RU2806135C1 - Rotary part of aircraft tail boom - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: rotating part of the aircraft's tail boom is a control surface designed to control an aircraft having a wing with an elevon and a wingtip, and is designed as an extension of the aircraft's tail boom with the possibility of deflection. In this case, this part includes the front end, the upper and the lower panels, the rear edge and internal compartments for accommodating a set of on-board equipment and antenna posts. In this case, the said rear edge of the rotating part of the tail boom and the rear edges of the said wing tip and elevon are made so that they can be located parallel.

EFFECT: improved take-off and landing characteristics, stability and controllability characteristics of the aircraft, reduced area of the aircraft's washed surface, reduced aerodynamic drag, reduced loads on the rear fuselage, reduced weight of the aircraft. and reduced radar signature.

4 cl, 3 dwg

Description

Field of technology

The invention relates to the field of aviation technology, in particular to control surfaces (rudders), and can be used to control an aircraft.

In order to ensure competitiveness, modern aircraft must meet the requirements for high flight performance, low radar signature and have a developed set of on-board equipment. These requirements are achieved, among other things, by shaping the airframe, reducing the area of the washed surface, the density of the layout and the weight of the aircraft, as well as giving individual units the properties of multifunctional systems.

The traditional horizontal tail leads to an increase in the level of radar signature, airframe wash surface, aerodynamic drag, and also causes the appearance of parasitic torque on the rear fuselage. At the same time, the absence of horizontal tail impairs the takeoff, landing and maneuverability characteristics of aircraft due to a decrease in stability and controllability characteristics. Therefore, there is a need to use developed control surfaces made in the form of an extension of the rear fuselage.

State of the art

From RU patent No. 2749175, published. 06/07/2021, Cl. B64C 1/36, H01Q 1/28, H01Q 3/00, the Su-57 aircraft is known, containing a fuselage equipped with bulges, which are located above the engine air intakes and include controlled rotating parts, while the rotating part of the fuselage bulge is made in the form of a removable antenna system, including a load-bearing frame with casing and consisting of an antenna and instrument sections. The use of the specified implementation of control surfaces makes it possible to create a diving pitch moment when deflecting downwards, but practically does not create a pitching moment when deflecting upwards. The known rotating parts of the fuselage influx can affect the characteristics of the engine air intake during deflection, which requires the implementation of additional design solutions to ensure safety in the event of failure of the organ drive. In a famous airplane, the antennas are located along the edge of the organ.

The MiG “1-44” aircraft (“Mig”: flight through time” by E.V. Arsenyev et al., p. 380) is known, the consoles of which are equipped with developed rear overhangs with additional multifunctional control surfaces. The direct use of such an implementation of control surfaces does not allow for a reduced level of radar signature due to the peculiarities of shaping and the presence of pronounced drive fairings on the lower and upper surfaces.

In contrast to the additional rear influx of the MiG "1-44", the rotating tail parts of the side boom are the main balancing element and fully ensure the takeoff, landing and maneuverability of the aircraft, the low radar signature of the aircraft as a whole due to the shaping and shielding of individual elements.

Disclosure of the Invention

The technical problem to be solved by the invention is to develop a design for the rotating part of the tail boom for controlling the aircraft and ensuring its low radar signature, without reducing the aerodynamic characteristics.

The invention provides a technical result consisting in increasing takeoff and landing characteristics, stability and controllability characteristics of the aircraft, reducing the area of the aircraft's washed surface, reducing aerodynamic drag, reducing loads on the rear fuselage, reducing the weight of the aircraft as a whole, and reducing radar signature.

The technical result is achieved by the rotating part of the tail boom, which is a control surface designed to control an aircraft having a wing with an elevon and a wingtip, and made in the form of a continuation of the tail boom of the aircraft with the possibility of deflection, including a windshield, upper and lower panels, a trailing edge and internal compartments to accommodate a complex of on-board equipment and antenna posts, wherein said rear edge of the rotating part of the tail boom and the rear edges of said wing tip and elevon are made so that they can be located parallel. The rotating part of the tail boom has large construction heights from 130 mm to 350 mm. The rotating part of the tail boom in one embodiment contains a rotation drive in the internal compartment; in an alternative embodiment, the rotation drive of the rotating tail part is located outside its volume.

Brief description of drawings

The invention is illustrated by the following images:

fig. 1 - general view of the rotating part of the tail boom;

fig. 2 - rotating part of the tail boom as part of the aircraft,

fig. 3 - rear-top view of the rotating part of the tail boom in its various positions within the aircraft.

