RU2725036C1 - Air combat model - Google Patents

Abstract

FIELD: aircraft model.SUBSTANCE: invention relates to aircraft models and, in particular, to air combat models. Aerial combat model is made according to aerodynamic scheme of "tailless". It comprises wing (1) (fig. 1) of symmetrical profile. Wing (1) of model is equipped with slat (3), which is arranged in front of wing (1) and has symmetrical profile. When maneuvering in poorly maneuvering, slat (3) operates in feather mode. When performing high maneuverability, slat (3) is fixed by thrust (5) of normal flight or thrust (6) of inverted flight. Model becomes statically unstable along the longitudinal channel, as a result, its evolution rate considerably increases.EFFECT: invention is aimed at improvement of operational properties of air combat model.1 cl, 1 dwg

Description

The invention relates to aircraft models and, in particular, to models of air combat, both to cordovye and with remote control.

State of the art

There is a known model of air combat, made according to the "tailless" scheme in the version with cord control (see Model of air combat F2D http://www.parkflyer.ru/ru/blogs/view_entry/8337/).

The closest analogue is the model of air combat, made according to the “duck” scheme, its front horizontal tail unit operates in a vane mode at small and medium angles of attack and is fixed by a cord control system at large angles of attack (see RF patent No. 2702279). Such a model provides its very high maneuverability.

The disadvantage of the described model is that air combat models in most cases are carried out according to the “tailless” and, more rarely, “normal” aerodynamic scheme, on which the manufacturing technology of the above model is not applicable.

Due to this, modern models of air combat have insufficiently high maneuverability and therefore are characterized by insufficiently high operational properties.

The technical problem solved by the present invention is to improve the operational properties of air combat models.

SUMMARY OF THE INVENTION

The problem is solved due to the fact that in the model of air combat, containing the wing, propeller installation and elevator associated with the control system, the wing is equipped with a hinge of a symmetrical profile with a balancer connected to it; the focus of the slat is behind its axis of rotation, and the angles of deviation of the slat from the base plane of the wing are limited by the emphasis of forward flight and the emphasis of reverse flight.

Brief Description of the Drawings

Details, features, and advantages of the present invention follow from the following description of an embodiment of the claimed air combat model using the drawings, which show:

in FIG. 1 schematically shows a section along the middle aerodynamic chord (SAX) of the wing of the claimed model, made according to the aerodynamic scheme "tailless".

In the drawing, the numbers and letters indicate the following positions:

1 - wing; 2 - elevator; 3 - section slat; 4 - balancer; 5 - emphasis of normal flight; 6 - emphasis inverted flight; G is the center of mass of the model; F _cr - the focus of the wing model; F _{cr + pr} - the general focus of the wing and both fixed sections of the slat; OO ¹ - axis of rotation of the slat section; C - deviations of model elements at average angles of attack; B - deviations of model elements at large angles of attack.

Disclosure of invention

The model of air combat is made by the tailless aerodynamic scheme. It contains the wing (1) (see Fig. 1) of a symmetrical profile. At the trailing edge of the wing (1), a rudder (2) of height is pivotally connected to the wing. The wing (1) of the model is equipped with a slat, which is placed in front of the wing (1) and pivotally connected with it; it occupies the entire length of the leading edge of the wing except for its central part, where the propeller, not shown, is placed. Thus, in the simplest case, the slat consists of two sections (3) - one for each wing console. Each section (3) of the slat has a symmetrical profile; it is pivotally connected with the wing (1) along the axis ОО ¹ lying in its base plane. Section (3) of the slat is balanced by the balancer (4) relative to the axis ОО ¹ and it is able to freely deviate from the basal plane of the wing within the angle limited by the stop (5) of normal flight and symmetrical stop (6) of the inverted flight. Not marked in the drawing, the focus of the slat section (3) is behind its axis ^of rotation OO ¹ . The model contains a propeller installation and control system, which are not shown in the drawing.

In the drawing, the solid lines show the position of the model elements during horizontal normal flight of the model. In this case, the angle of attack of the wing (1) of the model is small and is approximately plus 2 degrees. The slat section (3) is freely oriented along the oncoming air flow; therefore, in relation to the wing base plane (1), it is inclined at an angle of minus 2 degrees. Free orientation is ensured by the location of the focus of the section (3) behind the axis of OO ¹ and the presence of a balancer (4). Since sections (3) of the slat operate in a vane mode, they do not create lifting force. The model’s centering corresponds to the tailless scheme and its center (G) of masses is 5% of the SAX value in front of the focus (F _cr ) of the wing (1), which ensures the longitudinal stability of the model’s flight.

The second flight mode of the model is to perform a little maneuverable evolution with direct piloting of an aircraft model. In this case, the workers are the average angles of attack, located in the region of plus 6 degrees. In this mode, the slat section (3) also works in the vane mode, and it does not generate lifting force. In relation to the base plane of the wing (1), it will be inclined at an angle of minus 6 degrees. This position of the slat section (3), as well as the elevator (2), is indicated in the drawing by dashed lines with the letter (C). Here, as in the previous case, the alignment of the aircraft model corresponds to the tailless scheme and its center (G) of mass is 5% of the SAX in front of the focus (F _cr ) of the wing (1), which ensures the longitudinal stability of the flight of the aircraft model.

The third flight mode of the model is to perform highly maneuverable evolutions during direct piloting of an aircraft model. The indicated evolution is performed at large angles of attack, which can significantly exceed 10 degrees. In this case, the slat section (3) under the action of the oncoming air flow is also deflected at a large angle, indicated in the drawing by dashed lines with the letter (B). When the slat section (3) comes in contact with the stop (5) of normal flight, it is pressed against it by a counter flow of air and, thus, becomes fixed. And on it there is a lifting force. As a result, the focus of the model is in front of the center (G) of the mass of the model. This position of the model’s focus at large angles of attack is marked on the drawing with a letter (F _{cr + pr} ). The model becomes statically unstable along the longitudinal channel. As a result, the rate of its evolution increases significantly.

Quite similar processes, but in mirror reflection occur during the pilot flight of the model, and here the emphasis (6) of the inverted flight is working.

The invention is applicable not only to the tailless scheme, but also to the normal scheme.

Technical result

The supply of the model with a slat, of course, somewhat reduces its speed, but this decrease is more than offset by significantly increased maneuverability. As a result, the operational properties of the air combat model are improved.

Claims (1)

An air combat model comprising a wing, a propeller-driven installation and an elevator associated with a control system, characterized in that the wing is provided with a symmetrically shaped slat articulated with a balancer, the focus of the slat being behind its axis of rotation, and the angles of deviation of the slat from the base wing planes are limited by forward flight and backward flight.

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