CN101380997A

CN101380997A - Louver type cracking composite wing

Info

Publication number: CN101380997A
Application number: CNA2008101581497A
Authority: CN
Inventors: 穆骞
Original assignee: Individual
Current assignee: Individual
Priority date: 2008-10-24
Filing date: 2008-10-24
Publication date: 2009-03-11

Abstract

The invention discloses a shutter-typed cracking composite wing, comprising a wing mainbody which is internally provided with a main wing beam and a rear wing beam; the main wing beam consists of an inclinable section and a non-inclinable section which are connected with each other; the wing mainbody is connected with an aircraft main bearing frame; the left side and the right side of the wing mainbody are respectively provided with two through spaces; the inclinable section of the main wing beam is provided with two groups of inclined power devices; each through space is respectively provided with a group of shutter-typed cracking composite envelope which consists of an upper shutter-typed cracking composite envelope and a lower shutter-typed cracking composite envelope; the upper shutter-typed cracking composite envelope and the lower shutter-typed cracking composite envelope are respectively connected with the wing mainbody. The wing leads the unbalanced moment during the vertical lifting of the aircraft and the wind-facing resistance during the transitional flying of the aircraft to be reduced to the minimum; meanwhile, the whole wing, especially for the external wing of the large wing keeps horizontal and still fixedly all the time, thus ensuring the stability during the vertical lifting of the aircraft and successful transition to the flat flying state.

Description

Louver type cracking composite wing

Technical field

The present invention relates to a kind of aircraft wing, particularly a kind of louver type cracking composite wing.

Background technology

At present, the vert vertically taking off and landing flyer of engine installation of conducts such as existing various employing screw propeller, counter rotating propeller, rotor or ducted fan, it all is the wing tip that these engine installations that vert is installed in wing, perhaps vert together with whole wing, unbalanced moment was very big when this had just caused vertical takeoff and landing, very easily unstability taking place and causes roll, or the frontal resistance of whole wing is big especially when transition flight, can't successfully carry out the transition to and flat fly state, this also is that this class aircraft rarely has one of main reason of success till now.So the wing configuration of existing vertically taking off and landing flyer can't satisfy people's user demand.

Summary of the invention

Purpose of the present invention, provided a kind of louver type cracking composite wing, it can make the unbalanced moment of aircraft when vertical takeoff and landing, all reduce to minimum with the wing frontal resistance when the transition flight, whole wing of while, the outer wing of the especially big span keeps horizontal fixed motionless from start to finish, stability in the time of can guaranteeing the aircraft vertical takeoff and landing and successfully to the flat status transition that flies, and, also can keep original structural strength of wing and bending resistance, anti-twisting property is constant, and aerofoil profile and wing thickness are constant, and promptly the original whole aeroperformance of wing is constant, thereby can satisfy people's user demand.

The objective of the invention is to be achieved through the following technical solutions: louver type cracking composite wing, comprise the wing main body, main spar and rear spar are set in the wing main body, main spar can the section of verting by main spar and can not the section of verting be connected and composed, the wing main body is connected with body primary load bearing framework, the right and left of wing main body is offered two run-though spaces respectively, main spar can the section of verting be gone up two groups of engine installations that vert of installation, each run-though space is respectively installed one group of louver type cracking composite skin, the louver type cracking composite skin is made up of last louver type cracking composite skin and following louver type cracking composite skin, and last louver type cracking composite skin is connected with the wing main body respectively with following louver type cracking composite skin.

For further realizing purpose of the present invention, can also realize by the following technical solutions: main spar can the section of verting by the rocking arm that verts, left main spar can the section of verting and right main spar can the section of verting connect and compose, right main spar can the section of verting be made of second beam and first beam that verts that verts, second beam and first that verts verts erecting frame is set between the beam, the engine installation that verts is installed on the erecting frame, left side main spar can the section of verting with right main spar can the section of verting shape and structure symmetrical fully, left main spar can the erecting frame of the section of verting on the installation engine installation that verts.Second verts is provided with cavity in the beam, and transmission shaft is installed in the cavity, and an end of transmission shaft is connected with the engine installation that verts, and the other end enters body.The two ends of wing main body are provided with outer wing respectively.The described engine installation that verts is a screw propeller.Trailing edge flap respectively is installed about the rear portion of wing main body, and flaperon is respectively installed at the rear portion of left and right outer wing, and wing fence is set on the wing.

