Tactical light aircraft

Abstract

The invention relates to the field of aviation, and more particularly to tactical light aircraft having low radar detectability. The technical result consists in increasing the stability and handling properties of an aircraft without negatively impacting its detectability characteristics. The claimed tactical light aircraft comprises a fuselage with lateral tail booms, wing panels, a tail assembly, an air inlet, a power plant, and a propelling nozzle. The lateral tail booms are developed and terminate in parts that are rotatable on a horizontal axis. Arranged on the wing panels, which are highly swept, are rotatable leading edges and inner and outer elevons. The tail assembly is V-shaped with all-moving panels that act as both a horizontal and a vertical stabilizer. The air inlet is disposed in the bottom part of the fuselage, partially encompassing same from below.

Description

[0001] LIGHT TACTICAL AIRCRAFT

[0002] Field of technology

[0003] The invention relates to the field of aviation, in particular to light tactical aircraft with low radar signature.

[0004] Prior art

[0005] A supersonic convertible aircraft is known from the prior art (see patent RU 2432299 C2, published on 27.10.2011), which contains a fuselage with a lower air intake and a V-shaped tail unit.

[0006] However, the design of the known aircraft has a drawback, consisting of insufficient stability and controllability of the aircraft, as well as a fairly high radar signature.

[0007] The Lockheed F-117A Nighthawk aircraft with low radar visibility is also known from the state of the art, it is made according to the scheme "tailless with V-shaped tail" without horizontal tail. On the wing of the known aircraft there are deflectable elevons. Pitch and roll control is carried out by elevons, yaw - by an all-moving vertical tail.

[0008] However, the disadvantage of this aircraft is its poor takeoff and landing characteristics, as well as insufficient stability and controllability of the aircraft.

[0009] Disclosure of invention

[0010] The objective of the claimed invention is to eliminate the disadvantages of aircraft known from the state of the art. Thus, the technical result, which the claimed invention is aimed at achieving, is to increase the stability and controllability of the aircraft without worsening the characteristics of radar visibility. The light tactical aircraft comprises a fuselage with side tail booms, wing consoles, a tail unit, an air intake, a power plant and a jet nozzle. The side tail booms are developed and end with parts that rotate on a horizontal axis. On the wing consoles, which have a large sweep, there are rotating noses and internal and external elevons. The tail unit is made V-shaped, the consoles of which are made all-rotating, performing the function of both horizontal and vertical tail. The air intake is located in the lower part of the fuselage and partially covers it from the bottom.

[0011] The rotating jet nozzle is located along the axis of symmetry of the fuselage and is used for control and balancing in flight and is designed to be deflected in the vertical plane.

[0012] The rotating jet nozzle is located along the axis of symmetry of the fuselage and is used for control and balancing in flight and is designed for all-aspect control.

[0013] The rotation axes of the V-shaped tail consoles are located perpendicular to the fuselage axis.

[0014] The rotation axes of the V-shaped tail consoles are located closer to the leading edge of the consoles.

[0015] All edges of the air intake are arrow-shaped.

[0016] Brief description of the drawings The claimed invention is further explained in more detail by drawings, in which:

[0017] Fig. 1 - the claimed aircraft, top view,

[0018] Fig.2 - the claimed aircraft, front view,

[0019] Fig.3 - the declared aircraft, side view.

[0020] The best embodiment of the invention The claimed light tactical aircraft comprises a fuselage (1) with developed side tail booms (2) and an air intake (10) of the power plant, wing consoles (3) and a V-shaped tail unit (4). The air intake (10) is located in the lower part of the fuselage (1) and partially covers it from the bottom (see Fig. 2). The wing consoles (3) are made with a large sweep (40-55°) and have deflectable wing leading edges (6). On the trailing edge of the wing console (3) are located internal (7) and external (8) elevons. The side tail booms (2) end in rotating parts (5), which perform the function of elevators.The V-shaped tail unit (4) is all-moving, simultaneously plays the role of horizontal and vertical tail unit, and provides the ability to control the aircraft in the longitudinal channel with in-phase deviation and in the transverse channel with differential deviation, and also provides stability and controllability in the trajectory channel at all flight speeds and provides the air braking function. The trajectory stability at supersonic flight speeds with insufficient static stability is provided artificially, due to the deflection of the consoles of the V-shaped tail unit (4). When an atmospheric disturbance or a gust of wind occurs in the trajectory channel, the in-phase deflection of the consoles of the V-shaped tail unit (4) is carried out in the direction of parrying the disturbance. Such a solution allows to reduce the area of ​​the tail unit, thereby reducing the mass and drag of the tail unit and the aircraft as a whole.Control in the track channel is carried out with a common-mode deflection of the V-shaped tail unit (4), and air braking is carried out with a differential deflection of the V-shaped tail unit (4).

