CN1353070A - Cross-section structure of flying vehicle's wing for generating greater life force - Google Patents

Abstract

An improved wing of flying vehicle for generating greater life force features that the highest point of its top surface is moved to close to the wing tip, the top surface is inclined backward, the bottom surface of the wing is similar to wide-angle-triangle, that is, its front half is inclined backward and its rear half is near to horizontal, and dual-layer back flap can be selectively used.

Description

A kind of aircraft wing cross-section structure that produces bigger lift

The present invention relates to a kind of cross-section structure of aircraft wing

Wing profile for aircraft, the type that now has been suggested or has been used is more, the topmost low speed aerofoil profile that profile features such as flat or up-bow is recessed are arranged under the up-bow, and double-arc shape, diamond pattern, half diamond pattern, go some other different structure types such as ridge diamond pattern, spliting type, although the morphosis feature of these different wing sections structure sections has nothing in common with each other, but its common feature is to use height commonly used, common speed, load-carrying commonly used to put down when flying, the vertex of upper surface of the airfoil is general relatively near wing middle part direction, and not at the wing tip position of wing.

Target of the present invention will propose exactly that a kind of airfoil lift is higher, the wing carries the wing profile structure better than bigger and various performances.

In order to realize above target, the wing profile structure that the present invention proposes is, the upper surface of the airfoil structure is relatively mild low horizontal curve shape, and with height commonly used, speed, load-carrying is put down when flying, aerofoil surface is generally with highly maximum near the anterior wing tip position, highly descend backward, lower surface then is a class wide-angle trigonometric expression curve-like, wherein the first half lower surface is streamiline surface or the planarea that extends to the oblique back lower place, the latter half lower surface then is to be nearly horizontal surface or the very little curvilinear plane of sinuousness up and down, and to extend rearward to wing rear portion wing tail crossing with upper surface always.In addition for preventing that aircraft produces stall when widening the angle of attack, the rear portion of wing of the present invention, also can design a kind of structure such as double-deck wing flap, slat of self contained function separately, so that when aircraft rises with the big angle of attack, turn over the last wing flap of wing tail suitably, thereby the negative-pressure air-flow layer that makes upper surface of the airfoil can be unlikely to blocked up, and produces very strong involute forward eddy current, so just can prevent or alleviate stall and endanger.

This wing increases the principle and the frame mode of lift in addition, equally also can be applicable to the transformation to existing aircraft fuselage structure.With fuselage by present being generally under flat up-bow mode, change down bow into and go up flat or the bottom is arched manyly more than top, and suitably revise vertical section simultaneously when reducing the fuselage height and strengthening fuselage width, can greatly improve lift especially.

The present invention is positioned at all air molecules in wing the place ahead when adopting above method to make, all can constantly move forward the suppressing action of process owing to wing, and when improving constantly density pressure, along the constantly mobile backward (see figure 3) of wing lower surface.Much higher times big lifting application force when thereby generation acts on the horizontal lower aerofoil of wing more than normal barometric pressure to wing, so this wing lower stream of airflow is definitely much bigger than the various aerofoil profiles that now proposed to the lifting power of wing.And this wing top is owing to begin just constantly reduction of height from wing tip, and what flow through backward is not have to obtain as existing wing the lower pressure air that the supercharging density is handled, and it can constantly reduce pressure more low than normal pressure when the stream of back, can form on the negative pressure at whole upper surface of the airfoil so again and inhale application force, and action intensity is also stronger than various existing nature aerofoil profiles, naturally its whole lift feature will be to be higher than existing other aerofoil profile far away, if the rear portion at this wing is aided with double-deck trailing edge flap again, endanger so that eliminate or alleviate stall, its flight in-use performance is just more outstanding.The increase lift principle that I here mention, though it is different fully with some traditional theories, but in fact should more meet objective reality, its reason key be since people when analyzing wing and produce the principle of lift, tended to ignore the effect of the angle of attack that wing must exist when producing lift, and consider time spent of doing of the angle of attack, the formation of lift is just more reasonable with the principle of narrating in this patent.

Below just in conjunction with the accompanying drawings to the feature of wing of the present invention and with implement relevant issues and once discuss.

