RU2655562C1 - Aircraft with changed wings geometry - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: invention relates to aircraft engineering. Aircraft with variable geometry of the wings comprises a fuselage and wings arranged symmetrically to the longitudinal axis of the fuselage, each of which consists of a fixed on the fuselage base and pivotally mounted on the base with the ability to turn the console. Bases of the wings are fixed on the fuselage hingedly with the possibility of turning. Consoles are mounted on the bases with the possibility of turning with respect to the bases, with the axes of rotation of the consoles in the plane of the wing and placed at an angle to the axis of rotation of the bases. Bases and consoles are pivotally connected to rods hinged with their control devices placed in the fuselage. Axis of rotation of the bases is at an angle to the longitudinal axis of the fuselage. Rotating on their axes, the bases and consoles are controlled by rods pivotally connected to control devices.

EFFECT: invention is aimed at improving performance.

3 cl, 9 dwg

Description

The invention relates to the field of aircraft manufacturing and can be used to create light-engine aircraft, ekranoleta, ekranoplanes and flying cars.

Known aircraft Tu-154 ("Tu-154 aircraft. Design and maintenance", Moscow, "Engineering", 1975, Voloshin F.A., etc.) containing the fuselage and mounted symmetrically to the longitudinal axis of the fuselage, fixed on the fuselage wings with ailerons, flaps and slats. Before takeoff and landing, the slats rotate at a certain angle, and the flaps extend and also unfold at a certain angle. At the same time, the geometry of the wings changes (the curvature of the wings and their area changes), the aerodynamic quality of the wings changes, which reduces the speed of take-off and landing. This increases flight safety, reduces aircraft loads, and also makes it possible to use shorter runways for take-off and landing. To control the aircraft roll use ailerons.

The use of flaps and slats to change the geometry of the wings is justified for aircraft with significant dimensions. However, this significantly complicates the design of the wings, increases their mass, increases the cost of manufacture. Therefore, when creating small-sized light-weight aircraft, the use of wings of this design is often refused. In addition, the described aircraft has significant transverse dimensions, which requires the presence of significant areas during storage of the aircraft at the airport, as well as large production facilities during repair work on the aircraft.

Known aircraft Mig-23 ("Fighter Mig-23", S. Moroz, publishing house "Exprint", 2005) containing the fuselage and wings placed symmetrically to the longitudinal axis of the fuselage, made in the form of swept bases fixed on the fuselage with pivotally mounted on them consoles equipped with slats, flaps and spoilers. In the initial position, the sweep of the leading edges of the bases and consoles is the same. The axis of rotation of the consoles relative to the bases are directed perpendicular to the planes of the wings. Before takeoff and in flight before landing, the cantilevers unfold relative to the bases in the direction of flight, the slats and flaps deviate by a certain angle. There is a change in the geometry of the wings. In this case, the sweep of the leading edges of the consoles, in comparison with the sweep of the leading edges of the bases, decreases significantly, the wing area and the general curvature of the wing profile change, which makes it possible to significantly reduce the take-off and landing speed. As a result of these measures, flight safety is increased, aircraft loads during takeoff and landing are reduced, and it is also possible to use shorter runways. To increase the flight speed of the console are deployed relative to the bases in the starting position. Flaps and slats also return to their original position. To control the aircraft roll used interceptors.

The wing structure of this aircraft is quite complex, which increases the mass of the aircraft and its cost. To control slats, flaps and interceptors placed on the rotary consoles, complication of their control mechanisms is required, which also leads to an increase in the mass and cost of manufacture. In addition, to transport the aircraft by air, land or water transport, to reduce the size you will have to undock the wings, which complicates the technology of transportation and transfer of the aircraft to its working position after transportation. Also, large dimensions require large areas of structures when stored in structures (for example, in protected hangars).

The task to which the invention is directed is to simplify the design of the aircraft, reduce its mass, change its aerodynamic characteristics in a wide range of flight modes, increase flight safety, simplify transportation and storage.

This problem is solved due to the fact that the wing bases are pivotally mounted on the fuselage, the consoles are mounted on the bases with the possibility of rotation relative to the bases, with the rotation axles of the consoles located in the wing plane and angled to the rotation axes of the bases, base and console connected to rods articulated with their control devices located in the fuselage, and the axis of rotation of the bases relative to the fuselage are at an angle to the longitudinal axis of the aircraft but.

The control device of the rods connected to the wing bases can be made in the form of a slider mounted with the possibility of translational movement on a guide mounted in the fuselage.

The control device of the rods connected to the consoles can be made in the form of a mechanism that provides simultaneous movement of the rods both in different directions and in one direction

The technical result provided by the given set of features is that, using the proposed design of a controlled wing with variable geometry, it is possible to change the aerodynamic characteristics of an aircraft in a wide range directly in flight, the general kinematics of controlling the wing is simplified, which should improve the flight characteristics of the created aircraft and to simplify their transportation and storage, reduce production costs.

The essence of the invention is illustrated by drawings, where

- in FIG. 1 shows a General view of the aircraft in a variant of the hydroplane in its initial state (axonometry);

- in FIG. 2 shows a seaplane in front view in the initial state;

- in FIG. 3 shows a seaplane in the left view in the initial state with the open fuselage (view A);

- in FIG. 4 shows a seaplane in a top view in the initial state (view G);

- in FIG. 5 shows a section B-B (axonometry);

- in FIG. 6 shows a section bb (axonometry);

- in FIG. 7 shows a seaplane in front view in the state of the geometry of the wings, providing take-off of the seaplane;

- in FIG. 8 depicts a seaplane in front view in the state of the geometry of the wings, providing control of the seaplane along the roll;

- in FIG. 9 shows a seaplane in the state of wing geometry, simplifying the transportation of a seaplane.

