CN104176237B - Deformable wing installation and apply its aircraft - Google Patents
Deformable wing installation and apply its aircraft Download PDFInfo
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- CN104176237B CN104176237B CN201410359598.3A CN201410359598A CN104176237B CN 104176237 B CN104176237 B CN 104176237B CN 201410359598 A CN201410359598 A CN 201410359598A CN 104176237 B CN104176237 B CN 104176237B
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Abstract
The invention provides a kind of deformable wing installation, it comprises: fuselage central platform; Parallel drive mechanism, three driving branches that it comprises fixed platform, moving platform and connects fixed platform and moving platform; Fixed platform is fixed on fuselage central platform; Three drive branch coplanar and not parallel between two; Each two connecting rods that drive branch to include conllinear, one end of two connecting rods is connected with fixed platform and moving platform by revolute pair respectively, and the other end of two connecting rods interconnects by moving sets; Transmission connecting mechanism, two of the left and right slide block that it comprises line slideway and can slide on line slideway; Line slideway is fixedly connected on moving platform; Left and right Liang Ge wing mechanism, each wing mechanism includes universal joint, L shaped transmission beam, ball pair, girder, support column; The galianconism end universal-joint of L shaped transmission beam, universal joint is fixed on the slide block of its respective side; The long-armed end of L shaped transmission beam and one end of girder are all fixedly connected with ball pair, and the long-armed conllinear of girder and L shaped transmission beam; Ball pair is movably connected on the top of support column, and the bottom of support column is fixed in fuselage central platform.
Description
Technical field
The present invention relates to a kind of deformable wing installation, and apply the aircraft of this deformable wing installation.
Background technology
The invention of present generation aircraft comes from the understanding of people to bird flying, but equally for generation of liftAircraft wing but cannot freely stretch and wave as the wing of bird, so also just can not look like bird oneSample is flap by sometimes, sometimes spirals and disappears in blue sky and white cloud. With the U.S. headed by aviation big country fromThe morphing that begins one's study the nineties in 20th century, adjusts the wing shapes of aircraft according to demand, wingPlunderring angle, dihedral and inclination angle etc. can adjust and make aircraft reach optimum performance in real time according to flight environment of vehicle and task.Fighter plane as stealthy in F-111, these wings are rigid structure, adopt large-scale pivot device and fuselageConnect, so-called adjustment wing shapes are that a certain wing standing part is moved to certain angle, relativeIn other parts of wing, move certain position, but due under moving range, needed to increase machineryStructure, affects aircraft load-carrying, does not therefore occur similar structures at upgrade version F-114 afterwards again; NewlyThe MFX1 model machine angle of sweep of generation air technology company development has been realized from 15 ° and has been changed to 35 °Change continuously, at present also in the model machine stage; The Variable Geometry Wing concept of Lockheed Martin Corporation isUnder difference flight demand, change wing shapes, wing can fold and change torsion angle and aerofoil area,Because it is large that folding machinery is realized difficulty, design is always in the conceptual phase; Same United States Patent (USP)5645250 adopt slide rail type structure and ball screw to drive the magnification of the twice that has realized wing. SeparatelyOutward, Canadian Bombadier Inc is also studied work on morphing, Canadian riel in 2011Peak-to-peak professor team is practised by gloomy aeronautical engineering institute and the large aircraft of Pang Badi company has designed a kind of deformable wing,Adopt 8 bar parallel institutions that wing is fixed on parallel institution moving platform, mechanism's fixed platform is fixed on machineIn body, realize wing and plunder the variation at angle, dihedral, inclination angle and stretching of wing chord, but whole machineThe wing is by also link rod structural bearing and driving, and in working range, rigidity is very poor, is not suitable for practical application.Domestic research team mainly contains professor Wang Bangfeng of Nanjing Aero-Space University to classical 3-RPS machineStructure improves and is used for connecting fuselage and wing, makes wing produce torsion, deflection and flexible; Beijing University of Science & Engineering is largeLearn the morphing that has also designed similar Lockheed Martin Corporation. In addition, along with submarine and unmannedThe development of machine, between military power, conducting a research, a kind of new unmanned plane technology---unmanned plane packs into latentIn the firing box of ship, directly send in the air and execute the task, therefore unmanned plane is can not in emission processHave external wing, and after lift-off, need spademan to cruise, wing needs very large adjusting range, existingDesign cannot meet the demands.
