RU2770885C1 - Multifunctional supersonic single-engine aircraft - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: invention relates to aviation, in particular to supersonic aircraft with a low level of radar visibility. The multifunctional supersonic single-engine aircraft contains a fuselage, a trapezoidal wing, a V-shaped all-moving tail, developed side beams, a lower-side air intake engine located under the nose of the fuselage, the channel of which is located along the axis of symmetry of the aircraft, a central and side cargo compartments, a single-engine power plant, including an engine with a jet rotary nozzle located along the axis of symmetry of the aircraft.

EFFECT: aircraft design and layout scheme provide a reduction in the geometric and weight dimensions of the aircraft, a decrease in aerodynamic drag, a decrease in RCS and radar visibility, high flight performance, maneuverability, high stability and controllability of the aircraft, an increase in the relative volume of cargo compartments, the ability to accommodate bulky cargo for various purposes and versatility.

10 cl, 7 dwg

Description

The invention relates to aviation, in particular to supersonic aircraft with a low level of radar visibility.

The prior art multi-mode highly maneuverable aircraft integral aerodynamic layout patent RU 2400402 C1, publ. 09/27/2010, Cl. B64C 30/00, B64C 1/22. The aircraft contains a fuselage, the middle part of which is smoothly connected with the swept wing consoles, the head and tail sections, all-moving vertical tail and all-moving horizontal tail, having the possibility of in-phase and differential deflection, a twin-engine power plant and two main cargo compartments. At the same time, the fuselage, the middle part of which is made flattened, has an increased width in cross section.

From patent RU 2440916 C1, publ. 01/27/2012, Cl. B64D 27/20, B64D 33/02, an aircraft of integral aerodynamic layout is known. The aircraft contains a fuselage, a wing, the consoles of which are smoothly connected with the fuselage, all-moving vertical tail and all-moving horizontal tail, a twin-engine power plant and cargo compartments.

From patent RU 2502643 C2, publ. 12/27/2013, Cl. B64D 7/00, B64D 27/16, B64D 33/02, B64D 45/00, B64D 39/04, B64C 1/36 multifunctional aircraft with reduced radar visibility. The aircraft contains a glider, a twin-engine power plant and a set of onboard equipment.

From patent RU 2583824 C2, publ. 05/10/2016, Cl. B64D 7/08, B64C 30/00 supersonic aircraft with intrafuselage cargo compartments. The aircraft contains a fuselage, in the lower part of which there are large-sized longitudinal cutouts for tandem-arranged cargo compartments.

The disadvantages of the aircraft known from the prior art include a large geometric and weight dimension that arises in connection with the use of two engines. The presence of two main cargo compartments makes it impossible to place bulky cargo in the side compartments. In addition, the placement of the main and side cargo compartments, air intake channels and wheel wells of the main landing gear at the same distance increases the midsection area of the aircraft, which, together with a large number of aerodynamic control surfaces, which increases the area of the washed surface of the aircraft, leads to an increase in weight and aerodynamic drag. aircraft. The presence of an all-moving horizontal tail, which forms an acute angle with the all-moving vertical tail, leads to an increase in the RCS in the lateral hemisphere, to reduce which requires the application of special coatings. The direct channels of the air intakes of the power plant necessitate the installation of special devices in them that reduce the effective dispersion area (ESR) of the engines in the front hemisphere, which also leads to an increase in the weight of the aircraft. The location of the air intakes for blowing out the heat exchangers of aircraft systems and engine compartments on the front of the pylons of the all-moving vertical tail unit leads to an increase in the RCS in the front hemisphere and the lateral hemisphere, which requires the use of special measures to reduce the RCS, causing an increase in aircraft weight.

The technical problem to be achieved by the invention is to eliminate the shortcomings of aircraft known from the prior art and create a light tactical aircraft with a smaller geometric and weight dimension, low radar visibility, and providing the possibility of placing bulky cargo.

The technical result of the claimed invention is to reduce the geometric and weight dimensions of the aircraft, reduce aerodynamic drag, reduce the EPR and radar visibility of the aircraft, ensure high performance and maneuverability, stability and controllability of the aircraft, increase the relative volume of cargo compartments, provide the ability to accommodate bulky cargo for various purposes and ensuring the multifunctionality of the aircraft.

The specified technical result is achieved by the fact that the aircraft contains a fuselage, a trapezoidal wing, a V-shaped all-moving tail, developed side beams, a lower-side air intake of the engine located under the nose of the fuselage, the channel of which is located along the axis of symmetry of the aircraft, a central and side cargo compartments, a single-engine a power plant including an engine with a rotary jet nozzle located along the axis of symmetry of the aircraft.

The consoles of the V-shaped all-moving tail of the aircraft are mounted on pylons and deviated from the vertical plane by an increased angle, preferably 12°-50°, and perform the functions of horizontal and vertical tail.

