CN201494624U - Venetian blind-type cracking combined airfoil - Google Patents
Venetian blind-type cracking combined airfoil Download PDFInfo
- Publication number
- CN201494624U CN201494624U CN2009203123756U CN200920312375U CN201494624U CN 201494624 U CN201494624 U CN 201494624U CN 2009203123756 U CN2009203123756 U CN 2009203123756U CN 200920312375 U CN200920312375 U CN 200920312375U CN 201494624 U CN201494624 U CN 201494624U
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- wing
- verts
- verting
- type cracking
- spar
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Abstract
The utility model provides a venetian blind-type cracking combined airfoil which comprises an airfoil body, a main wing beam and a rear wing beam are arranged inside the airfoil body, and two sets of mounting frames are arranged on the main wing beam and capable of leaning and rotating relative to the airfoil body, the two sets of mounting frames are positioned on the two sides of an airplane body respectively, a groups of leaning and rotating power devices are arranged on each set of the mounting frames, the airfoil body is connected with the main load-bearing frame of the airplane body, and two cavities are symmetrically arranged at the left and the right edges of the airfoil body and communicated with each other. Without changing the original load-bearing structures of the airfoil body such as the wing beams, the wing ribs, the reinforced wing ribs, the stringers and the like, a group of venetian blind-type cracking composite coatings are mounted inside each cavity, wherein each venetian blind-type cracking composite coating consists of an upper venetian blind-type cracking composite coating and a lower venetian blind-type cracking composite coating, and the upper and the lower venetian blind-type cracking composite coatings are movably connected with the airfoil body respectively. The venetian blind-type cracking combined airfoil minimizes both the unbalanced moment during the vertical take-off and landing of the aircraft and the aerofoil wind resistance during the transition flight, and ensures the stability of the vertical take-off and landing of the aircraft.
Description
Technical field
The utility model relates to a kind of aircraft wing, particularly a kind of flap type cracking type 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 takes place and cause roll, or the frontal resistance of whole wing is big especially when transition flight, can't successfully carry out the transition to the flat state that flies.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
The purpose of this utility model, provided a kind of flap type cracking type 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 purpose of this utility model is achieved through the following technical solutions: flap type cracking type wing, comprise the wing main body, main spar and rear spar are set in the wing main body, a left side, the erecting frame that one cover can vert with respect to the wing main body respectively is installed on the main spar on right both sides, one group of engine installation that verts is installed on every cover erecting frame, the wing main body is connected with body primary load bearing framework, the left side of wing main body, right both sides symmetry is offered two run-though spaces, the original spar of wing main body in the run-though space, rib, strengthen rib, load bearing frame structures such as long purlin are constant, each run-though space is respectively installed one group of flap type cracking composite skin, flap type cracking composite skin is made up of last flap type cracking composite skin and following flap type cracking composite skin, and last flap type cracking composite skin is connected with the wing subject activity respectively with following flap type cracking composite skin.The described engine installation that verts is wherein any of screw propeller, counter rotating propeller, rotor, ducted fan or the like, and corresponding speed reduction gearing etc.
For further realizing the purpose of this utility model realizing by the following technical solutions: main spar is conventional fixed beam, and the main spar on left and right both sides respectively is movably installed with one group of engine installation that verts.The two ends of wing main body are provided with outer wing respectively.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.
Main spar also can the section of verting and can not the section of verting connect and compose by main spar, and the main spar on left and right both sides can the section of verting respectively be equipped with one group of engine installation that verts respectively.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 again, 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 also be equipped with the engine installation that verts on the erecting frame of the section of verting.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.
