{<figure-callout\; id="2"\; label="N\; m"\; filenames="00000005.png"\; state="\{\{state\}\}">N\; </figure-callout>}}{m^{}}=645$$

kg / m ² , hence the component P of static pressure in the stream will decrease to 0.93 atm.

The speed of air flow through the blinds will depend on their design and the opening angle. Given the amount of air drawn through the TRD - a turbojet engine, it is easy to imagine that this speed can be easily achieved, and the lifting force, respectively, is provided at this level.

The proposed method of increasing the lifting force of an aircraft wing can significantly change the state of military aviation. In flight, the aircraft will be able, without changing its position to the horizon, to make sharp maneuvers upward, in an inverted position to perform horizontal jumps down, if not from a place, then quickly rise into the air after a short acceleration.

Claims (1)

A method of increasing the lift force of an aircraft wing, characterized in that the upper plane of the main wing of the aircraft is made in the form of louvers with a controlled air flow passing through them and the internal wing cavity into the suction cavity of a turbojet engine, and synchronized with the blinds is installed between the internal wing cavity and the engine air intake controlled flap, which smoothly opens the air flow from the wing cavity with the gradual opening of the blinds before landing and in the opposite order Audit these actions before take-off; in the rear part of the aircraft, rear wings are made proportional to the corresponding part of its weight, and between the main and rear wings and below them two turbojet engines are installed on the sides of the aircraft so that in the upper part of the exhaust nozzle, under the rear wings, controlled shutters between air cavities of the rear wings and exhaust nozzles, which, when opened by their surfaces, partially narrow the exhaust channels, increasing the rate of exhaust gas flow in this section c, and this creates an ejection effect for sucking air through the rear louvres from the upper plane of the rear wings, while ailerons are installed in the rear of the wings, and the keel and course rudder are installed on the rear of the aircraft.

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