The channel of the lower-side air intake of the aircraft engine has a bend in the vertical plane and a changing cross-sectional shape from U-shaped to round.

Under the channel of the lower side air intake of the aircraft engine, there is a central cargo compartment.

In the side beams of the aircraft, side cargo compartments, niches of the main landing gear, and equipment compartments are sequentially placed.

The side beams of the aircraft include controlled rotary tail parts located on the tail parts of the beams, and performing the function of the elevator.

On the inner sides of the pylons of the installation of the consoles of the V-shaped all-moving tail unit, there are air intakes for blowing through the engine compartments and heat exchangers of aircraft systems.

In one of the embodiments of the invention, the front horizontal edges of the lower side air intake, the front edges of the trapezoidal wing consoles and the rear edges of the rotary tail parts of the side beams are made parallel.

The side surfaces of the lower parts of the side of the fuselage are deflected from the vertical plane by an increased angle, preferably 12°-50°.

The side surfaces of the lower parts of the fuselage side and the outer side surfaces of the consoles of the V-shaped all-moving tail are deflected by the same angle from the vertical plane.

The invention is illustrated by the following drawings:

fig. 1 - side view of the plane,

fig. 2 - view of the plane from above,

fig. 3 - view of the plane from below,

fig. 4 - front view of the plane,

fig. 5 - section A-A,

fig. 6 - section B-B,

fig. 7 - section B-B.

In the presented drawings, positions are indicated:

1 - fuselage;

2 - side beams;

3 - trapezoidal wing consoles;

4 - console V-shaped all-moving tail;

5 - jet rotary nozzle;

6 - rotary tail parts of the beam;

7 - pylons;

8 - air intakes for blowing out the engine compartments and heat exchangers of aircraft systems;

9 - lower side air intake of the engine;

10 - channel of the lower side air intake of the engine;

11 - central cargo compartment;

12 - side cargo compartments;

13 - niches of the main landing gear;

14 - equipment compartments.

The multifunctional supersonic single-engine aircraft is a monoplane made according to the "tailless" balancing scheme with a V-shaped plumage. The aircraft contains a fuselage 1, developed side beams 2, a trapezoidal wing, the consoles 3 of which are smoothly connected with the fuselage 1, a V-shaped all-moving tail, the consoles 4 of which are deflected from the vertical plane of the aircraft, a single-engine power plant, including an engine with a rotary jet nozzle 5, located along the axis of symmetry of the aircraft in the engine nacelle.

Console 3 of the trapezoidal wing is smoothly connected with the fuselage 1 and is equipped with mechanization of the leading and trailing edges, including rotary socks, elevons, flapperons.

The mechanization of the trapezoidal wing is used to provide control in the roll and pitch channels, improve aerodynamic quality, and also to increase lift.

The consoles 4 of the V-shaped all-moving tail are mounted on pylons, deflected from the vertical plane by an increased angle, preferably 12°-50°, and perform the functions of both horizontal and vertical tail, providing the necessary characteristics of stability and controllability of an aircraft that does not have a horizontal tail .

Thus, in the proposed aircraft, instead of the central rotary horizontal tail unit, an all-moving tail unit is used, which combines the functions of vertical and horizontal tail unit. The V-shaped all-moving tail unit is used as longitudinal, transverse and directional controls and provides effective control and balancing of the aircraft in the longitudinal and transverse channels in all flight modes.

In addition, the absence of a horizontal tail makes it possible to eliminate the acute angle between the vertical and horizontal tail, reduce the number of edges of the aircraft elements, thereby reducing the overall level of the aircraft RCS both in the azimuthal plane and in the lateral hemisphere.

Console 4 V-shaped all-moving tail mounted on fixed pylons 7, mounted on the side beams 2 of the fuselage 1.

The side booms 2 include steerable swivel tails 6 located in the tails of the side booms 2. The swivel tails 6 are used as a longitudinal control, i. serve as elevators for control and balancing in the longitudinal channel.

All available controls while deflecting can be used to increase aerodynamic drag to act as brake flaps.

On the inner sides of the pylons 7 there are air intakes 8 for blowing out the engine compartments and heat exchangers of aircraft systems. In addition, the pylons 7 are the fairings of the hydraulic all-moving tail.

The lower side air intake 9 of the engine is located under the forward fuselage, under the cockpit. The entrance of the lower side air intake 9 of the engine is located below and on the sides of the forward part of the fuselage 1.

The channel 10 of the lower side air intake 9 of the engine has a bend in the vertical plane and a changing cross-sectional shape from U-shaped to round. This embodiment of the channel 10 eliminates the direct visibility of the input guide apparatus of the engine in the front hemisphere.

Under the channel 10 of the lower side air intake 9 of the engine there is a central cargo compartment 11. In front of the side beams 2 of the fuselage 1 there are side cargo compartments 12, behind them in the middle part of the side beams 2 there are niches 13 of the main supports, behind them in the rear part of the side beams 2 are compartments 14 equipment. Behind the compartments 14 of the equipment are rotary tail parts 6 of the side beams.

