Self-stabilizing wig

 

The invention relates to aircraft and is about creating self-stabilizing wig. Self-stabilizing wig is made on a "Duck" and has the fuselage. In the front part of the fuselage installed horizontal stabilizer rectangular shape in plan. The aft portion of the fuselage are a wing of small aspect ratio and vertical tail with rudder and engine with the propeller. At least two motors with propellers mounted on the horizontal tail can be rotated about the horizontal axis. The ratio of the area of the horizontal tail to the square of the wing of small aspect ratio determined from the relationwhere S2- the area of the horizontal tail; S1- the area of a wing of small aspect ratio, and the ratio of shoulder horizontal tail to shoulder wing of small aspect ratio determined from the relationwhere L2- shoulder horizontal tail is the distance between the center of pressure horizontal tail and the center of mass GeV; L1the shoulder wing of small aspect ratio is the distance between the center of pressure of the wing of small aspect ratio and center of mass GeV, and tehnicheski a result of implementation of the invention is to improve the safe operation of the wig by providing its longitudinal stability. 1 C.p. f-crystals, 3 ill.

The invention relates to an aircraft, in particular to sometimesiwonder the wig.

From aerodynamics it is known that the transition from one mode of throwing machine to another, as well as the restoration balancing are additional forces and moments generated by the controls. In accordance with this, the controllability can be considered as an impact tool to transition from one flight mode to another. This concept includes the ability to maneuver longitudinal balancing GeV and restore the disturbed equilibrium of the longitudinal forces and moments.

In the prior art, for example, Belavin N. And. The wig. Leningrad: Sudostroenie, 1968, it is known that the problem of stabilization (i.e., sustainability) of the aircraft near the screen is solved either by selecting the layout, or by using automatic control systems.

In U.S. patent 4442986, CL 64 With 21/04, 244/12.1, publ. 17.04.84 presented wig, made by aircraft circuit and having a horizontal stabilizer with a large relative surface area. The use of horizontal tail with large relative size, prodit to reduce the efficiency of the use of the display effect, increase the weight of the structure and the moment of inertia of wig that has a negative impact on the flight characteristics and controllability GeV. The use of automatic control systems for such vehicles is associated with significant inputs required for practically continuous deflection surfaces, providing damping GeV, for example, the deviation of the elevators. In addition, the introduction of automatic control systems leads to a significant rise in the cost of the wig.

In U.S. patent 5065833, class B 60 V 1/08, 180/117, publ. 19.11.91, presents the water-containing wing, fuselage, stabilizer, power unit, including the engine and gas thruster or propeller, blowing the stabilizer and rudder. Airflow horizontal tail gas stream from the propeller (propeller) really increases the resistance of the wig at the screen, because across the border streams do not pass the bevels flow induced attached vortex wing, the position of which largely depends on the height and pitch angle of the wing in the area of the display effect. However, the installation of the thruster under patinnova the angle of attack of the true angle of attack of the horizontal tail, blown by a jet of gas, will remain almost constant, not providing the necessary change in the value of the lifting force of the horizontal tail. This is to reduce the adverse impact of the jet propulsion flow over the horizontal stabilizer, on the stability of wig in U.S. patent 5065833 prompted to install the horizontal stabilizer at a large angle to the axis of the jet propulsion.

Known patent of Russia 2097269, IPC B 60 V 1/08, priority 21.12.95 published 27.11.97, in which the ekranoplan, which implements the method of stabilization, contains the wing, stabilizer, and engine with the propeller and the generator and shaper jet, this wig is the orientation of the driver of the jet at a constant angle to the horizon, made for example in the form of a tilt actuator thruster propulsion.

The essence of this invention is as follows: due to the fact that when flying in ground effect vehicle in the area of the display effect of the change of pitch angles is limited, the horizontal stabilizer will almost always be in a jet oriented at a constant angle to the horizon, and there will be little affected chamfered is therefore the angle of attack will change and the true angle of attack of the horizontal stabilizer and tail that, in the author's opinion, will provide a horizontal tail aerodynamic stabilizing moment that will provide stabilization i.e. the stability of wig in a longitudinal movement when flying in the area of the screen effect.

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

The closest solution to its technical essence and the achieved result for the proposed solution is and.with. The USSR 1316170 Semistability the ekranoplane the Canard configuration, IPC B 60 V 1/08, priority 17.07.85 stamped for official use. The stamp for official use only cleared on the basis of the Protocol EC Department vehicles Irkutsk Polytechnic Institute 37 from 30.06.98,

The claims published in the official Gazette of Rospatent.

According to the invention, the GeV on a "Duck" contains the fuselage, horizontal and vertical tail, wing of small aspect ratio, the engine with the propeller. According to the authors of the invention, for improvement of characteristicsa perturbations proposed horizontal stabilizer to perform in the form of two rigidly interconnected consecutive overlapping along the longitudinal axis of the wig-bearing profiled surfaces, and the installation angle of the rear bearing surface to perform more of the installation angle of the front bearing surface, at the location of the rear edges of the bearing surfaces in the same horizontal plane.

The disadvantages of the known wig should include the following: - installation of double horizontal tail in the fore part of the wig will lead to an increase in weight, decrease the lifting force horizontal tail and increase the resistance.

- reducing the lifting force and the increase of the resistance of the horizontal tail will reduce the quality of the wig.

