RU2400402C1 - Multimode high maneuverability aircraft of integral aerodynamic configuration - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: proposed aircraft comprises airframe wherein central part 2 smoothly fairs with backswept outer wings 3, nose part 1 and tail part 6 wherein all-moving vertical tail 4 and horizontal tail 5 are arranged. Canopy 10 is arranged in airframe hose 1. Airframe features greater width in cross section and is made up of aerodynamic profiles with their height allowing accommodating freight compartment between air intakes.

EFFECT: uniform distribution of air load and increased load bearing qualities of airframe.

10 dwg

Description

The invention relates to multi-mode aircraft operating at supersonic and subsonic flight speeds in a wide range of flight heights. An advantageous field of application of the invention is multimode super-maneuverable aircraft with cruising at supersonic speeds and a low level of visibility in the radar (RL) range.

The prior art aircraft integrated aerodynamic layout containing a single supporting fuselage, in which the middle part of the fuselage is smoothly mated with swept wing consoles, the head of the fuselage and its tail (RU 2140376 C1).

The disadvantages of the known aircraft should indicate the following. In a well-known aircraft, the placement of goods on an external suspension does not allow to achieve a low degree of radar visibility and high aerodynamic characteristics at supersonic flight modes.

Due to the complex of technical solutions used in this layout and, above all, the integrated aerodynamic layout of the fuselage, the aircraft is characterized by a high value of aerodynamic quality in subsonic flight modes.

The technical result to which the invention is directed is to create an aircraft with a low radar degree of visibility, super maneuverability at large angles of attack, high aerodynamic quality at supersonic speeds and, at the same time, maintaining high aerodynamic quality at subsonic modes.

The specified technical result is achieved by the fact that in a multi-mode highly maneuverable aircraft of an integrated aerodynamic layout containing a fuselage, the middle part of which is smoothly interfaced with the swept wing consoles, the head part of the fuselage and its tail part, the whole-rotated vertical and all-rotational horizontal tailings located in the rear middle part of the fuselage part of the fuselage is integrated with the center wing and is made flattened in the vertical direction, and its outer surface in The native direction is formed by a set of aerodynamic profiles with high building heights, which ensure that the built-in cargo compartments are placed inside the fuselage, while the upper surface of the fuselage is conjugated with the external surface of the lamp and expanding from the lamp to the rear of the fuselage of the aircraft with a decrease in curvature.

The invention is illustrated by drawings, where in Fig.1 shows an airplane when viewed in plan; figure 2 is a section aa of figure 1; figure 3 is a section bB of figure 1; figure 4 is a section bb In figure 2; figure 5 is a section GG of figure 2; figure 6 - the body of rotation of the least resistance (body Siires-Haak); Fig.7 - the place of cross-sections of the fuselage; in Fig.8 is a cross section of Fig.7; figure 9 is a graph of the cross sections of the fuselage of the aircraft; figure 10 is an enlarged part of the graph of the cross-sectional areas of the fuselage behind the lamp.

The aircraft contains a fuselage, in which the middle part 2 is smoothly interfaced with the swept wing consoles 3, the head part 1 of the fuselage and its tail part 6. In the tail part 6 of the fuselage there is a fully rotatable vertical 4 and a rotatable horizontal tail unit 5. In the head part 1 of the fuselage there is a flashlight 10 .

From the point of view of the aerodynamic configuration, the aircraft has the following features: a wide bearing fuselage and a smoothed-out graph of the plane cross-sectional areas in the area behind the cockpit.

The fuselage has an increased width in cross section (Fig. 1, 2) and is composed of aerodynamic profiles 11, 12, 13 (Figs. 3, 4, 5), the height of which allows you to place the main cargo compartment 9 in the fuselage of the plane (Fig. 2, 3) between the air intakes 8, and also gives the necessary building heights to accommodate the side cargo compartments 7 (figure 2, 4).

In addition to the place for placing cargo, the consequence of the flattened layout is a uniform distribution of air load over the surface of the airframe and an increase in the bearing properties of the fuselage from the point of view of creating lift, which allows you to save the aerodynamic characteristics of the aircraft as a whole with a smaller wing area,

In addition, such a flattening of the fuselage reduces the effective radar area in the most likely directions of exposure: side and front projection of the aircraft.

Smoothing the graph of the cross-sectional area of the aircraft in the area behind the cockpit can improve the aerodynamic characteristics of the aircraft by reducing aerodynamic drag.

In addition to the general theoretical contour, the aerodynamics of the aircraft and drag are influenced by the relative position and mutual coordination of the aircraft parts. To assess the drag from mutual influence (interference) in the design, the area rule is used (Fig. 6), which is as follows: in order to reduce the resistance, the plot of 14 cross-sectional areas ΣS _{j of} all elements of the aircraft along the length of the aircraft should correspond to the plot of the equivalent body rotation of the least resistance (cigar-shaped body of large elongation, the so-called body of Siirs-Haak).

According to the prior art, when designing airplanes, the lantern and fuselage linking scheme shown in Fig. 8 is used (A is a generally accepted diagram), which is characterized by the fact that the cross-sectional area decreases in the area from the lantern to the tail. The area graph for this scheme has a pronounced deviation from the Siires-Haack body in the region of the lantern (Fig. 9 and Fig. 10, section A).

To improve the aerodynamic characteristics, a linkage scheme was developed, consisting in the fact that the upper surface of the fuselage 15 expands in the area from the flashlight 10 to the rear part 6 of the fuselage, compensating for the reduction in cross-sectional area (Fig. 8, B - invented scheme), as a result of which the “failure” is smoothed out »On the area chart behind the pilot’s lantern, typical for a traditional integrated aerodynamic layout aircraft. At the same time, the curve on the area graph approaches the optimal shape, which indicates an improvement in aerodynamic characteristics (Fig. 10, section B) by reducing drag.

Claims (1)

A multi-mode highly maneuverable aircraft with an integrated aerodynamic configuration, comprising a fuselage, the middle part of which is smoothly interfaced with the swept wing consoles, the head part of the fuselage and its tail part, all-rotational vertical and all-rotational horizontal plumage located in the rear part of the fuselage, characterized in that the middle part is integrated center wing and made flattened in the vertical direction, and its outer surface in the longitudinal direction is formed abord airfoils with high building heights, providing a placement inside the fuselage built cargo compartments, with the upper surface of the fuselage is made conjugate with the outer surface of the lamp and expanding the area of the lamp to the tail section of the aircraft fuselage with decreasing curvature.

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