CN1061005C - Anti-drag new installation for aeroplane wing tip - Google Patents

Abstract

The present invention relates to a novel device for the resistance reduction of the wing tips of a plane, which is composed of a vertical end plate (1), a gradually contractile air inlet pipe (2), a spraying pipe (3), a mixing chamber (4), a diffusing pipe (5), an air suction pipe (9), an air suction hole (11), a connection short pipe (12), a fastening connection body (6) and skin (10). When a plane flies at high speed, high pressure is generated at the tail of the air inlet pipe (2), and high-velocity airflow is sprayed out by the spraying pipe (3); negative pressure appears around the spout of the spraying pipe (3). Thus, when flowing along the horizontal sides of wing tips towards the upper wing surfaces, high pressure airflow on the lower wing surfaces can be sucked in the wing tips and is ejected to be discharged out of the tail of the plane so that induced resistance is reduced and is even eliminated, which greatly improves the combination properties of the plane.

Description

A kind of aeroplane wing tip injector

The present invention relates to the aircraft wing aerodynamic force and establish measure, specifically is a kind of aeroplane wing tip injector.

The aircraft that countries in the world are existing, when it flies, because the air-flow of wing lower surface is in high pressure, can be at left and right sides wing tip place link up along the low-pressure air current of horizontal side direction and upper surface of the airfoil, form from bottom to up mobile of wing tip place, the result, the lift of each section of wing descends on the one hand, on the other hand, forms eddy current at two wing tip places, make the air-flow of the wing of flowing through be subjected to the influence of vortex and produce purling, the result a kind of level that is referred to as induced drag occurs and is divided into X1.According to the 541st page of record of " Encyclopadia Sinica " " aerospace ", the induced drag of aircraft accounts for 40% of cruise drag, and at wingtip, as world name machine A340-200 space truck, the c-17 military transportation airplane, shown in Figure 20 4 passenger planes etc., winglet is set, installs vertical end plate simply additional, though also can reduce induced drag, but can only reduce about 20-35%, effect is unsatisfactory.Therefore, take new drag reduction measure for reducing the aircraft induced drag, to improving 1ift-drag ratio and thrust-weight ratio and economic performance when cruising, significant.

Purpose of the present invention provides a kind of aircraft induced drag that makes and reduces significantly, thereby can save energy resource consumption greatly, significantly improves its propulsion coefficient, increases the wingtip injector of aircraft capacity weight and maximum range.

For achieving the above object, the present invention is provided with the convergent shape air inlet pipe of the affixed jet pipe of its afterbody in the wingtip leading edge, and coexist on a line center line parallel with outside aspirate tube with inboard fuselage axis with jet pipe, blending box, diffuser pipe, closed at both ends before and after the aspirate tube, be evenly equipped with suction hole from front to back on its outside tube wall,, aspirate tube and the air-breathing inlet seal of blending box be communicated with being communicated with short tube, thus, constitute the aeroplane wing tip injector.Like this, during by high-speed flight, the air inlet pipe of convergent can make the jet-stream wind of jet pipe acquisition greater than velocity of sound to the punching press that air forms.Thus, the negative pressure of utilizing high speed jet around nozzle exit, to form, wing tip place horizontal side direction air-flow from bottom to top can be carried disconnected midway and it is sucked injection through the suction hole on the aspirate tube and be discharged to wing tail, make it unlikely arrival top airfoil, like this, the communication of wingtip horizontal side direction lower aerofoil high pressure draft and top airfoil low-pressure air current is about to destroy, and tip vortex has not existed, and induced drag is about to die-off and even eliminate.

Below, further describe structure of the present invention and advantage in conjunction with the embodiments:

Fig. 1 is an installation site of the present invention front elevation

Fig. 2 is an installation site of the present invention birds-eye view

Fig. 3 is the A-A cutaway view of Fig. 2

Fig. 4 is I-I cutaway view of Fig. 3

Fig. 5 is II-II cutaway view of Fig. 3

Fig. 6 is III-III cutaway view of Fig. 3

Among the figure

1 vertical end plate, 2 convergent shape air inlet pipes, 3 jet pipes

4 blending boxs, 5 diffuser pipes, 6 fastening connection pieces

The air-breathing inlet 8 blending box housings of 7 blending boxs 9 aspirate tubes

10 coverings, 11 suction holes 12 are communicated with short tube

From Fig. 1-6 as can be known, aeroplane wing tip injector of the present invention is equipped with the sweepback vertical end plate 1 that is called as winglet above wingtip, and vertical end plate 1 bottom line is fixed on the back with the aspirate tube 9 that is communicated with by 7 sealings of injection gas access of the inner injector of wingtip.Before wingtip, be provided with convergent shape air inlet pipe 2, this air inlet pipe 2 stretches out the wingtip leading edge, and its big footpath one end mouth of pipe opens wide to atmosphere, and converging transition is affixed with jet pipe 3, it is by the punching press effect that in the high-speed flight air is formed, air inlet pipe 2 afterbodys are obtained at a high speed, spray from jet pipe 3 with very high speed thereby promote air, and around spout, keep low pressure, air in the blending box 4 is attracted, mix, then by the diffuser pipe reduction of speed, boost, discharge tail at last.Wherein, convergent shape air inlet pipe 2, jet pipe 3, blending box 4, diffuser pipe 5 coexistence is on an axis parallel with inboard fuselage axis and outside aspirate tube 9, and outside atmosphere is led in the outlet of diffuser pipe 5.The aspirate tube 9 affixed with vertical end plate 1 bottom line, its rear and front end mouth of pipe is sealed by semicircle end socket, is evenly distributed with the suction hole 11 that leads to the outside passage portion atmosphere from front to back on the first half tube wall in its vertical end plate 1 bottom line outside.It is outwards affixed with aspirate tube 9 to be communicated with short tube 12, and with aspirate tube 9 and the air-breathing inlet 7 sealing connections of blending box.When the aircraft high-speed flight, injector is worked voluntarily, jet pipe 3 beginnings are jet, negative pressure just appears in the blending box 4, cause suction hole 11 inwardly air-breathing thus, and, be communicated with short tube 12, the air-breathing inlet 7 of blending box through aspirate tube 9, flow into blending box 4 continually, discharged wing tail by injection, like this, the high pressure draft of left and right sides wingtip lower surface is horizontal side direction flowing to the upper surface meiobar, just become flowing in the set suction hole 11 of the horizontal side direction of wing tip, reason thus, the wing tip vortex has not existed, and induced drag is promptly eliminated by containment.