Good effect of the present invention is: it is provided with " louver " type cracking composite wing, and the covering blade of " louver " type cracking composite wing can ftracture along with verting verting of engine installation or be compound.When vertical takeoff and landing, the axis direction of engine installation of verting is vertical with respect to ground, at this moment the covering blade of " louver " type cracking composite wing ftractures, wash greatly down the run-though space that the power jet flow passes in the wing and blow to the below, can increase substantially lift efficient, thereby for aircraft provides big as far as possible dynamic lift, simultaneously by controlling the deflecting direction of multiple-blade cracking composite skin, can make aircraft realize vertical takeoff and landing, hovering, hover and turn to or left and right sides translation, and before fly, maneuvering flights such as inverted flight, and at this moment whole wing, the outer wing of the especially big span still keeps horizontal fixed motionless; When the horizontal flight transition, the covering blade of " louver " type cracking composite wing is again along with verting verting of engine installation and closure, again be combined into complete wing, for aircraft provides aerodynamic lift, can increase substantially pneumatic efficiency, the power jet flow of the engine installation that at this moment verts also blows to the rear, thereby has become thruster fully, promote the horizontal high-speed flight of aircraft, can solve the problem that prior art exists.

The present invention has following uniqueness and excellent technical advantage: 1, two groups of longitudinal axiss of the as close as possible fuselage of engine installation that vert, so the arm of force of its dynamic lift is very short, corresponding torque load is just little; The load-carrying construction of the main spar section of verting is solid simultaneously, and the stress of lift load disperses; 2, vert engine installation totally in the wing outside, therefore kept the original load bearing frame structure of wing not change as much as possible, ftracture/compound only is the small part covering, so bending resistance that wing is overall and anti-twisting property are still very strong, promptly kept the original structural strength of wing constant, bulk strength height, rigidity are big; 3, vert engine installation totally in the wing outside, therefore also kept original aerofoil profile of wing and wing thickness not to change as much as possible, thereby can obtain best aerodynamic lift characteristic; 4, the vert lifting line center of gravity by aircraft just in time of power, so in a longitudinal direction, center of gravity, centre of lift, and the position of focus can accomplish optimum matching, help the overall trim of aircraft; 5, the vert unbalanced moment of power of both sides, the directional balance when lateral stability when guaranteeing the aircraft vertical takeoff and landing as far as possible and flat at a high speed flying have farthest been reduced; 6, do not limit the diameter of the engine installation that verts (as screw propeller, rotor etc.), promptly can exceed the scope of covering cracking, so just can obtain bigger dynamic lift; 7, the covering cracking has reduced wing blocking gas washing stream under the power that verts as much as possible, the following gas washing stream that guarantees the overwhelming majority all blows to the below, can increase substantially lift efficient, thereby obtain big as far as possible dynamic lift, and enough lift is the basic foundation of aircraft vertical takeoff and landing; 8, under the vertical takeoff and landing state, the power itself that verts can be effectively carries out flicon (facing upward the control and hovering of bowing as lift-over turns to etc.) to aircraft, in addition fly before finishing, maneuver such as inverted flight, and provide enough required control torque.This point is of crucial importance, because have only the flight attitude control of balance and stability, just really makes vertically taking off and landing flyer itself become possibility; 9, the vertical takeoff and landing state down by the deflection of control multiple-blade cracking composite skin, changes the injection direction of washing jet flow under the power that verts, can obtain vectored thrust, turns to or maneuver such as left and right sides translation thereby aircraft is finished hover; 10, do not limit the size of the wing span, make whole wing have the outer panel of the big span, and the big span with high lift-drag ratio characteristic is aircraft stability, safety, economy, and the basic guarantee of some other important flight qualities; 11, increased the gross area of wing significantly, flown to provide more lift, significantly reduced wing load simultaneously for flat at a high speed; 12, vert that gas washing stream is reduced to minimum to wing influence on flow field scope under the power, the outer panel of the big span is in the middle of the level and smooth stable laminar flow all the time, therefore can obtain highly stable lift, and this is even more important in transition flight; 13, vert under the power that to flow to speed down very high for gas washing, add effective obstruct of large-area host wing, lower stream of airflow is difficult to be back to the top of oar plate edge, does not also just form " eddy current ring " state of danger; 14, power transmission path is short, and structure design is simple, in light weight, the driving efficiency height; 15, the inheritance to traditional wing structure is very strong, and therefore design is very simple, and in light weight.As can be seen, this " flap type " cleverly cracking/compound wing structure has farthest been taken into account vertical takeoff and landing and has been put down at a high speed and flown two kinds of state of flights, and the big span of high lift-drag ratio that is brought by it then is the foundation stone of subsonic flight.

Description of drawings

Fig. 1 is a structural representation of the present invention, and the louver type cracking composite skin is in open mode among the figure: Fig. 2 is a structural representation of the present invention, and the louver type cracking composite skin is in closure state among the figure; Fig. 3 is that the structure for amplifying scheme drawing is looked on the right side of Fig. 1; Fig. 4 is that the structure for amplifying scheme drawing is looked on the right side of Fig. 2.

