CN101941523A

CN101941523A - Adjustable aerofoil and double-body aircraft aerofoil layout scheme thereof

Info

Publication number: CN101941523A
Application number: CN2010102515042A
Authority: CN
Inventors: 吴新保
Original assignee: Individual
Current assignee: Individual
Priority date: 2010-08-12
Filing date: 2010-08-12
Publication date: 2011-01-12

Abstract

The invention discloses an adjustable aerofoil and a double-body aircraft aerofoil layout scheme thereof. The double-body aircraft aerofoil layout scheme is as follows: two fuselages are arranged side by side and the insides of the two fuselages are connected through a rectangular main aerofoil. The used rectangular main aerofoil is characterized in that the outer flexible aerofoil skin is supported by a plurality of inner rollers which can rotate to drive the flexible aerofoil skin, thus initiatively increasing the relative speed between the upper and lower surfaces of the aerofoil and the air flow; and the positions of the rollers can be adjusted to change the airfoil profile and adapt to different flight speeds. Compared with the existing fixed wing aircraft, the aircraft with the adjustable aerofoils of the invention has higher weight capacity and smaller floor space and has less resistance in the high-speed flight; and during the low-speed flight, the aircraft has the advantages of lower level flight speed, safer ultra-short take-off and landing and the like.

Description

The binary aircraft wing placement scheme of adjustable aerofoil profile wing and application thereof

Affiliated technical field

The present invention relates to aviation field, the wing that is specially a kind of later-model adjustable aerofoil profile with and the binary aircraft wing placement scheme used.

Technical background

As everyone knows, the principle that fixed wing aircraft produces lift is that the top airfoil of wing protrudes, and lower aerofoil is flat slightly, thereby when in air, streaking, in the passive utilization. the air-flow velocity difference of lower aerofoil produces lift.Known fixed wing aircraft generally has the branch of subsonic aircraft and supersonic plane, and subsonic aircraft divides dopey and high-subsonic aircraft again.The thickness of the aerofoil profile of existing various aircrafts is different in the residing position of wing chord, the maximum ga(u)ge position in subsonic aircraft wing section is about the place of 25-40% in the distance of leading edge and trailing edge, and the maximum ga(u)ge position in supersonic plane wing section is about the place of 30-50% in leading edge and trailing edge distance.The wing profile of subsonic aircraft is generally the straight wing or swept wing, and its wing thickness is big, the aspect ratio height, the lift of generation is big, the road-holding property of aircraft is also strong, but aircraft flight speed when high the resistance of its generation also big, limited the flying speed of aircraft; The supersonic plane wing of using swept wing or delta wing is thinner, aspect ratio is less relatively, though resistance is smaller during flight, help supersonic flight, reduced the manipulative capability of aircraft, the lift that its wing produces is also little, during low-speed operations, they can not bear very big capacity weight, and the efficient of aircraft is not high, when field takeoff and landing, generally also need very long runway, need consume too many fuel when stagnating sky.Can change the swing-wing layout that wing aircraft has awing, do not change the minimal thickness of wing, make aircraft under given speed, obtain better performance also, yet, realize these move needed mechanical device not only complexity but also heaviness of wing, these devices also can take big quantity space simultaneously, lower efficiency and capacity weight.Big many of bar pressure during aircraft flight around the suffered pressure ratio of the leading edge of a wing, because the sharp-pointed leading edge of a wing causes the situation of burbling easily, the design of the leading edge of a wing generally all is circular, has caused the powerful resistance of forward movement.Also will there be horizontal tail the both sides of airframe except that host wing, horizontal tail is no matter at the front portion or the afterbody of fuselage, all with the air-flow mutual interference mutually of host wing, increase interference drag.No matter the aircraft of those a kind of wing configurations, all be that fuselage is in the centre, two lateral surfaces of fuselage are host wing and tailplane, and the induced drag in the process of flight is bigger: it is big that the aircraft that aspect ratio is bigger is compared the little airplane ascensional force of aspect ratio. the efficient higher position is strong proof.