Comprehensive above-mentioned known, the major defect of existing morphing technology is that load-bearing rigidity is low, changes widthSpend little, weight is large, self adaptation is poor etc.
Summary of the invention
For the shortcoming of prior art, the object of this invention is to provide a kind of deformable wing installation,Can realize wing and plunder the continuous variation adjusting at angle, dihedral, inclination angle, can realize wing and be concealed in fuselage,Can effectively improve air maneuver performance, security performance.
To achieve these goals, on the one hand, the invention provides a kind of deformable for aircraftWing installation, aircraft comprises head and tail, wherein, deformable wing installation comprises:
Fuselage central platform, within it is positioned at aircraft;
Parallel drive mechanism, it is 3RPR parallel drive mechanism, it comprise fixed platform, moving platform, withAnd three driving branches of connection fixed platform and moving platform; Fixed platform is fixed on fuselage central platform; ThreeIndividual driving branch is coplanar and not parallel between two; Each two connecting rods that drive branch to include conllinear, twoOne end of root connecting rod is connected with fixed platform and moving platform by revolute pair respectively, another of two connecting rodsEnd for example, connects by moving sets (hydraulic mechanism);
Transmission connecting mechanism, the left and right two that it comprises line slideway and can slide on line slidewayIndividual slide block; Line slideway is fixedly connected on the moving platform of parallel drive mechanism;
Left and right Liang Ge wing mechanism, each wing mechanism includes universal joint, L shaped transmission beam, ballPair, girder, support column; The galianconism end universal-joint of L shaped transmission beam, universal joint is fixed on itOn the slide block of respective side (left side or right side); The long-armed end of L shaped transmission beam and one end of girder are equalBe fixedly connected with ball pair, and the long-armed conllinear of girder and L shaped transmission beam; Ball pair is movably connected on support columnTop, the bottom of support column is fixed in fuselage central platform.
In the present invention, the meaning of 3RPR parallel drive mechanism is that this parallel drive mechanism has three and drivesMoving branch, wherein moving platform has two translations and a rotation three degree of freedom. Translation direction is positioned at verticallyIn fuselage central platform and along in the plane of head and the tail line of centres, rotation direction is perpendicular to 3RPRThe plane that parallel drive mechanism forms.
In the present invention, each two connecting rods that drive branch to include conllinear, one end of two connecting rods is dividedBe not connected with fixed platform and moving platform by revolute pair, the other end of two connecting rods passes through moving sets(such as hydraulic mechanism, air pressure mechanism, linear electric motors etc.) connect; It should be noted that whole dressIn putting, only having three three moving sets in driving branch is driving link, that is to say three drivingsThe stretching motion of initiative can do in branch; Remaining auxiliary connection, for example two of the left and right on guide rail cunningPiece, the universal joint being fixedly connected with slide block, ball pair between L shaped transmission beam and girder, bePassive part.
In the present invention, from top to bottom, three drive branch to be respectively the first driving branch, the second drivingBranch, the 3rd drives branch. First drives branch, second to drive branch, the 3rd to drive branch between twoNot parallel.
In the present invention, three driving branches can realize axis direction and stretch. Drive branch to do not at threeIn the situation of congeniality (stretch or contract), stretching motion in various degree, moving platform can be with respect to fixedTranslation before and after platform, upper and lower translation, and drive in the plane that branches form with respect to fixed at threePlatform rotates.
Particularly, for example, under original state, moving platform plane and fixed platform plane parallel. When threeDrive branch to extend or shrink according to certain speed proportional is synchronous, can realize moving platform with respect to allocatingTranslation before and after platform.
