RU2362693C2 - Self-stabilising wing-in-ground effect craft - Google Patents

Abstract

FIELD: transportation.

SUBSTANCE: invention is related to aviation engineering and to creation of self-stabilising wing-in-ground effect crafts. Self-stabilising wing-in-ground effect craft comprises fuselage. In front part of fuselage there is horizontal empennage of rectangular shape in plan, and in stern part of fuselage - wing of small extension and two vertical empennages with steering wheels. At least two engines with propellers are installed in upper ends of vertical empennages so that the latter are in flow blown from propellers. Extension of horizontal empennage is identified from the following ratio:

where λ₁ is extension of the main wing - small extension wing; S₁ is area of horizontal empennage; S₂ is area of small extension wing.

EFFECT: makes it possible to increase course controllability also in wider zone of longitudinal stability, determined by geometric parameters

and λ₂=S₂/S₁·λ₁ and guaranteeing stability of wing-in-ground effect craft of "Duck" type at all distancing above the screen up to flight outsider of screen effect zone.

2 cl, 2 dwg

Description

The present invention relates to aircraft, in particular to ekranoplanes.

From aerodynamics it is known that the transition from one flight mode of an aircraft to another or in case of violation of the balancing conditions, for example, discharge of cargo, a sudden rush of air in the vertical direction, is carried out using additional forces and moments created by the controls. Therefore, controllability can be considered as the ability of an aircraft to transition from one mode of movement to another. This concept includes both the possibility of maneuver and the restoration of balancing if the balance of forces and moments of the ekranoplan is disturbed.

From the prior art, for example, Belavin N.I. WIG. P .: Shipbuilding, 1968, it is known that the stabilization problem (i.e., balancing and stability) of an aircraft near the screen is solved either by choosing the layout of the ekranoplan itself, or by using automatic control systems.

In US patent No. 4442986, CL. B64C 21/04, 244 / 12.1, publ. 04.17.84, an ekranoplane is presented, made according to the “airplane” scheme and having horizontal tail with a large relative area exceeding 0.35 of the wing area. The use of horizontal plumage with a large area leads to a decrease in the efficiency of using the screen effect, an increase in the mass of the ekranoplan and has a negative effect on the flight performance.

The ekranoplanes of the “airplane” scheme require the installation of automatic control systems on them, which is associated with significant energy consumption and an increase in the cost of the ekranoplan.

In US patent No. 5065833, CL. B60V 1/08, 180/117, publ. 11.19.91, an ekranoplane is presented containing a wing, a fuselage, a stabilizer, a power plant, including an engine and a gas propulsion device or an air screw, blowing the stabilizer and elevator. Having blown the horizontal tail with a gas jet from the propulsion device (propeller), in fact, slightly increases the stability of the winged craft at the screen, since the bevels of the flow induced by the attached wing vortex, the position of which largely depends on the height and angle of the pitch of the wing located in the area of effect of the screen effect. However, the installation of the propulsion unit at a constant angle to the horizontal tail limits the possibility of stabilization, since with a change in the true angle of attack of the wing, the true angle of attack of the horizontal tail section blown by the gas stream will remain almost constant, not providing the necessary change in the magnitude of the horizontal tail feathering. It is in order to reduce the adverse effects of the propulsion jet flowing around the horizontal tail on the stability of the ekranoplan in US Pat. No. 5,065,833, it is proposed to install horizontal tail feathering at a large angle to the axis of the propulsion jet.

Known patent of Russia No. 2097269, IPC B60V 1/08, priority 12/21/95, published 11/27/97, in which the ekranoplane that implements the stabilization method contains a wing, a stabilizer, an engine with a propulsion, as well as a gas generator and a shaper, a feature of this ekranoplan is the presence in it of the orientation system of the jet shaper at a constant angle to the horizon, made, for example, in the form of a tilt drive propulsion propulsion system.

