CN205738056U - A kind of aerodynamic arrangement of the big aircraft of strategy - Google Patents

Abstract

This utility model belongs to technical field of aerospace Flight Vehicle Design direction, mainly solves the problem that the lift-drag ratio of the big aircraft of strategy is relatively low.This utility model relates to the aerodynamic arrangement of the big aircraft of a kind of strategy, aerodynamic arrangement including fuselage, wing, horizontal tail, vertical tail and electromotor, it is characterized in that: the aerodynamic arrangement of expanded letter fuselage, the aerodynamic arrangement of the high aspect ratio wing with winglet, the aerodynamic arrangement of lift horizontal tail, the aerodynamic arrangement of double fins flare, and the aerodynamic arrangement that fanjet installation is under the wings of an airplane.The aerodynamic arrangement of the big aircraft of described strategy makes big aircraft possess, and lift-drag ratio property high, controllable is good and the advantage of good stability.

Description

Aerodynamic layout of a strategic large aircraft

technical field

The utility model relates to an aerodynamic layout of a strategic large aircraft, which belongs to the field of aviation technology.

Background technique

The strategic large aircraft is a supporting platform for multi-purpose aircraft, which has various development prospects for civil, military and aerospace applications. Russia's large strategic aircraft include "Il-76", Ukraine's strategic large aircraft include "An-124" and "An-225", and the United States' strategic large aircraft include "C-17", "C-5", " "Boeing-747" and "Boeing-777", etc., Europe's strategic large aircraft has "A-380". China is very concerned about the world's strategic large aircraft. The research and development of strategic large aircraft has just started. Compared with the strategic large aircraft of the United States, Europe, Russia and Ukraine, there is a certain gap in technology.

At present, the aerodynamic layout of large strategic aircraft generally belongs to the normal layout. Under the current technical conditions, when the aircraft adopts a normal aerodynamic layout, the usual aerodynamic focus is behind the center of gravity of the aircraft. When the aircraft is in level flight and trimmed, the lift of the aircraft produces a nose-down moment, and the negative lift of the horizontal tail produces a nose-up moment. The two balance each other , the pitch damping is large, and the longitudinal stability of the aircraft is good. However, in this way, the horizontal tail provides negative lift when the aircraft is trimmed in level flight, which contributes negatively to the lift of the aircraft, the lift of the aircraft is lost, and the lift-drag ratio is relatively low.

Utility model content

The purpose of the utility model is to provide an aerodynamic layout of a strategic large aircraft, which enables the strategic large aircraft to have excellent lift-drag characteristics, maneuverability and stability.

In order to achieve the above object, the technical scheme adopted by the utility model is:

The aerodynamic layout of a large strategic aircraft, including the aerodynamic layout of the fuselage, wings, horizontal tail, vertical tail and engine, is characterized in that: the aerodynamic layout of the wide-body fuselage, the large aspect ratio wing with winglets The aerodynamic layout of the lift flat tail, the aerodynamic layout of the twin vertical tails and the aerodynamic layout of the camber, and the aerodynamic layout of the turbofan engine installed under the wing.

As a further improvement of the utility model, the specific structure of the aerodynamic layout of the wide-body fuselage is: the fairing hatch (1) of the nose (2) is smooth and excessive when closed, and the cross-section of the middle fuselage (3) The outline of the fuselage is smooth, and the tail of the fuselage (4) is smooth and excessively reduced in order to reduce resistance. There is a fairing (5) for the landing gear under the middle fuselage, the nose (2), the middle fuselage (3), and the tail of the fuselage (4) form described wide-body fuselage together.

As a further improvement of the present utility model, the specific structure of the aerodynamic layout of the large aspect ratio wing with winglet (8) is: root wing (6), middle wing (7), wing The pointed winglets (8) form the described large aspect ratio wing together, and the large aspect ratio wing is an upper single wing, lower reverse, and swept back; the aspect ratio of the large aspect ratio wing is 5.2～6.2, The anhedral angle is 2°～4°, the installation angle is 3°～4°; the sweep angle of the leading edge of the wing root is 35°～45°, and the sweep angle of the trailing edge of the wing root is 0°; The sweep angle of the leading edge of the wing is 35°～45°, and the sweep angle of the trailing edge of the middle wing is 21°～31°; 15%; the trailing edge of the large-aspect-ratio wing has flaps (9), outer flaps (10), and ailerons (11); the ratio of the area of the flaps (9) to the area of the large-aspect-ratio wing is 3 % to 5%, the ratio of the area of the outer flap (9) to the area of the wing with a large aspect ratio is 5% to 8%, the ratio of the area of the aileron (11) to the area of the wing with a large aspect ratio is 10% to 12 %.