When the second driving branch keeps length constant, first drives branch to shrink, and the 3rd drives branch to stretchLong, for example can realize moving platform, with respect to fixed platform forward rotation (clockwise); When the second driving dividesProp up and keep length constant, the 3rd drives branch to shrink, and first drives branch's elongation, can realize moving platformRotate backward (for example counterclockwise) with respect to fixed platform.
When the first driving branch shrinks, second drives branch to extend, and the 3rd drives branch to extend, can be realExisting upwards translation of moving platform; Shrink when the 3rd driving branch, second drives branch to extend, and first drivesBranch extends, and can realize the downward translation of moving platform; Certainly, respectively driving branch to shrink and extend will be according toCertain ratio is carried out.
In the present invention, universal joint (U pair) has two rotational freedoms, and for example, an one turning cylinder is flatThe plane that row forms in moving platform, the plane that another turning cylinder forms perpendicular to moving platform.
In the present invention, Left Drive beam and right transmission beam are respectively by the end movement of 3RPR parallel drive mechanismPass to port wing and starboard wing through line slideway. Thereby make wing realize three rotational motions, rotateCenter is respectively left ball pair and right ball pair, and around the angle of rotation scope of fuselage central platform plane is10-80 degree, as shown in Figure 1, wing is realized dihedral α, angle of inclination beta, is plunderred angle γ variation, thereby realizesWing distortion. Particularly, drive wing girder to launch to draw in (plunderring angle γ changes), the leading edge of a wingUnder press under the end of lifting (angle of inclination beta variation), girder and press and lift (dihedral α variation).
According to the present invention another detailed description of the invention, parallel drive mechanism is arranged on fuselage central platformMiddle, and the upper surface maintenance of the plane at three driving branch places and fuselage central platform is vertical,Three drive the direction of branch is the center line connecting direction of head and tail.
Another detailed description of the invention according to the present invention, described in each wing mechanism further comprise rib andWing cover.
Another detailed description of the invention according to the present invention, the upper surface of line slideway and fuselage central platform is flatOK, and with described three drive the plane at branch place vertical.
On the other hand, the invention provides the aircraft with above-mentioned deformable wing installation.
The invention has the beneficial effects as follows:
Adopt in the present invention Spatial closed loop and parallel drive mechanism, realized wing and plunder angle, anti-The continuous variation at angle, inclination angle regulates, thereby improves the pressure distribution of wing, the in real time thriving face of reconditionerThe aerodynamic configurations such as area, lift-drag ratio and aspect ratio, make aircraft carry out different task or fly in differenceWhen line, aeroplane performance all remains on optimum state, has greatly improved air maneuver performance, has expanded and has cruisedScope; In addition, deformable wing installation of the present invention can be realized wing collection, can be used for diving the formula of penetrating withoutMan-machine, promote the disguise of unmanned plane and the combat duty of execution various ways; The present invention adopts spaceClose loop mechanism, has that rigidity is large, precision is high, working space is large, the advantages such as strong operability, design letterSingle, easy for installation, easily safeguard, effectively improve aircraft handling security performance.
Brief description of the drawings
Fig. 1 is wing dihedral α of the present invention, angle of inclination beta, plunder the variation schematic diagram of angle γ;
Fig. 2 is the aircaft configuration schematic diagram of embodiment 1;
Fig. 3 is in embodiment 1, the structural representation of deformable wing installation.
Detailed description of the invention
Embodiment 1
As shown in Figure 2, the aircraft of the present embodiment comprises: head 1, tail 9, deformable wing dressPut.
As shown in Figure 3, deformable wing installation comprises: fuselage central platform 2, parallel drive mechanism3, transmission connecting mechanism 4, port wing mechanism 5, starboard wing mechanism 6. Fuselage central platform 2 is positioned at and fliesWithin machine.