The proposed design of the aircraft, embodied in a number of interconnected layout elements and the mutual arrangement of elements, namely: the use of a V-shaped all-moving tail, which performs the functions of both horizontal and vertical tail, instead of an all-moving horizontal tail, the location of the lower side air intake of the engine under the nose of the fuselage, the use of a single-engine power plant and the presence of a central and lateral cargo compartments provide a reduction in the geometric and weight dimensions of the aircraft, a decrease in aerodynamic drag, a decrease in the EPR and radar visibility of the aircraft and high flight performance, maneuverability and characteristics of the stability and controllability of the aircraft.

In addition, the use of a lower-side air intake with a channel bent in a vertical plane, which changes the cross-sectional shape from U-shaped to round, makes it possible to exclude direct visibility of the inlet guide vane of the engine and further reduces the EPR of the aircraft in the front and side views, and also makes it possible to place under the lower-side air intake the central cargo compartment is large and ensures stable operation of the engine in all flight modes of the aircraft.

The location of the niches of the main landing gear behind the side cargo compartments allows you to reduce the midsection area, while allowing you to get a significant volume of the side cargo compartments, which ensures the placement of bulky cargo in them. This ensures a reduction in the number of cargo compartments while maintaining the possibility of placing the same number of oversized cargo in comparison with known analogues.

The proposed design and arrangement of the cargo compartments and niches allows them to be made with a large volume while maintaining the small dimension of the aircraft and even reducing the geometric dimension of the aircraft. The presence of cargo edemas of a large volume ensures the placement of bulky cargo for various purposes, due to which the aircraft has versatility.

The execution of the front horizontal edges of the lower side air intake of the engine, the consoles of the trapezoidal wing and the trailing edges of the rotary tail parts of the side beams are parallel, which makes it possible to localize the peaks of electromagnetic waves reflected from the bearing surfaces of the airframe of the aircraft and, thereby, reduce the overall level of radar visibility of the aircraft in the azimuth plane.

The side surfaces of the lower parts of the side of the aircraft and the outer side surfaces of the all-moving tail are deflected by the same angle from the vertical plane of symmetry of the aircraft (see Fig. 4). Such an orientation of the aircraft elements contributes to the reflection of electromagnetic waves falling on the airframe elements from lateral angles into the upper and lower hemispheres, thereby reducing the overall level of the aircraft EPR in the lateral hemisphere.

Thanks to the proposed structural layout of the aircraft, a reduction in radar visibility in the front and side hemispheres is achieved.

Thus, the claimed multifunctional supersonic single-engine aircraft is a new technical solution for volume-weight and structural-power layout and is a light tactical aircraft with high key characteristics: low weight and geometric dimensions, low visibility in the radar wavelength range, high flight performance and maneuverability characteristics, due to which it performs tasks in a wide range of altitudes and flight speeds.

Claims (10)

1. A multifunctional supersonic single-engine aircraft containing a fuselage, a trapezoidal wing, a V-shaped all-moving tail, developed side beams, a lower-side air intake of the engine located under the nose of the fuselage, the channel of which is located along the axis of symmetry of the aircraft, the central and side cargo compartments, a single-engine power installation, including an engine with a jet rotary nozzle located along the axis of symmetry of the aircraft. 2. The aircraft according to claim. 1, characterized in that the console V-shaped all-moving tail mounted on pylons, deflected from the vertical plane at an increased angle, preferably 12-50°, and perform the functions of horizontal and vertical tail. 3. The aircraft according to claim 1, characterized in that the channel of the lower side air intake of the engine has a bend in the vertical plane and a changing cross-sectional shape from U-shaped to round. 4. The aircraft according to claim 1, characterized in that the central cargo compartment is located under the channel of the lower side air intake of the engine. 5. The aircraft according to claim 1, characterized in that the side beams are sequentially placed side cargo compartments, niches of the main landing gear, equipment compartments. 6. The aircraft according to claim. 1, characterized in that the side beams include controlled rotary tail parts located on the tail parts of the beams, performing the function of the elevator. 7. The aircraft according to claim 1, characterized in that it contains air intakes for blowing out the engine compartments and heat exchangers of aircraft systems located on the inner sides of the pylons for installing consoles of a V-shaped all-moving tail. 8. The aircraft according to claim 1, characterized in that the front horizontal edges of the lower side air intake, the front edges of the trapezoidal wing consoles and the rear edges of the rotary tail parts of the beams are made parallel. 9. The aircraft according to claim 1, characterized in that the side surfaces of the lower parts of the fuselage side are deflected from the vertical plane by an increased angle, preferably 12-50°. 10. The aircraft according to claim 1, characterized in that the side surfaces of the lower parts of the fuselage side and the outer side surfaces of the all-moving tail surfaces are deflected by the same angle from the vertical plane.

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