The essence of this invention is as follows. Due to the fact that during the flight of an ekranoplane in the area of the effect of the screen effect, the pitch angle is limited, the horizontal tail will be practically the whole time in a stream oriented at a constant angle to the horizon, and will practically not be affected by the bevels of the flow from the attached vortex to the wing of the ekranoplan . As a result, with a change in the pitch angle of the winged wing and, consequently, the angle of attack of the wing, the true angle of attack of the stabilizer and horizontal tail will also change, which, according to the author, will ensure the creation of a stabilizing aerodynamic moment on the horizontal tail, which will provide stabilization, i.e. the stability of the ekranoplan in longitudinal motion during flight in the area of the effect of the screen effect.

With all the advantages of the known ekranoplan, its main drawback is the complexity of the orientation system of the jet shaper at a constant angle to the horizon.

It is known A.S. USSR No. 1316170 Self-stabilized ekranoplane of the "Utka" scheme, IPC B60V 1/08, priority July 17, 19.85 with a bar for official use. The signature stamp for official use was removed on the basis of the EC protocol of the faculty of vehicles of the Irkutsk Polytechnic Institute No. 37 dated 06/30/1998

The claims are published in the official bulletin of Rospatent.

According to the invention, the ekranoplan according to the "Duck" scheme contains a fuselage, horizontal and vertical plumage, a wing of small elongation, an engine with a propeller. According to the inventors, in order to improve the characteristics of the longitudinal stability of the ekranoplan by reducing the time of the oscillatory process when exposed to external disturbances, it is proposed that the horizontal tail be made in the form of two profiled bearing surfaces rigidly interconnected in series with the overlapping along the longitudinal axis of the ekranoplan, and the installation angle of the rear bearing surface make more than the installation angle of the front bearing surface with the rear edges of the bearing boiling surfaces in the same horizontal plane.

The disadvantages of this invention are an increase in the weight of the structure due to a decrease in the load-bearing properties of the horizontal plumage, an increase in its resistance, and, as a consequence, a decrease in the quality of the structure. In addition, the installation of a “slotted” horizontal tail can in no way affect the oscillation time of a perturbed transient ekranoplan process.

The closest solution in its technical essence and the achieved result to the proposed solution is the patent of Russia No. 2224671, IPC B60V 1/08, priority January 8, 2003, published February 27, 2004.

According to the invention, the ekranoplan according to the “Duck” scheme contains a fuselage with horizontal tail installed in the front part, and a small elongation wing and vertical tail with a rudder in the aft part of the fuselage, at least two engines with propulsion devices are mounted on a horizontal tail unit with rotation relative to the horizontal axis, the ratio of the area of horizontal tail to the wing area of small elongation is determined from the ratio:

, где

where

S ₂ - the area of horizontal plumage;

S ₁ - the wing area of small elongation,

and the ratio of the shoulder of the horizontal tail to the shoulder of the wing of small elongation is determined from the ratio:

где

Where

L ₂ - shoulder of the horizontal tail - this is the distance between the center of pressure of the horizontal tail and the center of mass of the winged craft;

L ₁ - shoulder of the wing of small elongation is the distance between the center of pressure of the wing of small elongation and the center of mass of the ekranoplan, and the zone of its longitudinal stability is determined from the lower limits of the ratio:

wherein the relative elongation of the horizontal tail is less than the relative elongation of the wing of small elongation.

связывает конструктивные параметры экраноплана схемы «Утка» и определяет границу зоны устойчивости данной компоновочной схемы.Ratio

connects the design parameters of the ekranoplane of the "Duck" scheme and determines the boundary of the stability zone of this layout scheme.

The objective of the invention is to expand the stability zones of the ekranoplanes of the "Duck" scheme, defined by the design parameters of the scheme and ensuring the stability of the ekranoplanes at all flight altitudes up to the flight far from the shielding surface, which allows the ekranoplanes of the "Duck" scheme to fly from one watershed to another or from one water area to another, which significantly expands their operational capabilities.

The technical result of the solution is to increase the flight safety of ekranoplanes of the “Duck” scheme by flying around possible obstacles from above by moving away from the screen with a further approach to the screen and further flight in screen mode.