- dual "slotted" horizontal tail in the opinion of the authors leads to a reduction of the time-oscillatory process, which in our opinion is problematic.

Object of the present invention is to improve the safe operation of the wig by providing its longitudinal stability.

The technical result is to increase the aerodynamic quality and sustainability of the wig on a "Duck".

The technical result is achieved by the fact that the self-stabilizing water on a "Duck", containing the fuselage in front of the what about the small aspect ratio and vertical tail with rudder, at least two motors with propellers mounted on the horizontal tail can be rotated about the horizontal axis, while the ratio of the area of the horizontal tail to the square of the wing of small aspect ratio determined from the relationwhere S2- the area of the horizontal tail; S1- the area of a wing of small aspect ratio, and the ratio of shoulder horizontal tail to shoulder wing of small aspect ratio determined from the relationwhere L2- shoulder horizontal tail is the distance between the center of pressure horizontal tail and the center of mass GeV; L1the shoulder wing of small aspect ratio is the distance between the center of pressure of the wing of small aspect ratio and center of mass GeV, and the area of its longitudinal stability is determined from the lower limit values of the ratio
the relative lengthening of the horizontal tail is less than the relative elongation of the wing of small aspect ratio.

Ratiosbinds the design parameters of the GeV of the Canard configuration and defines the boundary of the zone of stability of this layout schemes.

what stop engines with propellers in a horizontal plumage;
- motors with propellers mounted to rotate about a horizontal axis;
the ratio of the area of the horizontal tail to the square of the wing of small aspect ratio in the ratio of 0.2-1;
- the ratio of shoulder horizontal tail to shoulder small elongation ratio of 0.59-4,5;
- use the wig in the area of its longitudinal stability, a certain polynomial stability thresholds;
In the known technical solution of such signs is not, therefore, the proposed solution meets the criteria of the invention of "novelty."

For comparison of proposals with other known solutions conducted a search of the patent and scientific literature.

In the search process identified:
well - known installation of engines with propellers in the fore part of the GeV (see the patent of Russia 2097269, class B 60 V 1/08), but not known to install them on the horizontal tail in the wig type "Duck";
- from the same patent of Russia 2097269 fundamentally known to use water-drive rotation of the gas engines.

However, the prior art does not know the set of essential features, namely: the ratio of the area of the horizontal tail to the square of the wing of small aspect ratio with Saotome, use the wig in the area of its longitudinal stability defined by the polynomial bounds of sustainability.

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

The invention is illustrated by figures.

In Fig.1 shows the ekranoplan, side view, Fig.2 is a view in plan of Fig.3 is a graph of the zone of stability of wig.

The ekranoplan consists of a fuselage 1 with horizontal tail surfaces 2 and wings of small aspect ratio 3, the vertical fin 4 rudder 5.

On the horizontal tail 2 shows the Central pressure 6, on the wings of small aspect ratio 3 - the center of pressure is 7, and on the fuselage center of mass of the 8 GeV. In the front part of the fuselage 1, the horizontal plumage 2 engines are installed 9 thrusters 10 can be rotated.

Wing of small aspect ratio is equipped with flaps 11. Turning motors 9 thrusters 10 about a horizontal axis to direct the gas flow under the wing of small aspect ratio 3 (main wing GeV). This creates a static air cushion on the wing 3, similar to the static ones is ol, open front for receiving the gas flow from the thruster 10. Generated air cushion relieves the ekranoplan and facilitates its release in cruise flight mode.

Polynomialbinds the design parameters of the square horizontal tail 2 and the wing of small aspect ratio 3 and their "shoulders" L1and L2about the center of mass 8 so that the ekranoplane of Canard configuration with the design parameters of this curve and below it (i.e., if they lie in the zone of stability) is always stable when exposed to external disturbances. In addition, the ekranoplan scheme "Duck" semistability in flight speed range of the speed of separation to maximum speed by changing otstoyniy wings from the screen and change the angle of the tangent depending on speed. The limit of the zone of stability (Fig.3) the left limitdictated by the schema definition "Duck".

When the value ofdiagram "Duck".

diagram of the "Tandem" (equal to the area of the wing of small aspect ratio and horizontal tail).

When the value ofdiagram "Duck Back".

M what about the perfection of the apparatus and its quality.

Currently, the ekranoplan on a "Duck" is undergoing pilot testing.


Claims

1. Self-stabilizing wig on a "Duck", containing the fuselage, in front of which has a rectangular shape in plan horizontal tail and aft fuselage - wing of small aspect ratio and vertical tail with rudder, motor mover, characterized in that at least two engines with propellers mounted on the horizontal tail can be rotated about the horizontal axis, while the ratio of the area of the horizontal tail to the square of the wing of small aspect ratio determined from the relation

where S2- the area of the horizontal tail;

S1- the area of a wing of small aspect ratio,

and shoulder horizontal tail to shoulder wing of small aspect ratio determined from the relation

where L2- shoulder horizontal tail is the distance between the center of pressure horizontal tail and the center of mass GeV;

L1the shoulder wing of small aspect ratio is the distance between the price titsa lower limits of ratios

2. Self-stabilizing ekranoplan under item 1, characterized in that the relative lengthening of the horizontal tail is less than the relative elongation of the wing of small aspect ratio.

 

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