Good effect of the present utility model is: it is provided with " louver " type cracking type wing, and the covering blade of " louver " type cracking type 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 type 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, perhaps the direct control engine installation changes lift size (as the rotating speed that changes screw propeller or regulate pitch etc.), and it is differential, vert synchronously the action etc., 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 type 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 utlity model 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 main spar 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, counter rotating propeller, rotor, ducted fan or the like), 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 (as lift-over, face upward the control and hovering of bowing turn 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 composite 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 utility model, and flap type cracking composite skin is in open mode among the figure; Fig. 2 is a structural representation of the present utility model, and flap 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 flap type cracking composite skin 25-wing fence 26-strengthens rib under the long purlin 23-rib 24-of the upper flap type cracking of rocking arm 20-composite skin 21-installing rack 22-
The specific embodiment:
Flap type cracking type wing described in the utility model comprises wing main body 16, the structure of wing main body 16 is identical with existing wing structure, main spar and rear spar 14 are set in the wing main body 16, also be provided with long purlin 22, rib 23 in the wing main body 16 and strengthen rib 26 etc., they and main spar and rear spar 14 connect and compose the main load-carrying construction of wing; The erecting frame 21 that one cover can vert with respect to the wing main body respectively is installed on the main spar on left and right both sides, one group of engine installation that verts is installed on every cover erecting frame 21, wherein erecting frame 21 itself also is the load-carrying construction part of main spar, is used for bearing vert aerodynamic force that engine installation produces and lifting force of wings etc.Wing main body 16 is connected with body primary load bearing framework 15, and the main load-carrying construction of wing is connected with body primary load bearing framework 15 specifically; The left and right both sides symmetry of wing main body 16 is offered two run-though spaces 1, load bearing frame structures such as the wing main body 16 original spars 7 in the run-though space 1, rib 23, reinforcement rib 26, long purlin 22 are constant, each run-though space 1 is respectively installed one group of flap type cracking composite skin, flap type cracking composite skin is made up of last flap type cracking composite skin 20 and following flap type cracking composite skin 24, and last flap type cracking composite skin 20 and following flap type cracking composite skin 24 flexibly connect with wing main body 16 respectively.The described flap type cracking composite skin 20 of going up can be similar or identical with existing vane type louver with the structure of following flap type cracking composite skin 24; Long purlin 22, rear spar 14 or rib 23 in the middle of the run-though space 1, strengthen load bearing frame structure such as rib 26 again with wing main body 16 upper and lower surfaces, along exhibition to or multiple-blade " louver " type of the tangential cracking composite skin that ftractures flexibly connect.Between last flap type cracking composite skin 20 and the following flap type cracking composite skin 24 is run-though space 1, and the vert following power jet flow of washing of engine installation of confession wing main body 16 outsides is passed smoothly.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.Last flap type cracking composite skin 20 and following flap type cracking composite skin 24 are by corresponding connecting rod mechanism, are handled and are controlled by the personnel in the body or flight control unit or the like, ftracture and compound, and deflection etc. are moved.Simultaneously, the engine installation that also can direct control verts changes lift size (as the rotating speed that changes screw propeller or regulate pitch etc.), and differential, the action etc. of verting synchronously, realizes above-mentioned maneuvering flight control and keeps attitude stabilization.
When the aircraft 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 flap type cracking composite skin 20 and following flap type cracking composite skin 24 all 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 flap type cracking composite skin 20 and following flap type cracking composite skin 24 all are in closure state, 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 10-30 second.
During manufacturing, main spar can be conventional fixed beam, and the main spar on left and right both sides respectively is movably installed with one group of engine installation that verts.At this moment, have only described erecting frame 21 to vert, promptly only erecting frame 21 can drive the engine installation that verts and turn to level or vertical state.The planform of erecting frame 21 can be identical with the structure of the power erecting frame that verts of existing vertical lift aircraft, role all is can drive equal power devices such as screw propeller, counter rotating propeller, rotor, ducted fan to vert between level and vertical two positions, erecting frame 21 itself also is the load-carrying construction part of main spar, is used for bearing vert aerodynamic force that engine installation produces and lifting force of wings etc.
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.
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.
During manufacturing, main spar also can adopt following organization plan: main spar can the section of verting by main spar and can not the section of verting 12 be constituted by an active connection, main spar can the section of verting can be with respect to can not the section of verting 12 verting, the verted section on the left and right both sides of main spar respectively is equipped with one group of engine installation that verts, and wing main body 16 is captiveed joint with body primary load bearing framework 15.As shown in Figure 1: main spar can the section of verting 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 again, 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 overlaps fully independently vert rocking arm and the corresponding actuating link that independently verts and is connected with two with right main spar, realizes differential verting, and turns to hovering of controlling aircraft etc.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 flight control unit 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 fully work alone separately, 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.