The technical result is achieved by the fact that in a self-stabilizing ekranoplane of the "Duck" scheme containing the fuselage, in the front part of which there is a horizontal tail, the elongation of which is chosen so that its chord is the same as the chord of the main wing of small elongation installed in the rear of the fuselage , with two vertical tail units mounted on it with rudders and at least two engines with propulsors at the upper ends of vertical tail units, the ratio of the wing areas lies changes within

, где

where

S ₂ - the area of horizontal plumage;

S ₁ - the area of the main wing of small elongation,

and the ratio of the shoulder of the horizontal tail to the shoulder of the wing of small elongation varies within:

, где

where

L ₂ - shoulder of the horizontal tail - this is the distance between the center of pressure of the horizontal tail and the center of mass of the winged craft;

L ₁ - shoulder wing of small elongation is the distance between the center of pressure of the wing of small elongation and the center of mass of the winged craft,

moreover, the elongation of the horizontal tail is determined from the condition of equality of the chords of the wing of small elongation and horizontal tail and is equal to:

,

,

where λ ₁ is the elongation of the main wing - wings of small elongation, and the zone of longitudinal stability of the ekranoplan of the "Duck" scheme is bounded from above by the ratio:

.

.

делит область существования конструктивных параметров экраноплана схемы «Утка» на две части: над кривой - зона неустойчивых для экраноплана значений

и

и ниже кривой - зона устойчивых для экраноплана значений этих параметров.Ratio

divides the area of existence of design parameters of the ekranoplane of the “Duck” scheme into two parts: above the curve is the zone of values unstable for the ekranoplan

and

and below the curve there is a zone of values stable for the ekranoplan.

Comparison of the proposed technical solution with the prototype shows that it differs from it:

- installation of engines with propellers at the upper ends of the vertical tail;

;- the elongation of the horizontal tail is determined from the ratio

;

определяет зону устойчивых значений параметров экраноплана схемы «Утка»

и

, отличающейся от прототипа более широкой зоной значений этих параметров и гарантирующей устойчивость экраноплана схемы «Утка» на всех отстояниях над экраном вплоть до полета вне зоны влияния экрана.- polynomial

defines a zone of stable values of the parameters of the ekranoplan of the Duck scheme

and

, which differs from the prototype in a wider range of values of these parameters and guarantees the stability of the ekranoplan of the “Duck” scheme at all distances above the screen until the flight outside the zone of influence of the screen.

In the known technical solution there are no such signs, therefore, the proposed solution meets the criteria of the invention of "novelty."

To compare the proposals with other well-known solutions, a search was carried out in patent and scientific and technical literature.

During the search revealed:

- the installation of engines with propulsion devices in the bow of the ekranoplan is known (see Russian patent No. 2097269, class B60V 1/08) and on the horizontal tail (see Russian patent No. 2224671, class B60V 1/08), but their installation on ends of vertical plumage;

- of the same patents No. 2097269 and No. 2224671 it is fundamentally known to use the gas propulsion drive on an ekranoplane;

и

для устойчивого экраноплана схемы «Утка», но только для полета в экранном режиме.- from the patent of Russia No. 2224671 the definition of the zone of values of the parameters is known

and

for a stable ekranoplan of the Duck scheme, but only for flight in the on-screen mode.

, кроме того, использование экраноплана схемы «Утка» в устойчивой зоне значений параметров

и

, определенной полиномом, два последних признака обеспечивают экраноплану устойчивость в экранном режиме полета и при полете в безграничной жидкости.However, the prior art does not know the totality of essential features, namely: the ability to install engines with propulsors at the ends of the vertical tail, the chord of the horizontal tail and the main wing — the wings of small elongation are the same and the elongation of the horizontal tail is determined from

In addition, the use of the ekranoplane of the “Duck” scheme in a stable zone of parameter values

and

defined by the polynomial, the last two signs provide the ekranoplan stability in the on-screen flight mode and when flying in unlimited fluid.