In the accompanying drawing Fig. 1 be wing tip top have one very this wing structure Fig. 2 of small embossment be that another kind of sectional structure chart Fig. 3 of this wing is up and down density of air, distribution of pressure and flow performance figure of wing (shows density and pressure height when streamline is intensive, otherwise density and pressure decay)

The first half of this wing lower surface, can be the planarea that extends to the oblique back lower place, also streamline face, and the embroidery of its streamiline surface and the inclination angle of planarea, can be with the varying in size and show difference of aircraft common speed, generally speaking inclination angle and curve camber should increase with design speed and reduce.

The lower surface that this wing is latter half of, can be aircraft with common speed, when height flat flies, be planarea that nearly horizontal linear extends or wiggle face down, also the curvilinear plane of rear portion K/UP.In these three kinds of modes, in the time of may flying with the normal fast Chang Gaoping of aircraft, during for nearly horizontal linear face, practicality is the strongest, because go up when bending when latter half of, but though drag reduction, but the wing lifting force also subtracts greatly simultaneously, and the rear portion is when constantly curved down, and then frontal resistance increases greatly, when having only latter half of nearly level, having to be beneficial to promptly increases lifting force greatly and does not increase resistance again strongly.

The degree of being bent downwardly of upper surface of the airfoil of the present invention, can be constant always after arrive first, also but forebody is less, latter half of bigger, and the wing tip position of wing front upper surface, the also slightly less lifting of rear upper surface relatively, form less step-like as Fig. 1, step-like anterior lifting like this, as crooked less and rear portion bending declines by a big margin and mutually combines with front upper surface, then more help upper surface of the airfoil when increasing negative-pressure sucking, alleviate the stall harm when big state of angle of attack.

Two wing flaps up and down at wing of the present invention rear portion, structures such as slat, can use and comprise wing flap, any structure array modes such as slat, wherein the lower rear edge wing flap is made as the Fu Shi wing flap to the upper back edge wing flap as being made as coventional type, may be more favourable, so when wanting the fast big angle of attack to rise, bottom Fu Shi wing flap is transferred to apply a upwards application force, and the top wing flap oppositely upwarps to prevent the burbling of top airfoil, then there is the air flow stream mistake in slit between last wing flap and the following Fu Shi wing flap, form negative pressure between two wing flaps up and down to prevent that triangular shape is open, so just can increase and not cause stall under the flying angle condition in certain amplitude, the benefit of trailing edge flap can have been given full play to again, particularly use the front and rear edge wing flap at the same time, and when upwarping droope snoot in order to increase pullover flight intensity, wing flap upwarps and causes that to preventing upper surface of the airfoil generation burbling stall is huge with regard to acting on especially on this trailing edge.In addition, under the wing flap condition, wing flap is turned over on common in top before and after using at the same time, and the rear portion also is a kind of better method with the openable slat.

Claims (4)

1, a kind of aircraft wing cross-section structure that produces bigger lift, it is characterized in that, when aircraft with the most frequently used speed, highly, load-carrying is put down when flying, the upper surface of wing is generally the highest with near the position height wing tip, from wing tip backward to wing tail, see on the whole highly for being generally the less relatively continuous decline of amplitude, the wing lower surface then is a class wide-angle triangular shape curvilinear style structure, its forebody is straight line or the stream line pattern that extends to the oblique back lower place from wing tip, transfer to backward again with nearly straight horizontal wire up and down the crooked curve-like in side extend to wing tail, intersect with top airfoil is terminal.Thereby form a kind of wide-angle triangular shape profile morphological characteristics of similar opened plication on the whole.

2, wing structure as claimed in claim 1 is characterized in that the trailing edge at wing rear portion having two layers of structures such as wing flap, aileron or slat up and down of self-movement separately.

3, wing structure as claimed in claim 1 is characterized in that the wing rear portion has only structures such as an independent cover trailing edge flap, slat.

4, as claim 1,2,3 described wing structures, the wing tip position that it is characterized in that wing top, relatively the rear portion aerofoil has a very little step to upper process, and the amplitude of sedimentation is less gradually backward for forebody top airfoil thereafter, and latter half of then sedimentation amplitude increases.

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