Summary of the invention

I invent a kind of adjustable aerofoil profile and have the novel wing of the increase lift unit except that wing flap, and be applied to a kind of wing configurations scheme of type aircraft, wing can be adjusted to the higher aerofoil profile of efficient when this type aircraft took off, and can start the device that increases lift, actv. increases the difference of pressure of wing upper and lower surface, and the adjusting wing flap, help short can regulating or close the device that it increases lift after taking off as required apart from rolling start.Flying speed reaches high subsonic speed, when needing to reduce the resistance of wing, wing can be adjusted to relatively thinner low resistance aerofoil profile again, makes the aircraft ratio be easier to break through sound barrier, carries out supersonic cruise.It is sharp-pointed that the leading edge place of wing can also increase the single raise leading edge, and the triangle droope snoot that can also move forward and backward and rotate reduces the powerful pressure that the circular leading edge of a wing brings, and is convenient to wing and breaks through shock wave and reduce aircraft powerful resistance when advancing.

Wing of the present invention and fuselage are such layouts: have two fuselages and be arranged side by side, adopt jet engine at afterbody on the fuselage general design, belly air inlet and advanced fly-by-wire, the inboard of two fuselages is connected by the host wing of a rectangle, host wing is used a kind of subsonic airfoil or supersonic airfoil and increase lift unit except that wing flap of can being adjusted to the need, the lateral surface of fuselage tail end and top a slice tailplane and a slice vertical tail arranged respectively, each alighting gear before and after each fuselage of aircraft, have four alighting gears, even aircraft landing is at a slight tilt when landing and also is unlikely to wing tip and contacts to earth and lead to a disaster.Whole airplane layout novelty, simple and clear.And the bright spot of innovation is middle rectangular wing, and its outside is the flexible machine of tubular

Wing covering, covering will be used has flexibility, air-tightness and very high pull resistance. heat-resisting. the cloth composite material of resistance to cold, wing cover is by in-to-in load-bearing cylinder and transfer the aerofoil profile cylinder that it is propped up, promptly can increase lift and can regulate aerofoil profile as required again, being used of wing flap before and after adding makes aircraft not only have subsonic aircraft short field take-off even advantage of can very-short-reach taking off and littler level speed, and be safer during landing; Also have supersonic plane and break through sound barrier easily, the lower advantage of resistance ratios during supersonic cruise, and the burbling situation of top airfoil when being more prone to control the big angle of attack have improved the manipulative capability of aircraft.

Description of drawings

Fig. 1 is a stereo appearance figure of the present invention; Fig. 2 is a birds-eye view of the present invention; Fig. 3 is a front elevation of the present invention; Fig. 4. Fig. 5. Fig. 6. Fig. 7 is a structural representation of the present invention; Wherein Fig. 6 be on the fuselage with the simplified schematic diagram of wing junction; Fig. 7. Fig. 8. Fig. 9. Figure 10 is accent aerofoil profile effect scheme drawing of the present invention.

In the drawings: 1 fuselage, 2 host wings, 3 tailplanes, 4 vertical tails, 5 spars, 6 flexible steel wires, load-bearing cylinder before 7,71 back load-bearing cylinders, 8 transfer aerofoil profile cylinder A, 81 transfer aerofoil profile cylinder B, and 82 transfer aerofoil profile cylinder C, 9 flexible wing coverings, 10 triangle droope snoots, 11 trailing edge flaps, 12 preceding load-bearing cylinder mounting holes, 13 back load-bearing cylinder and trailing edge flap mounting holes, 14 transfer aerofoil profile cylinder mounting hole, 15 triangle droope snoot mounting holes.

The specific embodiment:

