BG66873B1 - Aircraft - Google Patents

Abstract

The aircraft is intended for use in the aerial navigation. It has increased functionality. It consists of a body (1) with a keel (2), a stabilizer (3) and carrying wings (4) with flaps (5), having an aerodynamic profile (6) with a base (7) and upper (8) surface in a thickened (9) and a thin (10) section at its ends. At the protruding end of the thickened section (9) is located along the length of the wing at least one divider (11) of its circumfluent flow, mounted via bearings by carriers (12) in the wing (4) and coupled by means of an axial drive mechanism (13) connected to a control unit (14). The flaps (5) have, in its outgoing ends, a bevelling (15) with a backward inclination relative to the upper surface (8) of the wing (4) in which a second aerodynamic profile (22) is formed, which is inversely directed towards the first profile (6).

Description

Field of technology

The invention relates to an aircraft used in aircraft construction.

BACKGROUND OF THE INVENTION

An aircraft is known, consisting of a body is a shaft, a stabilizer and bearing wings with flaps, having an aerodynamic profile is the main and the upper surface is a thickened and thin section / 1 /.

In this solution, the wings are a constant shape in cross section and create a lifting force only in one-way dressing and have little maneuverability and functionality.

The object of the invention is to provide an aircraft with increased functionality.

Technical essence of the invention

The problem is solved by means of an aircraft, including a body, keel, stabilizer and supporting wings with flaps, having an aerodynamic profile is the main and the upper surface is a thickened and thin section at its ends. According to the invention, at least one divider of the coating fluid (flow) is arranged along the convex end of the thickened section of the sash (sash), mounted by carriers in the sash and an axial drive mechanism is connected, a control unit is connected. The flaps have at their protruding lower ends a bevel is inversely inclined to the upper surface of the wing, in which a second aerodynamic profile is formed, directed back to the first profile.

The second aerodynamic profile is a thickened and thin section directed in the opposite direction of the first profile, which profiles have a common main surface and a common section, between which the thickened sections have gaps forming inclined channels. Flaps are formed at the ends of the common section, respectively for the first and second aerodynamic profile.

The stabilizer has a forward and reverse aerodynamic profile / as the wing / is a common area with corresponding rudder feathers. The keel has a front and rear section, to the opposite ends of which are connected hinged corresponding steering feathers.

An advantage of the invention is the increased maneuverability and, if necessary, the absorption of a large reactive force by creating a lifting force when the wings are flown on both sides and changing their configuration, which increases the functional capabilities of the apparatus.

Explanation of the attached figures

Figure 1 is a side view of the aircraft;

figure 2 - top view of the apparatus;

Figure 2.1 is a top view of the apparatus in another embodiment;

Figure 3 is a cross-sectional view of the wing along AA of Figure 2.1;

Figure 3.1 is a section along Figure AA of Figure 2.1 in another embodiment;

Figure 3.2 is a section along AA of Figure 2.1 in another embodiment;

Figure 3.3 - view in B of Figure 3.2;

Figure 3.4 is a section along AA of FIG. 2.1 in execution is a flap;

figure 3.5 - cross section of the flap;

Figure 4 is a section of the wing along CC from Figure 2 being a divider;

Figure 4.1 is a section along CC from FIG. 2 in another embodiment;

figure 4.2 - section of the wing along CC from fig. 2 in another embodiment;

Figure 4.3 is a section along the CC of FIG. 2 when moving in the opposite direction to FIG. 4.2;

Figure 4.4 is a section along EE of the stabilizer of Figure 4; 2.

Examples of the invention

The aircraft consists of a body 1 is a keel 2, and a stabilizer 3 and supporting wings 4 with flaps 5 having an aerodynamic profile 6 is a main 7 and an upper 8 surface with a thickened 9 and a thinned 10 section at its ends. At the convex end of the thickened section 9 of the wing 4 is located along the length

Descriptions of issued patents for inventions № 05.2 / 31.05.2019 at least one divider 11 of its flow, mounted by carriers 12 in the wing 4 and connected to an axial drive mechanism 13 connected to a control unit 14, the flaps 5 of the wing 4 have at its outlet end a bevel 15 with an inverse inclination to the upper surface 8 of the sash 4.

In one embodiment, FIG. 3, the divider lie is mounted directly in the sash 4, and is otherwise located in a flap 16, FIG. 3.4 of the wing 4. In one embodiment, FIG. 3, the divider 1e is formed as a longitudinal plate 17, partially located in a corresponding gap of the wing 4, and in another embodiment, FIG. 3.2 the divider lie formed as a longitudinal stem / string / 18 with a streamlined profile, the supports of which 19 are mounted in openings in the wing 4.

In another embodiment shown in Figure 3.1, the front end of the divider lie is located behind an elastic band 20 fixed above and below the thickened section 9 of the wing 4.

In one embodiment, FIG. 3, the bevel 15 of the flap 5 is arcuate, and in another embodiment, FIG. 3.5, a longitudinal groove 21 is formed in the bevel 15. The actuator 13 in one embodiment, FIG. 3, is hydraulic, otherwise electromagnetic, mechanical.

