RU2713579C1 - Aircraft wing - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: invention relates to the aviation equipment. Wing of aircraft consisting of center section, cantilever and required functional systems is made with extension λ=7–11, narrowing η=3–4.5 and sweep to χ=35° and containing supercritical profiles. Wing is made up of four piece segments. Wing comprises front edge of wing, at top view straight and without an influx. Rear edge of wing is made with an influx and has four coordinates of fracture along wingspan. Relative thickness of profiles has the value of about 13–14 % in the side section and decreases to 8–9 % in the end section, monotonously decreasing in section from 40 % to its end. Wing is designed with positive swirling ε=2–2.5° in side section. End cross-sections are designed with negative swirling ε=-2…-3.6°. Act change of twist in span has practically linear decreasing character in range from 25 to 100 % of wingspan. Wing is formed by five basic sections, obtained by means of multi-stage optimization procedure, consisting of stage of initial choice of geometry, stage of solving inverse problem and stage of multi-mode optimization.

EFFECT: invention is aimed at providing cruising flight speeds of M_cr=0,84–0,9 while maintaining high aerodynamic quality and fuel efficiency.

1 cl, 6 dwg

Description

FIELD OF THE INVENTION

The present invention relates to aircraft.

The invention can be used in the development of the wings of promising medium and long-haul passenger aircraft.

Along with the need to ensure a high level of aerodynamic quality and fuel efficiency in the design of promising wings of passenger aircraft, special attention is paid to improving the speed and safety of flight. The proposed wing is designed for operation in the cruising speed range M = 0.84-0.9 while maintaining high values of aerodynamic quality and fuel efficiency.

State of the art

Various wing patterns of modern passenger aircraft are known. A typical wing of a passenger aircraft consists of a center section, a console and the necessary functional systems.

The wing of a Boeing B-777-300 aircraft is known (see Passenger Airplanes of the World, compiled by Belyaev V.V., pp. 230-231, Moscow, ASPOL, Argus 1997), made with lengthening λ = 7-11, narrowing η = 3-4.5, sweep χ _1/4 = 30-35 °.

The wing of the Airbus A330-200 aircraft is known (see Passenger Airplanes of the World, compiled by Belyaev V.V., pp. 122-123, Moscow, ASPOL, Argus 1997), made with lengthening λ = 7-11, narrowing η = 3 -4.5, sweep χ _1/4 = 30-35 °.

Known wing with an influx (RF Patent No. 2248303 IPC B64C 3/14, publ. 06/19/2003), made with lengthening λ = 9-11, narrowing η = 3-4.5, sweep χ _1/4 = 25-35 ° with front and rear influxes forming a profile formed as a spatial system based on the median surface, the wing inflow profile is formed with linear sections of the inserts in the bow and tail parts, which are located at the extremum points of the functions that describe the coordinates of the upper and lower wing surfaces, while linear sections of the inserts is equal to the length of the sag.

The prototype of the proposed technical solution is the wing of the aircraft (RF Patent No. 2600413. IPC В64С 3/10, publ. 10/20/2016), consisting of a center section, console and the necessary functional systems, made with lengthening λ = 7-11, narrowing η = 3-4.5 and sweep χ = 25-35 ° and containing supercritical profiles. The wing of the aircraft is characterized in that the leading edge of the wing is straight and without a front influx when viewed from above, the trailing edge is made with an influx, the radii of the toes of the wing sections referred to the local chord r _n. ≤0.7%, the middle line of the wing profiles in shape has a concave section in the range from the nose of the profile and up to 60% of the chord except for the end profiles of the wing and the limb in the tail section of the profile, the shape of the upper surface of the wing sections is characterized by a long section of small curvature in the section of 30-60% chords of the profile and the position of the maximum ordinate of the upper surface near 40% of the chord of the profile, the shape of the lower surface of the profile is made with a section of strong curvature (trimming) in the tail of the profile. The wing is formed from nine basic sections obtained using the three-stage aerodynamic design procedure, consisting of the initial geometry selection stage, the inverse problem solving stage and the multi-mode optimization stage, the wing surface is formed by constructing the spline surface in the first three sections, the next spline surface is constructed in the third , the fourth and fifth basic sections and is joined with the last section by a ruled section.

A common drawback of all the considered schemes is a large loss of aerodynamic quality with a Mach number M≥0.84 and, as a result, a significant decrease in fuel efficiency.

SUMMARY OF THE INVENTION

The problem solved by the claimed invention is to improve the technical, economic and technical and operational characteristics.

The technical result of the invention is the provision of a high cruising flight speed in the range of Mach numbers M = 0.84-0.9 while maintaining a high level of aerodynamic quality and fuel efficiency.