When the utility model is made, process each parts and assembling by above-mentioned requirements.Technical scheme described in the utility model is not restricted to be used in the scope of lightweight aircraft, is 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 utility model not technology contents of detailed description is known technology.
Claims (9)
1. flap type cracking type 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), the erecting frame (21) that two covers can vert with respect to wing main body (16) is installed on the main spar, two cover erecting frames (21) lay respectively at the both sides of airframe, one group of engine installation that verts is installed on every cover erecting frame (21), wing main body (16) is connected with body primary load bearing framework (15), the left side of wing main body (16), right both sides symmetry is offered two run-though spaces (1), the original spar of wing main body (16) (7) in the run-though space (1), rib (23), strengthen rib (26), long purlin load bearing frame structures such as (22) is constant, each run-though space (1) is respectively installed one group of flap type cracking composite skin, flap type cracking composite skin is made up of last flap type cracking composite skin (20) and following flap type cracking composite skin (24), and last flap type cracking composite skin (20) and following flap type cracking composite skin (24) flexibly connect with wing main body (16) respectively.
2. flap type cracking type wing according to claim 1, it is characterized in that: main spar is conventional fixed beam, and the main spar on left and right both sides respectively is movably installed with one group of engine installation that verts.
3. flap type according to claim 1 cracking type wing is characterized in that: main spar by main spar can the section of verting with can not the section of verting (12) connect and compose, the main spar on left and right both sides can the section of verting respectively be equipped with one group of engine installation that verts.
4. flap type cracking type wing according to claim 3, 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 symmetrical fully, left main spar can also be equipped with the engine installation that verts on the erecting frame (21) of the section of verting.
5. flap type according to claim 3 cracking type wing 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.
6. according to each the described flap type cracking type wing in the claim 1 to 5, it is characterized in that: the two ends of wing main body (16) are provided with outer wing (11) respectively.
7. according to each the described flap type cracking type wing in the claim 1 to 5, it is characterized in that: the described engine installation that verts is a screw propeller.
8. according to each the described flap type cracking type wing in the claim 1 to 5, it is characterized in that: the described engine installation that verts is a rotor.
9. according to each the described flap type cracking type wing in the claim 1 to 5, it is characterized in that: 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, and wing fence (25) is set on the wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009203123756U CN201494624U (en) | 2008-10-24 | 2009-10-13 | Venetian blind-type cracking combined airfoil |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200810158149.7 | 2008-10-24 | ||
| CN2009203123756U CN201494624U (en) | 2008-10-24 | 2009-10-13 | Venetian blind-type cracking combined airfoil |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201494624U true CN201494624U (en) | 2010-06-02 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009203123756U Expired - Fee Related CN201494624U (en) | 2008-10-24 | 2009-10-13 | Venetian blind-type cracking combined airfoil |
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| CN (1) | CN201494624U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105217029A (en) * | 2015-11-05 | 2016-01-06 | 伍卫 | Louver wing type tilt rotor aircraft |
| CN105270621A (en) * | 2015-10-30 | 2016-01-27 | 佛山市神风航空科技有限公司 | Aircraft with skylight on wing |
| CN108382578A (en) * | 2018-04-09 | 2018-08-10 | 北京航空航天大学 | A kind of mixed at high speed layout vertically taking off and landing flyer |
-
2009
- 2009-10-13 CN CN2009203123756U patent/CN201494624U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105270621A (en) * | 2015-10-30 | 2016-01-27 | 佛山市神风航空科技有限公司 | Aircraft with skylight on wing |
| CN105217029A (en) * | 2015-11-05 | 2016-01-06 | 伍卫 | Louver wing type tilt rotor aircraft |
| CN108382578A (en) * | 2018-04-09 | 2018-08-10 | 北京航空航天大学 | A kind of mixed at high speed layout vertically taking off and landing flyer |
| CN108382578B (en) * | 2018-04-09 | 2024-03-29 | 北京航空航天大学 | High-speed hybrid layout vertical take-off and landing aircraft |
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Legal Events
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20100602 Termination date: 20121013 |