In another embodiment shown in Figure 4, a second / reverse / aerodynamic profile 22 is formed in the wing 4 with a thickened 25 and a tapered 24 section directed in the opposite direction to the first 6, which profiles 6,22 have a common base surface 7 and a common section 23, and between the thinned sections 10, 24 of the profiles 6, 22 and their respective thickened sections 9, 25 there are gaps forming inclined channels 26, 27, the outlet ends of which are directed to the main surface 7, wherein the common section 23 is connected with the thickened sections 9, 25 of the wing 4. At the ends of the common section 23 of the wing 4 are formed flaps 5, 28, respectively for the first 6 and the second 22 aerodynamic profile 6, 22. The front 44 and rear 29 end of the housing 1 determine the shape its close to symmetrical.

In one embodiment, Figure 4.2, the thickened sections 9, 25 of the profiles 6, 22 of the sash 4 are fixedly connected to each other and movably relative to the common section 23.

In another embodiment, FIG. 4.1 the thickened sections 9, 25 of the sash 4 are fixedly connected to their common section 23, which has at its upper end a rotating longitudinal valve 30, connected by a known drive mechanism to the control unit 14.

In another embodiment shown in Figure 4.4, the stabilizer 3 has a straight 31 and a reverse 32 aerodynamic profile (like the wing 4) with corresponding steering feathers 33, 34 connected by known actuators to the control unit 14. The keel 2 has a front 35 and a rear 36 a section, to the opposite ends of which respective steering feathers 37, 38 are hinged. Alternatively, the ends of the steering feathers 37, 38 are movably connected to each other.

In another embodiment shown in Figure 2.1, the front end 44 of the housing 1 has a second keel 39 with a corresponding stabilizer 40, which is symmetrical to the first keel 2 with its stabilizer 3, between which there is a synchronizing mechanism 41 (of a known type), connected to the control unit 14.

In the embodiment of FIG. 2.1 a pair of backward-facing wings 4, 43 with one-way flow is used, optionally with movable / hinged / connection of the wings 4, 43 to the housing 1.

Use of the invention

The flow of the support wings 4 creates a lifting force of the aircraft. The movement of the divider 11, including in vibration mode, improves the flow and separation of the fluid flow from the wing 4. The flow is affected by both the direct impact of the divider 11 and the waves created by its elastic band 20. The bevel 15 of the flaps 5 reduces the turbulence of the flow at their ends. The use of wings 4 with two-way flow, fig. 4, allows two-way take-off and landing, and change the direction of flight, using the corresponding flaps 5, 28, rudder feathers 33, 34 from the stabilizer 3 and rudder feathers 37, 38 per keel 2. With wind flow from the rear of the hull 1 , respectively the wings 4, a lifting force is created, increasing the safety. The construction allows a large reactive force to be absorbed by the apparatus, when a large mass is separated from it, from which a lifting force for flying in the opposite direction is created by reversing the engines 42. When reversing one of the flaps 28, 6, fig. 4, the unused channel 27, 26 is closed according to the direction of flight. Similar closure of channel 27, 26, FIG. 4.1 in the wing 4

Descriptions of issued patents for inventions № 05.2 / 31.05.2019 performed by turning the valve 30. The effect is similar, fig. 4.2, when the sections 9, 25 move relative to their common section 23, whereby the working channel 26, 27 is increased and the non-working one is closed, according to the direction of flight. The device can also be used when driving in an environment with increased viscosity, in the liquid phase, with appropriate motors for the case.

Claims (3)

Patent claims An aircraft comprising a keel body, a stabilizer and flap-bearing wings having an aerodynamic profile with a main and an upper surface at a thickened and tapered section at its ends, characterized in that the convex end of the thickened section (9) is located along the wing (4) at least one divider (11) of the flowing stream, mounted by carriers (12) in the wing (4) and connected to an axial drive mechanism (13) connected to a control unit (14) as flaps 5) have at their protruding lower ends a bevel (15) with an inverse inclination to the upper surface (8) of the wing (4), in which a second aerodynamic profile (22) is formed, which is inversely directed towards the first profile (6). Aircraft according to claim 1, characterized in that the second aerodynamic profile (22) has a thickened (25) and a thinned (24) section directed in the opposite direction of the first profile (6), which profiles (6.22) ) have a common main surface (7) and a common section (23), between which and the thickened sections (9 and 25) there are gaps forming inclined channels (26, 27), and at the ends of the common section (23) are formed flaps. 5, 28), respectively for the first (6) and the second (22) aerodynamic profile. Aircraft according to claims 1 and 2, characterized in that the stabilizer (3) has a straight (31) and reverse (32) aerodynamic profile, such as the wing (4), with a common section with corresponding rudder feathers (33,34) ), and the keel has a front (35) and rear (36) section, to the opposite ends of which are connected respective steering feathers (37, 38).