Parallel drive mechanism 3 is arranged on the middle of fuselage central platform 2, and three drive institute of branchThe upper surface of plane and fuselage central platform 2 keep vertical, the direction of three driving branches is machine1 and the center line connecting direction of tail 9. Parallel drive mechanism 3 is 3RPR parallel drive mechanism, itsComprise fixed platform 31, moving platform 32 and connect three drivings point of fixed platform 31 and moving platform 32(from top to bottom, three drive branch be respectively the first driving branch 33, second drive branch 34,The 3rd drives branch 35). First drives branch 33, the second driving branch 34, the 3rd to drive branch35 is coplanar and not parallel between two. Fixed platform 31 is fixed in fuselage central platform 2; Each driving branchThe one end that includes 301,302, two connecting rods 301,302 of two connecting rods of conllinear is passed through respectively to rotateSecondary 303,304 are connected with fixed platform 31 and moving platform 32, another of two connecting rods 301,302End for example, connects by moving sets (hydraulic mechanism, not shown in the figures).
Transmission connecting mechanism 4 comprises line slideway 41 and the left slider that can slide on line slideway42, right slide block 43; Line slideway 41 is fixedly connected on moving platform 32; In line slideway 41 and fuselageThe upper surface of centre platform 2 is parallel, and drives the plane at branch place vertical with three.
Port wing mechanism 5 comprises universal joint 501, L shaped transmission beam 502, ball pair 503, girder 504(showing local), support column 505, rib 506, wing cover 507; L shaped transmission beam 502Galianconism end universal-joint 501, universal joint 501 is fixed on left slider 42; L shaped transmission beam 502Long-armed end and one end of girder 504 be all fixedly connected with ball pair 503, and girder 504 and L shaped biographyThe long-armed conllinear of moving beam 502; Ball pair 503 is movably connected on the top of support column 505, support column 505Bottom be fixed in fuselage central platform 2.
Starboard wing mechanism 6 comprises universal joint 601, L shaped transmission beam 602, ball pair 603, girder 604(showing local), support column 605, rib 606, wing cover 607; L shaped transmission beam 602Galianconism end universal-joint 601, universal joint 601 is fixed on right slide block 43; L shaped transmission beam 602Long-armed end and one end of girder 604 be all fixedly connected with ball pair 603, and girder 604 and L shaped biographyThe long-armed conllinear of moving beam 602; Ball pair 603 is movably connected on the top of support column 605, support column 605Bottom be fixed in fuselage central platform 2.
Although the present invention discloses as above with preferred embodiment, not in order to limit model of the invention processEnclose. Any those of ordinary skill in the art, not departing from invention scope of the present invention, when doingA little improvement, every equal improvement of doing according to the present invention, should be scope of the present invention and containsLid.
Claims (5)
1. for a deformable wing installation for aircraft, described aircraft comprises head and tail, itsIn, described deformable wing installation comprises:
Fuselage central platform, within it is positioned at described aircraft;
Parallel drive mechanism, it is 3RPR parallel drive mechanism, it comprise fixed platform, moving platform, withAnd connect described fixed platform and described moving platform three and drive branches; Described in described fixed platform is fixed onFuselage central platform; Described three drive branch coplanar and not parallel between two; Each described driving branchInclude two connecting rods of conllinear, one end of described two connecting rods respectively by revolute pair with described in allocatePlatform and described moving platform connect, and the other end of described two connecting rods interconnects by moving sets;
Transmission connecting mechanism, it comprises line slideway and the left side that can slide on described line slidewayRight two slide blocks; Described line slideway is fixedly connected on the moving platform of described parallel drive mechanism;
Left and right Liang Ge wing mechanism, described in each wing mechanism include universal joint, L shaped transmission beam,Ball pair, girder, support column; The galianconism end of described L shaped transmission beam connects described universal joint, described inUniversal joint is fixed on the described slide block of its respective side; The long-armed end of described L shaped transmission beam and instituteOne end of stating girder is all fixedly connected with described ball pair, and described girder and described L shaped transmission beam is long-armedConllinear; Described ball pair is movably connected on the top of described support column, and the bottom of described support column is fixed onIn described fuselage central platform.
2. the deformable wing installation for aircraft as claimed in claim 1, wherein, described parallel connectionDriving mechanism is arranged on the middle of described fuselage central platform, and described three driving branch placesPlane keeps vertical with the upper surface of described fuselage central platform, and described three drive the direction of branch to beThe center line connecting direction of head and tail.