Number in the figure: 1-run-though space 2-screw 3-fuselage skin 4 power set actuating link 5-the first sealing ring 6-power transmission shaft 7-second vert outer wing 12-main spar of load joint 11-that beam 9-the second sealing ring 10-main spar can not the section of verting of beam 8-first that verts that verts can not the section of verting 13-flaperon 14-rear spar 15-body Main heavy truss 16-wing main body 17-trailing edge flap 18-propeller hub radome fairing 19-verts that louver type cracking composite skin 25-wing fence 26-strengthens rib under the long purlin 23-rib 24-of the upper louver type cracking composite skin 21-installing rack 22-of rocking arm 20-

The specific embodiment:

Louver type cracking composite wing of the present invention comprises wing main body 16, main spar and rear spar 14 are set in the wing main body 16, main spar, rear spar 14, long purlin 22 and rib 23 etc. connect and compose the main load-carrying construction of main spar jointly, main spar can the section of verting by main spar and can not the section of verting 12 be connected and composed, and main spar can the section of verting can not the section of verting 12 vert relatively; Wing main body 16 is captiveed joint with body primary load bearing framework 15, can symmetry offer two run-though spaces 1 on the wing main body 16, main spar can the section of verting be gone up two groups of engine installations that vert of installation, one group of louver type cracking composite skin respectively is installed in each run-though space 1, the louver type cracking composite skin is made up of last louver type cracking composite skin 20 and following louver type cracking composite skin 24, and last louver type cracking composite skin 20 is connected with wing main body 16 respectively with following louver type cracking composite skin 24; The described structure that goes up louver type cracking composite skin 20 and following louver type cracking composite skin 24 can be similar or identical with existing vane type louver; Main spar can vert in the Duan Keyu wing main body 16 ribs 23 and strengthen rib 26 structures such as load bearing frame such as grade and flexibly connect, load bearing frame structures such as the long purlin 22 of run-though space 1, rear spar 14 or rib 23 are again with wing main body 16 upper and lower surfaces, along exhibition to or multiple-blade " louver " the type cracking composite skin of tangential cracking connect.Between last louver type cracking composite skin 20 and the following louver type cracking composite skin 24 is run-though space 1, passes smoothly for the vert following power jet flow of washing of engine installation of wing main body 16 outsides.According to different flicon requirements, the connection mode of load bearing frame structures such as mutliblade " louver " type cracking composite skin and long purlin, rear spar or rib, reinforcement rib can have multiple, and the direction of control multiple-blade cracking and deflection also can be to all directions.For example: as shown in figures 1 and 3, multiple-blade cracking composite skin can be opened up to being connected with edges such as long purlin, rear spars, the direction of cracking and deflection is to the fuselage rear or to fuselage the place ahead, perhaps differential to both direction respectively, can either when transition flight, obtain stable smooth wing flow field like this, produce bigger dynamic lift, can hover when vertical takeoff and landing again turns to.Perhaps multiple-blade cracking composite skin and rib, reinforcement rib etc. are along tangential hinged, and the direction of cracking and deflection just can realize left and right sides translation like this to left or to right-hand when vertical takeoff and landing.Again or above-mentioned connection mode and cracking and deflecting direction all exists simultaneously, thereby the flicon quality and the aerodynamic lift characteristic of the best are provided jointly.The cracking of last louver type cracking composite skin 20 and following louver type cracking composite skin 24 and compound be by corresponding connecting rod mechanism, handle and control by the personnel in the body or control convenience or the like, can control it by connecting rod mechanism and open or close, function unit is installed in the aircraft operator's compartment.

When aircraft needs vertical takeoff and landing, as shown in figures 1 and 3, the engine installation that verts is vertical with respect to wing main body 16, at this moment, last louver type cracking composite skin 20 and following louver type cracking composite skin 24 are in open mode, the vert following power jet flow of washing of engine installation can be passed run-though space 1 downwards swimmingly; When the aircraft horizontal flight, as Fig. 2 and shown in Figure 4, the engine installation that verts verts to level attitude, at this moment, last louver type cracking composite skin 20 and following louver type cracking composite skin 24 all are in closure state, have significantly increased the aerodynamic lift that wing produced.The flight of aircraft normal level, the time that carries out the transition to horizontal flight from plumbness is about 20-30 second.