The solution of the problem and the technical result are achieved by the fact that in the swept wing, consisting of a center wing, console and made with lengthening λ = 7-11, narrowing η = 3-4.5 and sweep to χ = 35 ° and containing supercritical profiles, and the wing is formed of four piece segments and contains a leading edge, when viewed from above is straight and not having an influx, and the trailing edge is made with an influx and has four kink coordinates along the wing span, while the wing is made of supercritical profiles, relative thickness on profiles has a value of about 13-14% in the side section and decreases to 8-9% in the end section, monotonously decreasing in the section from 40% of the wing span to its end, the wing is designed with positive twist ε = 2-2.5 ° in the side section , end sections are designed with negative twist ε = -2 ÷ -3.6 °; the change in twist in scope has an almost linear decreasing character in the range from 25% to 100%.

Brief Description of the Drawings

Details, features, and advantages of the present invention follow from the following description of embodiments of the claimed wing of the aircraft using the drawings, which show:

In FIG. 1 - general view of the swept wing;

in FIG. 2 - a typical profile of the wing console;

in FIG. 3 - distribution of the relative maximum thickness along the wingspan;

in FIG. 4 - distribution of twist along the wingspan;

in FIG. 5 - load distribution according to wing span;

in FIG. 6 - change in the aerodynamic quality K and the fuel efficiency indicator K * M from the Mach number of the cruise flight.

The figures show the following positions in numbers:

1 - swept wing of the aircraft, 2 - center wing, 3 - wing console, 4 - leading edge of the wing, 5 - trailing edge of the wing, 6, 7, 8, 9 - fractures of the trailing edge of the wing, 10 - wing profile, 11 - decreasing law distribution of the thickness (s) of the sections according to the wingspan (z) of the wing; 12 is the distribution law of the geometric twist (ε) of the sections along the wingspan (z) of the wing.

Disclosure of Invention

The wing of the aircraft (1) (Fig. 1) consists of a center section (2) and a console (3), made with lengthening λ = 7 ÷ 11, narrowing η = 3 ÷ 4.5 and sweep to χ = 35 °, without inflow and kink along the leading edge (4) and with a multiple kink (6), (7), (8), (9) on the trailing edge (5) of the wing.

The wing sections are formed by the selected profiles (10) (Fig. 2). The wing is created on the basis of the spatial surface, including certain shapes of the midlines, the distribution law of relative thicknesses (11) (Fig. 3) with values of the order of 13-14% in the side section and decreases to 8 ÷ 9% in the end section, monotonously decreasing in the section from 40% of the wing span and to its end and the law of changing the geometric twist of each profile in the span (12) (Fig. 4) with positive twist ε = 2 ÷ 2.5 ° in the side section, end sections are designed with negative twist ε = -2 ÷ - 3.6 °, the law of the twist change in scope It has a substantially linear decreasing character in the range of 25% to 100% of the wingspan. All characteristics are found when solving optimization problems under given flight conditions.

The wing is formed over five basic sections obtained using the multi-stage aerodynamic design procedure, consisting of the initial geometry selection stage, the inverse problem solution stage and the multi-mode optimization stage, the wing surface is formed by constructing a spline surface.

The load distribution over the span differs from the elliptical (Fig. 5). This distribution allows you to weaken the wave crisis on the consoles at large Su, reduce bending moment and protect the end sections from premature failure.

Comparative studies of the proposed wing with the wing prototype were performed. The research results showed that the proposed wing of the aircraft compared to the prototype allows without any deterioration in aerodynamic performance to provide an additional increase in aerodynamic quality ΔKmakh ≈ 0.1 ÷ 0.6 in the range of Mach numbers M = 0.85 ÷ 0.9 and fuel efficiency ΔKmakh * M ≈ 0.1 ÷ 0.5 ( Fig. 6) and, as a result, reduced fuel consumption and increased flight safety.

Thus, it is possible to create an aircraft wing having the following advantages:

- high aerodynamic quality and fuel efficiency at subsonic flight speeds in the range of Mach numbers M _cruise = 0.84-0.9.

Claims (5)

The wing of the aircraft, consisting of a center section, a console and made with lengthening λ = 7-11, narrowing η = 3-4.5 and sweep to χ = 35 ° and containing supercritical profiles, characterized in that the wing is formed of four piecewise segments and contains a leading edge of the wing, when viewed from above, it is straight-line and does not have an influx, and the trailing edge is inflated and has four kink coordinates along the wing span, the relative thickness of the profiles is of the order of 13 ÷ 14% in the side section and decreases to 8 ÷ 9% in the end section, monotonously decreasing in the area from 40% of the wing span to its end, the wing is designed with positive swirl ε = 2 ÷ 2.5 ° in the side section, the end sections are designed with negative swirl ε = -2 ÷ -3.6 °, the law of change in twist in span is almost linear decreasing in the range from 25 to 100% of the wing span.

Images