As a further improvement of the present utility model, the specific structure of the aerodynamic layout of the lift flat tail is: the lift flat tail (12) is a trapezoidal wing, reversed, and swept back, and has a segmented elevator (13); 12) The dihedral angle is 7°～10°, the installation angle is 3°～5°; the leading edge sweep angle of the lift flat tail (12) is 40°～45°, the trailing edge sweep angle is 28°～32° °; the aspect ratio of the lift flat tail (12) is 2.8 to 3.5; the ratio of the area of the segmented elevator (13) to the lift flat tail (12) area is 18% to 25%.

As a further improvement of the utility model, the specific structure of the aerodynamic layout of the double vertical tail camber is as follows: the double vertical tail camber angle is 15°～25°, and the vertical tail is divided into the upper vertical tail (14) and the lower vertical tail by the lift flat tail The vertical tail (15) has two sections with a segmented linkage rudder (16); the upper vertical tail (14) and the lower vertical tail (15) are both trapezoidal, and the airfoil of the vertical tail is a symmetrical airfoil; the segmented linkage rudder (16) The ratio of the area to the vertical tail area is 20% to 25%.

As a further improvement of the present utility model, the specific structure of the aerodynamic layout in which the turbofan engines are installed under the wings is: under the left and right wings with large aspect ratios, two turbofan engines (18) are suspended symmetrically, The outer wall nacelle (19) of turbofan engine (18) is suspended by pylon (17) and stretches out forward.

Compared with the prior art, the advantages of the utility model and the beneficial effects obtained are:

First, the lift-to-drag ratio is high. When the aircraft is trimmed in level flight, since the wings with large aspect ratio provide lift and the lift stabilizer provides positive lift, the lift is not lost, and because the fuselage adopts drag reduction measures, the resistance is small, so the lift-to-drag ratio of strategic large aircraft is high.

Second, good maneuverability. There are segmented elevators for pitch control, segmented linkage rudders for yaw control, ailerons for roll control, and flaps and outer flaps for increasing lift. So the maneuverability of the plane is good.

Third, good stability. The aerodynamic focus of the large strategic aircraft is in front of the center of gravity of the aircraft, the nose-up moment generated by the lift of the wing with a large aspect ratio on the center of gravity of the large strategic aircraft, and the nose-down moment generated by the positive lift of the lift and flat tail on the center of gravity of the large strategic aircraft are balanced together. The pitching damping is large, so the longitudinal stability of the strategic large aircraft is good; because the strategic large aircraft has an upper single wing, a large aspect ratio, and a downward reversal, the strategic large aircraft has good lateral stability; because the large aspect ratio wing has The wingtips are small, and the large aircraft has double vertical tails with outward tilt, so the heading stability of the strategic large aircraft is good.

Description of drawings

Fig. 1 is a perspective view of the utility model.

Fig. 2 is the front view of the utility model.

Fig. 3 is the rear view of the utility model.

Fig. 4 is a left view of the utility model.

Fig. 5 is a top view of the utility model.

Fig. 6 is a bottom view of the utility model.

Fig. 7 is the lift coefficient characteristic curve of the utility model.

Fig. 8 is the drag coefficient characteristic curve of the utility model.

Fig. 9 is the lift-to-drag ratio characteristic curve of the utility model.

In the accompanying drawings, 1 is the fairing hatch; 2 is the nose; 3 is the middle fuselage; 4 is the tail of the fuselage; 5 is the fairing of the landing gear; 6 is the root wing; 7 is the middle wing; 8 9 is the winglet; 9 is the flap; 10 is the outer flap; 11 is the aileron; 12 is the lift horizontal tail; 13 is the segmented elevator; 14 is the upper vertical tail; 15 is the lower vertical tail; 16 is the segment Linkage rudder; 17 is a pylon; 18 is a turbofan engine; 19 is an outer wall nacelle.

detailed description

The utility model will be further described in detail below in conjunction with accompanying drawings 1 to 9 and embodiments.