As Fig. 1, Fig. 2, shown in Figure 3: new aircraft wing configurations scheme, two fuselages that are arranged side by side 1 are arranged, adopt jet engine to advance at fuselage 1 afterbody on the general design, the belly air inlet, fly-by-wire with the advanced person, the position on the lower side of the medial surface of two fuselages 1 provides the rectangle host wing 2 of lift to connect by one, and the top of two fuselages 1 is held mutually with flexible steel wire 6, to prevent of the laterally separation of two fuselages owing to gravity, rectangle host wing 2 will provide lift for two fuselages 1, wing chord is very long, and two strings of rectangle host wing 2 all link to each other with fuselage 1, although aspect ratio is very little, owing to there is not the wing tip that exposes, so also can reduce induced drag by actv., because two fuselages are at a distance of distant, under the situation that prevents contingency, when having only the engine operation of remaining, the aircraft rotation that causes, can allow the outward-dipping certain angle of spout of two driving engines, use a driving engine just can promote aircraft and go ahead sideling, rather than rotation, can certainly utilize the superiority condition of this aircraft: start the device that increases lift, force-land with minimum speed.The lateral surface of fuselage 1 and top a slice tailplane 3 and a slice vertical tail 4 arranged respectively.Its host wing 2 has device that can increase lift and the device of regulating aerofoil profile, as Fig. 4, Fig. 5, shown in Figure 6: host wing 2 comprises altogether: four spars 5 that are used to be connected and fixed and supporting two fuselages 1 in wing inside, because spar is provoked two fuselages as shoulder pole, so spar will be with the very big material of intensity, the space between the spar 5 can be used as the passage that connects two fuselages and loads little article and place fuel tank etc.; There is a load-bearing cylinder 7 front of spar 5, and there is a load-bearing cylinder 71 back, its two ends respectively with about the accent aerofoil profile cylinder mounting hole 14 of two fuselage 1 inboards flexibly connect, back load-bearing cylinder can before and after adjusting; There are three or three in the position on the upper side of the centre of two load-bearing cylinders and forebody etc. to raise aerofoil profile cylinder 8; The two ends of transferring the aerofoil profile cylinder respectively with about the accent aerofoil profile cylinder mounting hole 14 of two fuselage 1 inboards flexibly connect; The outside of cylinder is the cylindrical shape wing cover 9 with similar high temperature resistant cold-resistant rubber transport tape flexibility of very high pull resistance.Will there be the anti-gas-leak device in two string places of wing cover 9 and fuselage 1 contacted place, there is a leg-of-mutton droope snoot 10 at the leading edge place of host wing 2, its two ends are connected with triangle droope snoot mounting hole above the fuselage 1 respectively with axle, can fore-and-aft adjustment, when adjusting forward, separate with the leading edge of host wing, can avoid the burbling of aerofoil surface, adjust backward and be mainly used in the cutting air, straight and the big shortcoming of the blunt first-harmonic resistance of circle with the leading edge that remedies host wing 2, can also stop the circulation layer that brings when circular leading edge is rotated down, the downward power of reasonably avoiding Magnus effect to produce; Trailing edge has trailing edge flap 11, with the same axle mounting of back load-bearing cylinder, so that it presses close to the trailing edge of host wing 2 all the time, is used to remedy the blunt trailing edge of host wing 2 circles.And can in certain angle, do rotation adjustment around the axle of back load-bearing cylinder.

When taking off, back wing flap 11 and back load-bearing cylinder 71 are suitably regulated forward, transfer aerofoil profile cylinder A8.B81.C82 simultaneously

To adjusted,, increase the protruding degree of wing 2 upper surfaces to raise the upper surface of wing 2.Because the pressure of wing 2 upper surfaces is less, wing cover 9 is upwards inhaled, and wing 2 lower surface pressure are bigger, and the covering nick of wing 2 lower surfaces or straight makes wing 2 present preferable aerodynamic configuration naturally, makes it to have bigger lift.

When starting the device that increases lift if desired, shown in the direction of arrow among Fig. 7: load-bearing cylinder 7 drives forward rotation continuously by its in-to-in engine, thereby driving exterior flexible wing covering 9 constantly rotates forward, flexible wing covering 9 drives transfers aerofoil profile cylinder 8 rotation forward, direction shown in arrow among Fig. 7, the wing cover 9 of wing 2 upper surfaces is motion forwards continuously, the airflow flowing direction is just in time opposite backward with wing 2 upper surfaces, according to the principle and the hydromechanical groundwork of relative motion, the atmospheric pressure that wing 2 upper surfaces obtain is littler; The wing cover 9 of wing 2 lower surfaces is continuously to the motion of the rear of wing, rearward the airflow flowing direction is identical with wing 2 lower surfaces, so the relative velocity of wing 2 lower surfaces and air-flow is low speed more,, obtain higher atmospheric pressure according to hydromechanical groundwork.Because on the wing 2. the pressure difference of lower surface is bigger, the lift that wing 2 obtains is just bigger, droope snoot 10 moves backward simultaneously, press close to the leading edge of host wing 2, stop circular leading edge and be rotated down the circulation layer that brings, reasonably avoid the downward power of Magnus effect generation, add the control of trailing edge flap, reach good lift-rising effect, actv. has shortened the ground run distance of taking off.