Learn from equation of continuity, make subsonic or high pressure subsonic flow accelerate to velocity of sound even hyprsonic, will be with shrinking the shape pipeline, and to make jet pipe be to expand to put shape.

And the differential expression of continuity equation is $\frac{\mathrm{df}}{f}=\frac{\mathrm{dv}}{v}-\frac{\mathrm{dw}}{w}$ In the formula: f-basal area rice ²

V-specific volume rice ³/ kilogram

W-speed meter per second again because of

As can be seen from the above equation, when flying speed is subsonic or high subsonic speed, owing to shrink the effect of shape air inlet pipe 2, make the outlet of jet pipe 3 can obtain air-flow greater than velocity of sound, it is M＞1, at this moment, desire to make the injection efficient of jet pipe 3 further to improve, be that flow velocity increases, then df/f is for just, and jet pipe should be that shape is put in expansion, if the speed of aircraft itself is equal to or greater than velocity of sound, jet pipe 3 more should be to expand to put shape, but the import and export cross section ratio of convergent shape air inlet pipe 2 can correspondingly reduce, so that reduce its type resistance.

Equally, from the differential expression of continuity equation as can be seen, when air-flow after jet pipe 3 ejections, its flow velocity reduces, when promptly dw was negative value, if air-flow is still greater than velocity of sound, diffuser pipe 5 should be a convergent; Otherwise when air-flow during less than velocity of sound, then diffuser pipe is a flaring, and jet pipe of the present invention 3 exit flows generally make it greater than velocity of sound, so diffuser pipe 5 is scaling types.Consider the working environment and the installation site of diffuser pipe 5, its external form is constituted with the wing profile line style coincide that to reduce the type resistance, so its converging transition and throat bench section are circular, its expansion section of putting bench section then progressively carries out the transition to down curved oblate.

As mentioned above, the present invention adopts convergent shape air inlet pipe 2, be to guarantee to make jet pipe 3 to obtain velocity of sound even supersonic velocity air-flow, make the suction hole 11 of top, aspirate tube 9 outsides, wing tip edge obtain enough big suction, thereby guarantee that the lower aerofoil high pressure draft is unlikely to cross the wing tip edge and arrives top airfoil, form wing tip vortex and purling.Thereby require air inlet pipe 2, and jet pipe 3, diffuser pipe 5, blending box housing 8, aspirate tube 9 and fastening connection piece 6 usefulness intensity height, in light weight, ganoid composite material or aluminum alloy are made, and covering 11 usefulness aluminum alloy plate materials are made.

Adopt aeroplane wing tip injector of the present invention, it is installed on wing taper position, do not need to establish in addition engine installation, can in aircraft flight, work voluntarily, the induced drag source that accounts for cruise drag 40% is given injection eliminates, can make thus up to now and generally adopt high aspect ratio to bring wingheaviness to increase for reducing induced drag, new breakthrough appears in the existing technology that thrust-weight ratio reduces.Its reliable operation, the type resistance is minimum, makes easily, be convenient to implement, in case be applied to the straight wing and swept-back wing aircraft, and homemade fortune 8 series aircrafts and a homemade war machine, bomber will improve its lift efficiency and aerodynamic characteristics greatly, and its payload capability is increased substantially.

And another advantage of the present invention is: if cancellation vertical end plate 1 still has the special good performance of wingtip drag reduction.

Claims (2)

1. aeroplane wing tip injector, affixed at wingtip position and wing, it is characterized in that: convergent shape air inlet pipe (2) and jet pipe (3) that it is stretched out the wingtip leading edge and opened wide to atmosphere by big footpath one end, blending box (4), diffuser pipe (5) and aspirate tube (9) are formed, convergent shape air inlet pipe (2) path one end and jet pipe (3) are affixed, air inlet pipe (2) and jet pipe (3), blending box (4), diffuser pipe (5) coexistence is on an axis parallel with outside aspirate tube (9) with inboard fuselage axis, diffuser pipe (5) afterbody is connected to the wingtip trailing edge, outside atmosphere is led in its outlet, the mouth of pipe sealing of aspirate tube (9) rear and front end, be evenly distributed with the suction hole (11) that leads to outside atmosphere from front to back on its outside tube wall, connection short tube (12) is outside and aspirate tube (9) is affixed, and air-breathing inlet (7) sealing of aspirate tube (9) and inboard blending box (4) is communicated with.

2. aeroplane wing tip injector according to claim 1 is characterized in that: sweepback vertical end plate (1) bottom line is fixed on the back of aspirate tube (9).

Images