An embodiment of the aerodynamic layout of a strategic large aircraft, including the aerodynamic layout of the fuselage, wings, horizontal tail, vertical tail and engine, characterized in that: the aerodynamic layout of the wide-body fuselage, the large span of the winglet Compared with the aerodynamic layout of the wing, the aerodynamic layout of the lifting horizontal tail, the aerodynamic layout of the double vertical tail and the outward tilt, and the aerodynamic layout of the turbofan engine installed under the wing; the length of the strategic large aircraft is 84.8m, and the height is 18.3m. The wingspan is 88.4m.

As a further improvement of the embodiment of the present invention, the aerodynamic layout of the wide-body fuselage is: the fairing hatch (1) of the nose (2) is smooth and excessive when closed, and the cross-section of the middle fuselage (3) is The outline is smooth, and the tail of the fuselage (4) is smooth and excessively reduced in order to reduce resistance. There is a landing gear fairing (5) under the middle fuselage, the nose (2), the middle fuselage (3), and the tail of the fuselage ( 4) form the wide-body fuselage together.

As a further improvement of the embodiment of the utility model, the aerodynamic layout of the large aspect ratio wing with winglet (8) is: root wing (6), middle wing (7), wingtip Winglet (8) forms described large-aspect-ratio wing together, and large-aspect-ratio wing is upper single-wing, lower reverse, swept back; The aspect ratio of large-aspect-ratio wing is 5.2, lower anhedral angle is 2°, and the installation angle is 3°; the sweep angle of the leading edge of the wing root is 35°, and the sweep angle of the trailing edge of the wing root is 0°; the leading edge sweep angle of the middle wing is 35°, and the sweep angle of the middle wing The trailing edge sweep angle of the wing is 21°; the ratio of the area of the winglet (8) at the tip of the wing to the area of the wing with a large aspect ratio is 11%; the trailing edge of the wing with a large aspect ratio has flaps (9), outer flaps Wing (10), aileron (11); the ratio of flap (9) area and large aspect ratio wing area is 3%, and the ratio of outer flap (9) area and large aspect ratio wing area is 5 %, the ratio of the aileron (11) area to the area of the large aspect ratio wing is 10%; the wing root chord length of the large aspect ratio wing is 21.2m, the wing center chord length is 13.638m, and the wing tip chord length is 3.6m, winglet chord length is 1.5m; large aspect ratio wing airfoil is AH-21.

As a further improvement of the embodiment of the present utility model, the aerodynamic layout of the lift flat tail is as follows: the lift flat tail (12) is a trapezoidal wing, reversed, and swept back, and has a segmented elevator (13); the lift flat tail (12) ) is 7 °, and the installation angle is 3 °; the leading edge sweep angle of the lift flat tail (12) is 40 °, and the trailing edge sweep angle is 28 °; the aspect ratio of the lift flat tail (12) is 2.8 The ratio of the segmented elevator (13) area and the lift flat tail (12) area is 18%; the root chord length of the lift flat tail is 11.2m, and the lift flat tail tip chord length is 6.2m; the lift flat tail airfoil type is AG10.

As a further improvement of the embodiment of the present utility model, the aerodynamic layout of the double vertical tail camber is: the double vertical tail camber angle is 15°, and the vertical tail is divided into an upper vertical tail (14) and a lower vertical tail (15°) by a lift flat tail. ) two sections, and with the segment linkage rudder (16); the upper vertical tail (14), the lower vertical tail (15) are both trapezoidal, and the airfoil of the vertical tail is a symmetrical airfoil; the segment linkage rudder (16) area The ratio to the area of the vertical tail is 20%; the chord length of the upper wing of the vertical tail is 3.816m, the chord length of the middle wing of the vertical tail is 9m, and the chord length of the lower wing of the vertical tail is 3.28m; the airfoil type of the vertical tail is NA006T.

As a further improvement of the embodiment of the present utility model, the aerodynamic layout in which the turbofan engines are installed under the wings is as follows: two turbofan engines (18) are hung symmetrically under the left and right wings with large aspect ratios, and the turbofan engines (18) are placed symmetrically. The outer wall nacelle (19) of the fan motor (18) is suspended by a pylon (17) and stretches out forward.

As shown in Fig. 7, Fig. 8 and Fig. 9, CFD calculation software is used to calculate that it has good aerodynamic characteristics at high Reynolds numbers, and its lift-to-drag ratio is large in the range of small angles of attack. The angle of attack is relatively large, and there is still no stall phenomenon when the angle of attack is 12°.