The aircraft (hydroplane) consists of the fuselage 1 (see Fig. 1) and mounted on the fuselage 1 symmetrically to the longitudinal axis of the fuselage 1 of the left and right wings. The left wing consists of a left base 2, pivotally mounted on the fuselage 1 with a possibility of a turn and a left console 3, pivotally mounted with a possibility of a turn on a left base 2. The axis of rotation of the left base 2 is at an angle to the longitudinal axis of the fuselage 1, and the axis of rotation the left console 3 is located in the plane of the wing and is placed at an angle to the axis of rotation of the left base 2 relative to the fuselage 1. The right wing consists of a right base 4, pivotally mounted with the possibility of rotation on the fuselage 1, and the right console 5, pivotally mounted with a possibility of a turn on the right base 4. The axis of rotation of the right base 4 is at an angle to the longitudinal axis of the fuselage 1 (see Fig. 4), and the axis of rotation of the right console 5 is in the plane of the wing and placed at an angle to the axis of rotation of the base 4 relative to the fuselage 1. The left base 2 and the right base 4 are pivotally connected to the rods 6 (see Fig. 5), the opposite ends of which are pivotally connected to the control device for turning the left base 2 and the right base 4, made in the form of pivotally connected 6 with the rods of the slider 7 mounted for translational movement on guide 8 fixed in the fuselage 1. The left and right arm 3 console 5 is pivotally connected with the rods 9 (see FIG. 6), the opposite ends of which are pivotally connected with the control device for the turn of the left console 3 and the right console 5, made in the form of a pivotally connected with the rods 9 of the rocking chair 10, pivotally mounted with the possibility of a turn on the housing 11, arranged for translational movement on the guide 12, fixed in the fuselage 1.

The seaplane operates as follows. In the initial state, before take-off, the relative position of the hydroplane elements and the geometry of the wings are shown in Figs. 1, 2, 3, 4, 5, 6. To reduce the take-off speed of the hydroplane and to reduce the path length, the slider 7 moves along the guide 8 a certain distance upward, as a result of which rods 6 are deployed relative to the fuselage 1, the left base 2 and the right base 4 at the required equal angle up. By moving the housing 11 relative to the guide 12, the rocker 10 is displaced from the initial position, as a result of which the rods 9 unfold the left console 3 relative to the left base 2 and the right console 4 relative to the right base 5 to the required equal angle downward. In this case, the wings take the geometric shape shown in FIG. 7. The resulting geometry of the wings provides take-off of the seaplane with a reduced speed and a shortened take-off run.

After gaining the required flight altitude and speed by moving the slider 7 and the body 11, the wing geometry returns to its original state, the speed of the aircraft increases.

Before landing, the geometry of the wings is changed in the same manner as described above. This provides a reduction in landing speed and a reduction in mileage.

By moving the slider 7 and the body 11, it is possible to give the wings a geometry that provides the maximum “screen” effect. At the same time, the seaplane can fly above the water surface, like an ekranoplane, which will significantly increase the mass of the payload transported by the seaplane.

The roll of the seaplane is controlled by turning the rocker 10 by the required amount in the right direction. In this case, with rods 9, the left console 3 relative to the left base 2 and the right console 5 relative to the right base 4 are synchronously deployed at a certain angle in opposite directions. As a result of this, a torque occurs, causing the hydroplane to turn around its longitudinal axis. The geometry of the wings at this point is shown in FIG. 8.

To ensure the movement of the slider 7, the housing 11, as well as the swing of the rocker 10, various types of drives can be used, the selection of which and determination of their parameters is carried out at the design stage of the aircraft.

To simplify the transportation of the seaplane and its storage conditions, the dimensions of the seaplane can be significantly reduced. To do this, the rods 9 are disconnected from the left console 3 and the right console 5, as well as from the rocker 10. Then, the left console 3 and the right console 5 are turned towards the fuselage 1 at the maximum possible angle. In this position, the left console 3 and the right console 5 can be fixed with technological latches.

For even more compact folding of the wings, it is possible to provide for the detachment of the rods 6 from the bases 2 and 4, and the rods 9 - from the consoles 3 and 5, and, turning the consoles 3 and 5 down and the bases 2 and 4 up, press them to the fuselage 1 in the folded form.

For movement on the ground, it is possible to provide a retractable wheeled chassis.

The proposed design of an aircraft with variable wing geometry is quite feasible using modern scientific and technical groundwork for aircraft and can be used to create light-weight aircraft such as ekranolets, ekranoplanes, aircraft and flying cars.

Due to the simplicity of the design of such aircraft, their manufacture should not require large material costs.

Claims (3)

1. Aircraft with variable wing geometry, comprising a fuselage and wings placed symmetrically to the longitudinal axis of the fuselage, each of which consists of a base fixed to the fuselage and pivotally mounted on the base to rotate the console, characterized in that the wing bases are pivotally mounted on the fuselage of rotation, the consoles are mounted on the bases with the possibility of rotation relative to the bases, with the rotation axes of the consoles located in the wing plane and placed at an angle to the axes p the rotations of the bases, the bases and the console are pivotally connected to the rods pivotally connected to their control devices located in the fuselage, and the axis of rotation of the bases relative to the fuselage are at an angle to the longitudinal axis of the aircraft. 2. An aircraft with variable geometry according to claim 1, characterized in that the control device for the rods connected to the wing bases can be made in the form of a slider mounted with the possibility of translational movement on a guide mounted in the fuselage. 3. Aircraft with variable wing geometry according to claim 1, characterized in that the control device for the rods connected to the consoles can be made in the form of a mechanism that provides simultaneous movement of the rods both in different directions and in one direction.

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