The following notations are used in the figures:

1 - windshield formed by a surface of rotation,

2 - upper and lower panels of large radius of curvature,

3 - trailing edge,

4 - internal compartments,

5 - rotating part of the tail boom,

6 - tail boom (tail part of the fuselage),

7 - wing console,

8 - wing tip,

9 - elevon.

Carrying out the invention

The rotating part of the tail boom is made in the form of a continuation of the tail boom, i.e. the tail section of the aircraft fuselage, made according to the “tailless with V-shaped tail” design and without horizontal tail. The rotating part of the tail boom is a developed control surface, i.e. an additional control element for the aircraft, and serves to control and balance the aircraft, made according to the “tailless with V-shaped tail” design, in the longitudinal channel.

The rotating part 5 of the tail boom 6 contains a front end 1, upper and lower panels 2, a trailing edge 3. The trailing edge 3 of the rotating part 6 of the tail boom is parallel to the edges of the wing tip 8 and the elevon 9 of the aircraft. The internal free volume 4 of the rotating part 6 of the tail boom is used to accommodate blocks of the on-board equipment complex and antenna posts.

The rotating part of the tail boom is designed to be deflectable relative to the transverse axis of the aircraft. The deflection of the rotating part of the tail boom is provided by the drive.

The ability to deflect the tail boom, made in the form of a rotating part of the tail boom, provides increased takeoff and landing characteristics, stability characteristics and controllability of an aircraft with a V-shaped tail. The rotating part of the tail boom does not affect the characteristics of the engine air intake when deflected, and, accordingly, does not require the introduction of additional design solutions to ensure safety in the event of failure of the organ drive.

Making the trailing edge 3 of the rotating part 5 of the tail boom parallel to the edges of the wing tip 8 of the aircraft and the elevon 9 of the aircraft makes it possible to reduce the range of swept edges, thereby reducing the number of peaks in the scattering diagram, reducing the overall level of radar signature of the aircraft.

The rotating tail section of the beam has large construction heights ranging from 100 mm, preferably from 130 mm to 350 mm. The shape of the rotating part of the tail boom and large building heights make it possible to place compartments of the onboard equipment complex and antenna posts in the internal volumes of the rotating part of the tail boom. In addition, a drive for its rotation can be placed in the internal volume of the rotating part of the tail boom. Placing units and systems of elements inside the rotating part of the tail boom makes it possible to increase the density of the aircraft layout. In addition, placing the drive inside the rotating part of the tail boom eliminates fairings and sagging on the outer surface of the aircraft. This ensures a reduction in the area of the aircraft's washed surface and, as a consequence, a reduction in the aerodynamic drag of the aircraft. In this case, the drive for turning the rotating part of the tail boom can be placed outside the volume of the rotating tail boom.

The rotating part of the tail boom is a multifunctional system, which is a developed control surface, made in the form of an extension of the rear fuselage, into which a wide range of antenna posts is integrated and compartments of the on-board equipment complex are located.

The rotating part of the tail boom can be used to control an aircraft of various types of aircraft, in particular aircraft with reduced radar signature and/or an aircraft that does not have a horizontal tail, and is not limited to the embodiments of the invention described in the description.

The invention can be used to control an aircraft in various control channels.

Thus, the rotating part of the tail boom performs the functions of an aerodynamic control surface, i.e. additional control element of the aircraft, provides an increase in takeoff and landing characteristics, stability and controllability characteristics of the aircraft, a reduction in the area of the aircraft's washed surface, minimizing aerodynamic drag, reducing loads on the rear fuselage, reducing the weight of the aircraft as a whole, increasing the density of the aircraft's layout and reducing radar signature.

Claims (4)

1. The rotating part of the tail boom of the aircraft, which is a control surface designed to control an aircraft having a wing with an elevon and a wingtip, and made in the form of a continuation of the tail boom of the aircraft with the possibility of deflection, including a front end, upper and lower panels, a trailing edge and internal compartments for housing a complex of on-board equipment and antenna posts, wherein said rear edge of the rotating part of the tail boom and the rear edges of said wing tips and elevon are made so that they can be located parallel. 2. The rotating part of the tail boom according to claim 1, having large construction heights from 130 mm to 350 mm. 3. The rotating part of the tail boom according to claim 1, in the internal compartment of which the rotation drive is located. 4. The rotating part of the tail boom according to claim 1, the rotation drive of which is located outside its volume.