[0021] The rotation axes of the V-shaped tail consoles are located perpendicular to the fuselage axis and are located closer to the leading edge of each console. The wing mechanization (3) is used to provide control in the pitch and roll channels, to increase the lift. The rotating nose (6) of the wing is used to increase the critical angle of attack and provide shock-free flow around the wing (3), for flight "along the enveloping polar" in takeoff, landing, maneuvering and subsonic cruising flight modes. Elevons (7, 8) are designed to control the aircraft in pitch with in-phase up-down deflection, increase lift with in-phase down deflection in various modes due to an increase in the curvature of the median wing surface, and control in roll with differential deflection.When providing the air braking function, the elevons (7, 8) are deflected together with other elements in such a way as to ensure an increase in aerodynamic drag with a zero increment in the total pitch moment.

[0022] The rotating parts (5) of the side tail booms, when deflected up and down, are used for pitch control, performing the functions of the elevator; in takeoff and landing modes, they serve to compensate for the nose-down moment that occurs when the elevons (7, 8) are deflected to increase the wing lift. When providing the air braking function, the rotating parts 5 are deflected together with other elements, ensuring an increase in resistance and a zero increment in the total pitch moment.

[0023] The design of all air intake edges as arrow-shaped ones ensures a reduction in the aircraft's radar signature.

[0024] The rotating jet nozzle (9) of the aircraft engine is located along the axis of symmetry of the fuselage and is used for control and balancing in flight; it can be designed to deflect only up and down in the vertical plane, or all-aspect.

[0025] All available controls (V-shaped tail unit, wing leading edges, elevons, rotating parts of the boom) when deflected simultaneously increase aerodynamic drag, thereby performing the function of brake flaps.

[0026] Industrial applicability

[0027] The presence of all the above control elements in the aircraft design together make it possible to move the zones of occurrence of unbalanced static instability of the aircraft in the longitudinal and directional control channels to the range of angles of attack of 15° or more, to increase the load-bearing properties and reduce the resistance of this aerodynamic configuration of the aircraft, which is confirmed by calculations and tests of the model in wind tunnels, and make it possible to have operational angles of attack, a level of aerodynamic quality that provide a significant improvement in cruising, maneuvering and takeoff and landing characteristics compared to known analogues.

[0028] The presented configuration of the light tactical aircraft, due to the declared design, ensures maximum controllability of the aircraft in any flight mode and at the same time does not increase the radar visibility of the aircraft.

Claims

Invention formula 1. A light tactical aircraft comprising a fuselage with side tail booms, wing consoles, a tail assembly, an air intake, a power plant and a rotating jet nozzle, characterized in that the side tail booms are developed and end in parts that rotate on a horizontal axis, on the wing consoles, which have a large sweep, there are rotating noses and internal and external elevons, and the tail assembly is made V-shaped, the consoles of which are made all-moving, performing the function of both horizontal and vertical tail, and the air intake is located in the lower part of the fuselage and partially covers it from the bottom.

2. A light tactical aircraft according to paragraph 1, characterized in that the rotating jet nozzle is located along the axis of symmetry of the fuselage and is used for control and balancing in flight and is made deflectable in the vertical plane.

3. A light tactical aircraft according to paragraph 1, characterized in that the rotating jet nozzle is located along the axis of symmetry of the fuselage and is used for control and balancing in flight and is made all-aspect.

4. A light tactical aircraft according to paragraph 1, characterized in that the axis of rotation of the V-shaped tail consoles is located perpendicular to the axis of the fuselage.

5. A light tactical aircraft according to paragraph 4, characterized in that the axis of rotation of the V-shaped tail consoles is located closer to the leading edge of the consoles. 7 SUBSTITUTE SHEET (RULE 26) 6. A light tactical aircraft according to paragraph 1, characterized in that the air intake is located in the lower part of the fuselage and partially covers it from the bottom.

7. A light tactical aircraft according to paragraph 6, characterized in that all edges of the air intake are swept back. 8 SUBSTITUTE SHEET (RULE 26)

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