Thus, a new set of previously known features and newly identified significant distinguishing features in the claimed technical solution allows to achieve the above task and technical result.

The invention is illustrated by drawings.

Figure 1 shows the ekranoplan, a side view, figure 2 is the same, a plan view, figure 3 is a graph of the stability zone of the ekranoplan.

The ekranoplan consists of a fuselage 1 with horizontal tail 2 and a wing of small elongation 3, two vertical tail 4 with rudders 5.

показан центр давления 6, а крыле малого удлинения 3 - центр давления 7, а на фюзеляже - центр масс экраноплана 8. На торцах вертикальных оперений 4 установлены двигатели 9 с движителями 10.On the horizontal plumage 2 extensions

the center of pressure 6 is shown, and the wing of small elongation 3 is the center of pressure 7, and on the fuselage is the center of mass of the ekranoplane 8. At the ends of the vertical tail 4 engines 9 are installed with propulsion 10.

The installation of engines 9 with propulsion 10 at the ends of the vertical tail provides airflow of vertical tail feathers with rudders by the air flow from the propulsors, which provides good directional stability and controllability of the ekranoplan at low speeds.

- кривая 13 на фиг.3 - связывает конструктивные параметры отношения площадей

и их «плечей»

относительно центра масс 8 таким образом, что экраноплан схемы «Утка» с конструктивными параметрами, лежащими на кривой и ниже нее, всегда устойчив на всех отстояниях и вдали от экрана, а при полете над экраном обладает свойством самостабилизации, обеспечиваемым изменением отстояния крыльев от экрана и изменением угла тангажа в зависимости от скорости полета. Кривая 12 на фиг.3 представляет результаты патента №2224671. Видно, что условие равенства хорд горизонтального оперения и крыла малого удлинения и определение из этого условия удлинения горизонтального оперения

расширяет область значений

и

, устойчивой для экранопланов схемы «Утка».Polynomial

- curve 13 in figure 3 - connects the structural parameters of the ratio of the areas

and their "shoulders"

relative to the center of mass 8 in such a way that the ekranoplan of the “Duck” scheme with design parameters lying on the curve and below it is always stable at all distances and far from the screen, and when flying above the screen it has the property of self-stabilization provided by the change in the distance of the wings from the screen and change in pitch angle depending on flight speed. Curve 12 in figure 3 represents the results of patent No. 2224671. It is seen that the condition for the equality of the chords of the horizontal plumage and the wing of small elongation and the determination from this condition of the elongation of the horizontal plumage

expands the range of values

and

, steady for ekranoplanes of the Duck scheme.

=1 диктуется самим определением схемы «Утка».The restriction of the stability zone (figure 3) left limit value

= 1 is dictated by the very definition of the Duck scheme.

<1 - схема «Утка».At value

<1 - “Duck” scheme.

=1 соответствует схеме «Тандем».Value

= 1 corresponds to the tandem scheme.

>1 - схема «Обратная Утка».Value

> 1 - “Reverse Duck” scheme.

Claims (2)

1. A self-stabilizing ekranoplane containing a fuselage, in the front part of which there is a horizontal tail in a rectangular shape, and in the aft part of the fuselage - a wing of small elongation and two vertical tail units with rudders, characterized in that at least two engines with propellers are mounted on the upper ends of the vertical plumage so that the latter are in a stream blown from the propulsors, and the elongation of the horizontal plumage is determined from the ratio

,
where λ ₁ - elongation of the main wing - wings of small elongation;
S ₂ - the area of horizontal plumage;
S ₁ - wing area of small elongation. 2. Self-stabilizing ekranoplan according to claim 1, characterized in that the ratio

- area S ₂ horizontal plumage to the area S _{1 of the} wing of small elongation is determined by the ratio

,
wherein

- the ratio of the distance L ₂ between the center of pressure of the horizontal tail and the center of mass of the winged wing to the distance L ₁ between the center of pressure of the wing of small elongation and the center of mass of the winged wing, and the range of values

, but

.

Images