As shown in Figure 1, main spar can the section of verting can by the rocking arm 19 that verts, left main spar can the section of verting and right main spar can the section of verting connect and compose, right main spar can the section of verting be made of second beam 7 and first beam 8 that verts that verts, second beam 7 and first that verts verts erecting frame 21 is set between the beam 8, the engine installation that verts is installed on the erecting frame 21, left side main spar can the section of verting with right main spar can the section of verting shape and structure symmetrical fully, left main spar can the erecting frame 21 of the section of verting on the also installation engine installation that verts.The engine installation erecting frame itself that verts also is the load-carrying construction part that main spar can the section of verting, be used for bearing aerodynamic force and the lifting force of wings that engine installation produces of verting, the engine installation of installing on it that verts can be wherein any of screw propeller, counter rotating propeller, rotor or ducted fan or the like, and corresponding speed reduction gearing etc.Left side main spar can the section of verting can the section of verting also can be respectively be connected with two independently vert rocking arm and the actuating links that independently vert with right main spar, can realize differential verting.The rocking arm 19 that verts is installed in the body, is handled and controls by manual draw bar or hydraulic servo etc. by personnel in the body or control convenience etc.

Second verts is provided with cavity in the beam 7, and transmission shaft 6 is installed in the cavity, and an end of transmission shaft 6 is connected with the engine installation that verts, and the other end enters body.The power resources of engine installation of verting have two kinds: a kind of is to adopt the body intrinsic motivation, gives the engine installation that verts by transmission shaft 6 with transmission of power; Second kind is that the engine installation itself that verts just has driving engine, and this moment, the effect of transmission shaft 6 then was the engine installation that connects the another side wing, played the effect of balance the right and left power.Or the engine installation that verts on left and right both sides also can work alone separately fully, so also just need not to use transmission shaft 6 to come the power of balance the right and left, so main spar can the section of verting second verts and just transmission shaft can be installed in the beam, promptly second beam that verts can change the solid beam that verts into.

The two ends of wing main body 16 are provided with outer wing 11 respectively, and outer wing 11 can increase the area of whole wing, the corresponding lifting force of wings that also just increased.

Second transmission shafts 6 that vert in the beam 7 can play two kinds of effects: the one, the transmission of power of body intrinsic motivation to verting engine installation; The 2nd, the engine installation itself that verts just has driving engine, and the effect of this moment then for connecting the engine installation that verts of another side, reaches the effect of balance the right and left power.

For aircraft is normally handled when the horizontal flight, trailing edge flap 17 respectively is installed about the rear portion of wing main body 16, flaperon 13 is respectively installed at the rear portion of left and right outer wing 11; Aerofoil surface also can be installed wing fence 25.

When the present invention makes, process each parts and assembling by above-mentioned requirements.Technical solutions according to the invention are not restricted to be used in the scope of lightweight aircraft, be applied to the vertically taking off and landing flyer of model airplane, unmanned plane, carrier operation version, transportation type or the like type but can also extensively derive, the present invention not technology contents of detailed description is known technology.

Claims

1, louver type cracking composite wing, it is characterized in that: comprise wing main body (16), main spar and rear spar (14) are set in the wing main body (16), main spar can the section of verting by main spar and can not the section of verting (12) be connected and composed, wing main body (16) is connected with body primary load bearing framework (15), the right and left of wing main body (16) is offered two run-though spaces (1) respectively, main spar can the section of verting be gone up two groups of engine installations that vert of installation, each run-though space (1) is respectively installed one group of louver type cracking composite skin, the louver type cracking composite skin is made up of last louver type cracking composite skin (20) and following louver type cracking composite skin (24), and last louver type cracking composite skin (20) is connected with wing main body (16) respectively with following louver type cracking composite skin (24).

2, louver type cracking composite wing according to claim 1, it is characterized in that: main spar can the section of verting by the rocking arm that verts (19), left side main spar can the section of verting can the section of verting connect and compose with right main spar, right main spar can the section of verting by second beam (7) and first beam (8) formation of verting of verting, second beam (7) and first that verts verts erecting frame (21) is set between the beam (8), erecting frame (21) is gone up the engine installation that verts is installed, left side main spar can the section of verting with right main spar can the section of verting shape and structure symmetry fully, the erecting frame (21) that left main spar can the section of verting is the installation engine installation that verts upward.

3, louver type cracking composite wing according to claim 2 is characterized in that: second verts is provided with cavity in the beam (7), and transmission shaft (6) is installed in the cavity, and an end of transmission shaft (6) is connected with the engine installation that verts, and the other end enters body.

4, according to each the described louver type cracking composite wing in the claim 1,2 or 3, it is characterized in that: the two ends of wing main body (16) are provided with outer wing (11) respectively.

5 louver type cracking composite wings according to claim 4 is characterized in that: the described engine installation that verts is a screw propeller.

6, louver type cracking composite wing according to claim 5 is characterized in that: trailing edge flap (17) respectively is installed about the rear portion of wing main body (16), and flaperon (13) is respectively installed at the rear portion of left and right outer wing, and wing fence (25) is set on the wing.