After taking off lift-off, can close the device that increases lift as required, both stop the rotation forward of load-bearing cylinder 7, along with the increase of air speed, can regulate aerofoil profile, during aircraft Gonna breakthrough sound barrier, as shown in Figure 9: transfer aerofoil profile cylinder A8.B81.C82, all regulating downwards, is to transfer aerofoil profile cylinder A8 by it, should be adjusted to lowest part, back load-bearing cylinder 71 and back wing flap 11 are regulated backward simultaneously, with the wing cover 9 of tension drum 7 outsides, make wing 2 attenuation as far as possible, thereby help breaking through sound barrier.

During supersonic cruise, accent aerofoil profile cylinder C82 upwards does adjusting a little, make the maximum ga(u)ge position of wing 2 be about the place of 30-50% in leading edge and trailing edge distance, because the upper surface pressure of wing 2 is original just lower, the wing cover 9 of wing 2 upper surfaces is upwards inhaled, thereby makes wing 2 obtain preferable aerodynamic configuration automatically.

If the angle of attack of wing 2 has arrived greatly to a certain degree, top airfoil burbling or when wanting to separate, as shown in figure 10: leg-of-mutton droope snoot can be adjusted forward, away from the certain distance of host wing, temporarily be for conversion into the winglet of similar canard effect, and can rotate a certain angle forward, to transfer aerofoil profile cylinder A8.B81.C82 simultaneously, all go up and adjust to sh, C82 adjusts to the highest, and back load-bearing cylinder 71 is regulated forward, makes host wing 2 be transformed into thicker aerofoil profile, control the back wing flap simultaneously, and can start the device that increases lift, shown in arrow among Figure 10: make it reversing, both load-bearing cylinder 7 rotations continuously backward, the wing cover 9 of wing 2 upper surfaces is continuously to the motion of the rear of wing 2, and rearward the airflow flowing direction is identical with wing 2 upper surfaces, so reduced the relative velocity of wing 2 upper surfaces and air-flow, and controlled the burbling of wing 2 upper surfaces, avoid or postponed the stall phenomenon of aircraft.

When cruising, transfer aircraft low speed aerofoil profile cylinder A8 and B81 to adjust upward, adjust back load-bearing cylinder 71 and back wing flap 11 simultaneously forward, with tension wing cover 9, make wing 2 maximum ga(u)ge positions be about the place of 25-40% in the distance of leading edge and trailing edge, with the increase of wing 2 integral thickness, and make wing 2 obtain bigger lift.

When aircraft needs minimum level speed, can restart the device that increases lift, actv. increases the difference of pressure of wing upper and lower surface, both load-bearing cylinder 7 drove forward rotation continuously by its in-to-in engine, rotate forward with exterior flexible wing covering 9, flexible wing covering 9 drives transfers aerofoil profile cylinder 8 rotation forward, the wing cover 9 of wing 2 upper surfaces is motion forwards continuously, the airflow flowing direction is just in time opposite backward with wing 2 upper surfaces, according to the principle of relative motion, the atmospheric pressure that wing 2 upper surfaces obtain is littler; The wing cover 9 of wing 2 lower surfaces is continuously to the motion of the rear of wing 2, rearward the airflow flowing direction is identical with wing 2 lower surfaces, so the relative velocity of wing 2 lower surfaces and air-flow is low speed more,, obtain higher atmospheric pressure according to hydromechanical groundwork.Because on the wing 2. the pressure difference of lower surface is bigger, and the lift that wing 2 obtains is just bigger, the control of wing flap before and after adding, and obtain lower level speed, also just safer during landing.

Claims

1. the wing of the new type of adjustable aerofoil profile of an aircraft comprises and transfers aerofoil profile cylinder and flexible wing covering, and its aerofoil profile can be adjusted, and it is characterized in that: the accent aerofoil profile cylinder under the covering can up-down adjustment, makes wing present different thickness.

2. novel wing in the claim 1, it has the device that increases lift, comprise: load-bearing cylinder and columnar flexible wing covering, with it is characterized in that: the continuous rotation of load-bearing cylinder, driving exterior flexible wing covering constantly rotates, with the relative velocity of increase, reach the purpose that increases lift with air-flow.

3. the wing configurations scheme of a kind of type aircraft of application rights requirement 1 and 2 comprises two fuselages that are arranged side by side, and the inboard of two fuselages is connected by the host wing of a rectangle.