The above-mentioned implementations are only preferred embodiments of the present utility model, rather than an exhaustive list of feasible implementations of the present utility model. For those skilled in the art, any obvious changes made to it without departing from the principle and spirit of the utility model shall be considered to be included in the protection scope of the claims of the utility model. Therefore, the protection scope of the present utility model should be based on the protection scope of the claims.

Claims (6)

1. an aerodynamic arrangement for the big aircraft of strategy, including the aerodynamic arrangement of fuselage, wing, horizontal tail, vertical tail and electromotor, its It is characterised by: the aerodynamic arrangement of expanded letter fuselage, the aerodynamic arrangement of the high aspect ratio wing of band winglet, lift horizontal tail pneumatic Aerodynamic arrangement under the wings of an airplane installed by layout, the aerodynamic arrangement of double fins flare, and fanjet.

The aerodynamic arrangement of the big aircraft of a kind of strategy the most according to claim 1, it is characterised in that the gas of described expanded letter fuselage The concrete structure of dynamic layout is: trousers hatch door (1) the Guan Bi time degree of slipping over of head (2), outside the cross section of middle fuselage (3) Shape contour smoothing, afterbody (4) smooth excessively reduces, with landing gear trousers below middle fuselage to reduce resistance (5), head (2), middle fuselage (3), afterbody (4) form described expanded letter fuselage together.

The aerodynamic arrangement of the big aircraft of a kind of strategy the most according to claim 1, it is characterised in that described band winglet (8) concrete structure of high aspect ratio wing aerodynamic arrangement is: wing root wing (6), middle wing (7), winglet (8) group together High aspect ratio wing described in one-tenth, high aspect ratio wing is high mounted wing, lower anti-, sweepback；The aspect ratio of high aspect ratio wing is 5.2 ～6.2, inverted diherdral be 2 °～4 °, established angle be 3 °～4 °；Wing root leading edge of a wing angle of sweep is 35 °～45 °, wing root trailing edge Angle of sweep is 0 °；Middle leading edge of a wing angle of sweep is 35 °～45 °, and middle trailing edge angle of sweep is 21 °～31 °；Winglet (8) Area and high aspect ratio wing area ratio are 11%～15%；High aspect ratio wing trailing edge is with wing flap (9), outer wing flap (10), aileron (11)；Wing flap (9) area and high aspect ratio wing area ratio are 3%～5%, outer wing flap (9) area and great Zhan String is 5%～8% than the ratio of wing area, and aileron (11) area and high aspect ratio wing area ratio are 10%～12%.

The aerodynamic arrangement of the big aircraft of a kind of strategy the most according to claim 1, it is characterised in that described lift horizontal tail The concrete structure of aerodynamic arrangement is: lift horizontal tail (12) is tapered airfoil, upper anti-, sweepback, and with stagewise elevator (13)；Rise The upper counterangle of power horizontal tail (12) is 7 °～10 °, and established angle is 3 °～5 °；The leading edge sweep of lift horizontal tail (12) be 40 °～ 45 °, trailing sweep is 28 °～32 °；The aspect ratio of lift horizontal tail (12) is 2.8～3.5；Stagewise elevator (13) area It is 18%～25% with lift horizontal tail (12) area ratio.

The aerodynamic arrangement of the big aircraft of a kind of strategy the most according to claim 1, it is characterised in that described double fins flare The concrete structure of aerodynamic arrangement be: double fins camber angle is 15 °～25 °, vertical tail by lift horizontal tail be divided into upper vertical tail (14) and Lower vertical tail (15) two sections, and with segmentation linkage rudder (16)；Upper vertical tail (14), lower vertical tail (15) are trapezoidal, vertical tail Aerofoil profile is symmetrical airfoil；Segmentation linkage rudder (16) area is 20%～25% with vertical tail area ratio.

The aerodynamic arrangement of the big aircraft of a kind of strategy the most according to claim 1, it is characterised in that described fanjet The concrete structure installing aerodynamic arrangement under the wings of an airplane is: under left and right high aspect ratio wing, symmetry respectively hangs 2 turbofans and sends out Motivation (18), the outer wall nacelle (19) of fanjet (18) is hung by hanger (17) and is forward extended out.