3. the deformable wing installation for aircraft as claimed in claim 1, wherein, described in eachWing mechanism further comprises rib and wing cover.
4. the deformable wing installation for aircraft as claimed in claim 1, wherein, described straight lineGuide rail is parallel with the upper surface of described fuselage central platform, and with described three drive the flat of branch placesFace is vertical.
5. there is the aircraft of the described deformable wing installation of one of claim 1-4.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410359598.3A CN104176237B (en) | 2014-07-25 | 2014-07-25 | Deformable wing installation and apply its aircraft |
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| CN201410359598.3A CN104176237B (en) | 2014-07-25 | 2014-07-25 | Deformable wing installation and apply its aircraft |
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| CN104176237A CN104176237A (en) | 2014-12-03 |
| CN104176237B true CN104176237B (en) | 2016-05-18 |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107284651B (en) * | 2016-04-05 | 2024-06-07 | 及兰平 | Folding wing |
| CN107554752A (en) * | 2017-09-21 | 2018-01-09 | 宋萍萍 | A kind of municipal afforestation unmanned plane of taking photo by plane |
| CN107651166A (en) * | 2017-09-21 | 2018-02-02 | 任球 | One kind is taken photo by plane unmanned plane |
| CN109606629A (en) * | 2018-11-07 | 2019-04-12 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft |
| CN109823513B (en) * | 2019-03-21 | 2020-09-08 | 北京航空航天大学 | Folding and rotating device applied to wings |
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| GB562693A (en) * | 1942-12-23 | 1944-07-12 | Saunders Roe Ltd | Retractable auxiliary wing elements |
| US3510088A (en) * | 1967-02-06 | 1970-05-05 | British Aircraft Corp Ltd | Variable-geometry aircraft |
| US5645250A (en) * | 1993-08-26 | 1997-07-08 | Gevers; David E. | Multi-purpose aircraft |
| CN101028866A (en) * | 2007-03-30 | 2007-09-05 | 哈尔滨工业大学 | Aircraft with wing sweepback angle change |
| CN102390229A (en) * | 2011-10-10 | 2012-03-28 | 南昌航空大学 | Airfoil transformation mechanism of submarine aircraft |
| CN102530238A (en) * | 2012-02-23 | 2012-07-04 | 北京理工大学 | Unmanned aerial vehicle with variable sweepbacks and spans of wings |
| CN203143002U (en) * | 2012-11-07 | 2013-08-21 | 成都飞机设计研究所 | Connective wing synchronous variable sweep-mobile mechanism |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US8083185B2 (en) * | 2007-11-07 | 2011-12-27 | The Boeing Company | Aircraft wing tip having a variable incidence angle |
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Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB562693A (en) * | 1942-12-23 | 1944-07-12 | Saunders Roe Ltd | Retractable auxiliary wing elements |
| US3510088A (en) * | 1967-02-06 | 1970-05-05 | British Aircraft Corp Ltd | Variable-geometry aircraft |
| US5645250A (en) * | 1993-08-26 | 1997-07-08 | Gevers; David E. | Multi-purpose aircraft |
| CN101028866A (en) * | 2007-03-30 | 2007-09-05 | 哈尔滨工业大学 | Aircraft with wing sweepback angle change |
| CN102390229A (en) * | 2011-10-10 | 2012-03-28 | 南昌航空大学 | Airfoil transformation mechanism of submarine aircraft |
| CN102530238A (en) * | 2012-02-23 | 2012-07-04 | 北京理工大学 | Unmanned aerial vehicle with variable sweepbacks and spans of wings |
| CN203143002U (en) * | 2012-11-07 | 2013-08-21 | 成都飞机设计研究所 | Connective wing synchronous variable sweep-mobile mechanism |
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Address after: 518055 Nanshan District Xili Shenzhen University, Shenzhen, Guangdong, Harbin Industrial University Campus Patentee after: Harbin Institute of Technology (Shenzhen) Address before: 518055 Nanshan District Xili Shenzhen University, Shenzhen, Guangdong, Harbin Industrial University Campus Patentee before: Harbin Institute of Technology Shenzhen Graduate School |