Short-, mid-range main line aircraft

FIELD: air transport.

SUBSTANCE: aircraft is made in proportion L/C=1/1, where L - hull length with diametre df≥4.18 m, C - wing span, which is formed with supercritical sections and made with the following parametres: aspect ratio λ≥1.5, sweep in line 1/4 chord χ≥26.5°, setting angle α0=3°, local transverse wing V angle ψ=5.37°, taper aspect η=3.928 and mean aerodynamic chord ba=3.479 m.

EFFECT: decreasing fuel consumption.

5 dwg, 3 tbl

 

The invention relates to the field of aviation.

Famous planes containing the fuselage, wing, control and stabilizing surfaces, two engines mounted on their respective consoles wing having a concave profile bottom surfaces (see Mikeladze, V.G., Titov V.M. "Basic geometric and aerodynamic characteristics of aircraft and missiles". The Handbook. - M.: Mashinostroenie, 1982).

Famous airplanes do not have the required flight performance, providing high reliable transportation and minimum operating costs, because we have the optimal proportion and a greater thickness of the wing.

The technical result, which is aimed invention is to reduce operating costs due to high flight characteristics of the aircraft.

This result is achieved in that the plane containing the fuselage, wing, control and stabilizing surfaces, two engines mounted on their respective consoles wing having a concave profile bottom surfaces, made in the proportion of L/C=1/1, where L is the length of the fuselage, C - span wing.

To achieve this ratio proposed the following technical solution. The plane is made with a wing of large aspect-ratio λ≥11,5.

The wing is made with the sweep line 1/4 chord) χ≥26.5°C, the angle α is=3°, narrowing η=3,928 and mean aerodynamic chord ba=3,479 m

Gondola engines are made of large diameter.

To use the engine nacelles large diameter wing made with a local angle transverse V-wing ψ=lower than the 5.37°.

To ensure high efficiency and aerodynamic properties of the wing transition from the linear area of its rear edge to the swept area is made in the form of a smooth continuous edge having the shape of the curve described by a third order spline f=cos(0,5·PI·x).

The wing is formed by supercritical profile with the following settings:

0.8
no profileZ (relative distance from a reference plane of the wing)C (relative thickness)φ° (angle)
I0.1140.1613
II0.20.1452.14
III0.2890.1291.4
IV0.3790.12
V0.470.11-0.04
VI0.60.101-0.625
VII0.750.10-1.25
VIII1.00.0975-2.65

To ensure a high level of comfort for passengers fuselage is made of circular cross section of diameter df≥4,18 m Such fuselage can accommodate 6 chairs in a row with a single pass between them with a higher level of comfort.

The invention is illustrated by drawings.

Figure 1 shows a General view of the plane, side view; figure 2 is a top view; figure 3 is a front view; figure 4 shows the wing with control surfaces; figure 5 - location of the respective profiles of the wing.

Aircraft short-medium range contains the fuselage 1, wing 2 with the flaps 3, 4 Aileron, air brakes, 5, 6 interceptors, slat 7, pylon 8, Kiel 9 rudder 10, the stabilizer 11 with the rudder 12, gondolas power unit 13, tricycle landing gear 14 and the cockpit 15.

For ware is high efficiency and aerodynamic properties of the wing 2, the transition from the linear area of its rear edge to the swept area is made in the form of a smooth continuous edge 16, having the shape of the curve described by a third order spline f=cos(0,5·PI·x).

The aircraft is a twin-engine airplane had with swept wings, performed on a normal aerodynamic scheme.

Wing highly mechanized (slats, flaps) with increased elongation λ≥11,5 through the use of composite materials in reinforcing elements.

Turbojet engines mounted on pylons under the wing.

The tail Assembly consists of a keel and deck horizontal tail.

The fuselage is made of circular cross section of diameter df≥4,18 m

The aircraft is cruising the number M=0.8, the maximum number M=0,82. Maximum glide for cruising flight mode M=0.8 andy=0,6 be Kmax=17,9.

Wing (wing) formed on 8 basic sections. The surface of the wing everywhere has a double curvature (spline) except for the bar area between the profiles 7 (z=13.5 m) and 8 (z=18 m). The wing is formed by supercritical profiles. The profile parameters are presented in table 1.

Table 1
no profileZ (relative distance from a reference plane of the wing)C (from oxytelinae thickness) φ° (angle)
I0.1140.1613
II0.20.1452.14
III0.2890.1291.4
IV0.3790.120.8
V0.470.11-0.04
VI0.60.101-0.625
VII0.750.10-1.25
VIII1.00.0975-2.65

Wing swept with a break on the rear edge and consists of 1 of the center section and the two consoles.

On each console mounted controls and mechanization of the wing: 4 ailerons, flaps 3, the slats 7, 6 interceptors, air brakes 5 and extinguishers lifting with the crystals.

Integrated optimization of supercritical wing with profiles of new generation and rational mechanization in terms of structural constraints, providing the required amount for the accommodation of fuel and the lowest possible mass of the structure, determined under other equal conditions, a significant increase in the efficiency of the aerodynamics of the aircraft relative to the aircraft of the same class.

The horizontal stabilizer arrow-shaped, trapezoidal shape in plan (angle transverse V=+6°) and consists of a stabilizer and rudder.

The adjustable stabilizer, installed in the fuselage at three sites: two in the rear of the site form the axis of rotation to a forward node connected to the screw mechanism, deflecting the stabilizer from the neutral position to the angles from +5° to -10°.

The design of the stabilizer consists of two consoles, narashima stacked along the axis of the plane.

Vertical tail trapezoidal shape in plan consists of the keel and rudder.

Table 2 shows the main geometrical data of the aircraft.

The wing area (on-line)S, m2112
WingspanLCR, m36
Mean aerodynamic chordba, m3,479
Extensionλ≥11,57
Narrowingη3,928
Sweep (1/4-chord line)χ, hail≥26,5
Wing setting angleα0, hail3,0
The diameter of the fuselagedfm≥4,18

In the present invention is implemented on a rational combination of high aerodynamic perfection, the use of new and improved structural materials, high-efficiency engines, digital fly-by-wire control system, new avionics, improved conditions of comfort of passengers and crew members, a high level of maintainability.

The aerodynamic configuration of the aircraft features a new high performance wing. Integrated optimization of supercritical wing with profiles and rational mechanization, providing the required volume for RA is a mix of fuel and the lowest possible weight design, provided a significant speed advantage in relation to well-known aircraft of the same class.

The design of the plane used a balanced combination of improved and new aluminum alloys and composite materials, allowing to optimize the design with regard to reliability and cost.

The plane containing the fuselage, wing, control and stabilizing surfaces, two engines mounted on their respective consoles wing having a concave profile bottom surfaces, characterized in that it is made in the ratio of L/C=1/1, where L is the length of the fuselage with a diameter of df≥4,18 m, C is the wing span, made with the following parameters: elongation λ≥11,5, sweep line 1/4 chord χ≥26.5°C, the angle α0=3°, the local angle of transverse V wing ψ=lower than the 5.37°, narrowing η=3,928, mean aerodynamic chord ba=3,479 m and educated supercritical profiles with the following parameters:

no profileZ (relative distance from a reference plane of the wing)C (relative thickness)φ° (angle)
I0.1140.1613
II0.20.1452.14
III0.2890.1291.4
IV0.3790.120.8
V0.470.11-0.04
VI0.60.101-0.625
VII0.750.10-1.25
VIII1.00.0975-2.65



 

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