CN102267557A - Canard forward-sweep telescoping wing aerodynamic configuration with variable span wing area - Google Patents
Canard forward-sweep telescoping wing aerodynamic configuration with variable span wing area Download PDFInfo
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- CN102267557A CN102267557A CN2011101059691A CN201110105969A CN102267557A CN 102267557 A CN102267557 A CN 102267557A CN 2011101059691 A CN2011101059691 A CN 2011101059691A CN 201110105969 A CN201110105969 A CN 201110105969A CN 102267557 A CN102267557 A CN 102267557A
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Abstract
The invention relates to a canard forward-sweep telescoping wing aerodynamic configuration with variable span wing area. The canard forward-sweep telescoping wing aerodynamic configuration comprises a fuselage, canards, wings, and a vertical fin; the wings comprise forward-sweep inner wings and forward-sweep telescopic outer wings having internal connections with the forward-sweep inner wings by a telescoping mechanism; and the telescoping mechanism extends to allow the forward-sweep telescopic outer wings to extend to the outside of the forward-sweep inner wings when the mach number (Ma) of an unmanned aerial vehicle is 0.2, and the telescoping mechanism contracts to allow the forward-sweep telescopic outer wings to contract to the inside of the forward-sweep inner wings when the Ma of the unmanned aerial vehicle is 0.4, wherein the area ratio of the forward-sweep telescopic outer wings to the forward-sweep inner wings is 0.25-0.45. The telescoping wing configuration with variable span wing area adopted in the invention allows the unmanned aerial vehicle to have good aerodynamic performances in scopes of different spatial domains and different speeds and the mobility and the flexibility of the unmanned aerial vehicle to be improved. According to the canard forward-sweep telescoping wing aerodynamic configuration of the invention, when Ma is equal to 0.2 or 0.4, the cruise lift-to-drag ratio of the high aspect ratio aerodynamic configuration is over 20% higher than the cruise lift-to-drag ratio of the low aspect ratio aerodynamic configuration when the unmanned aerial vehicle flies at a low speed, and the cruise lift-to-drag ratio of the low aspect ratio aerodynamic configuration is about 15% higher than the cruise lift-to-drag ratio of the high aspect ratio aerodynamic configuration when the unmanned aerial vehicle flies at a high speed, so the capacities of the cruise flight with the Ma of 0.2 and 0.4 are possessed.
Description
Technical field
The present invention relates to a kind of UAV aerodynamic layout, particularly relate to the telescopic wing aerodynamic arrangement that a kind of canard sweepforward becomes the long blade area of exhibition, belong to the UAV aerodynamic layout technical field.
Background technology
In recent years, the aeronautical technology fast development develops to the multi-functional direction of multitask gradually to Flight Vehicle Design.Traditional fixed-wing Flight Vehicle Design, be subjected to the restriction of technical elements, be merely able to accomplish between different aerial mission states, to trade off, aircraft only can have good aeroperformance in certain spatial domain scope, certain speed state scope, and the aerodynamic performance of aircraft then descends when leaving design point flight.Therefore, a kind of function of fixed-wing aircraft type highlights single, and its manoevreability and alerting ability all are very limited.The distortion aircraft can make aircraft all have optimized aeroperformance in each task phase, thereby strengthens the flying power of aircraft or save fuel oil, improve the takeoff and landing performance of aircraft and grasp steady characteristic, improve the combat duty adaptive capacity of aircraft.
Unmanned plane mainly adopts fixed-wing aerodynamic arrangement at present, and existence can't take into account high low-speed performance, and fight function is few, problems such as viability difference.
Summary of the invention
Technology of the present invention is dealt with problems and is: overcome the deficiencies in the prior art, a kind of aircraft high-performance cruise that takes into account is provided, the low speed scouting of spiraling, the canard sweepforward of the performance requriements of multiple combat duty such as fast dive attack becomes the telescopic wing aerodynamic arrangement of the long blade area of exhibition over the ground.
Technical solution of the present invention is: a kind of canard sweepforward becomes the telescopic wing aerodynamic arrangement of the long blade area of exhibition, comprise fuselage, canard, wing and vertical fin, wing comprises wing and the scalable outer wing of sweepforward in the sweepforward, the scalable outer wing of sweepforward is by wing internal connection in telescoping mechanism and the sweepforward, when unmanned plane Mach 2 ship 0.2, telescoping mechanism stretches the scalable outer wing of sweepforward is reached airfoil outer in the sweepforward, when unmanned plane Mach 2 ship 0.4, telescoping mechanism shrinks the scalable outer wing of sweepforward is contracted in wing inside in the sweepforward, and wherein the area ratio of wing is 0.25～0.45 in the scalable outer wing of sweepforward and the sweepforward.
Described telescoping mechanism comprises driver train, hinge linkage, telescopic rail and outer wing link span, telescopic rail, hinge linkage and outer wing link span distribute in the driver train bilateral symmetry, driver train comprises motor, two synchronizer gears and bearing, the guide-track groove of telescopic rail for directly in sweepforward, processing on the wing twin beams, the rhombus-mechanism that hinge linkage is made up of some hinges and pole, on the pole of prismatic mechanism end, nose bar is installed, nose bar is stuck in the telescopic rail, the outer wing link span is fixedly mounted on prismatic mechanism end, the scalable outer wing of sweepforward is installed on the outer wing link span, the pole of prismatic mechanism front end is connected with the synchronizer gear gear, two synchronizer gears are mediated mutually, one of them synchronizer gear is connected with drive axle of motor, motor and two synchronizer gear fixed installation bearings, bearing is fixedly mounted on the axis of symmetry of fuselage.
The present invention compared with prior art beneficial effect is:
(1) the present invention adopts the telescopic wing layout that becomes the long blade area of exhibition, make unmanned plane in different spatial domains, different speed state scopes all has good aeroperformance, improved the manoevreability and the alerting ability of unmanned plane;
(2) the present invention is in Ma=0.2 and 0.4 scope, during low-speed operations, the high aspect ratio aerodynamic arrangement 1ift-drag ratio that cruises is higher more than 20% than low aspect ratio, during high-speed flight, the low aspect ratio aerodynamic arrangement 1ift-drag ratio that cruises is higher by about 15% than high aspect ratio, compare with magnitude fixed-wing aircraft, the flexible variable geometry aircraft of the present invention can increase voyage 10%, possesses the ability of Ma0.2 and Ma0.4 cruising flight simultaneously;
(3) the present invention adopts telescopic wing aerodynamic arrangement, on the basis that does not increase the Flight Vehicle Structure complexity, takes into account the high low-speed performance of aircraft, improves the fight capability of aircraft;
(4) to adopt telescoping mechanism to be difficult for locked in the present invention, and robustness is stronger, is easy to realize wing and the scalable outer wing integrated design of sweepforward in the sweepforward, and weight is lighter, and the shrinkage distortion speed of the scalable outer wing of while sweepforward is fast.
Description of drawings
Fig. 1 is the structural representation under the lower-speed state of the present invention;
Fig. 2 is the structural representation under the fast state of the present invention;
Fig. 3 is a telescoping mechanism structural representation of the present invention;
Fig. 4 is a hinge linkage schematic diagram of the present invention;
Fig. 5 rises resistance polar (abscissa D represents resistance, and ordinate L represents lift) for high aspect ratio and low aspect ratio aerodynamic arrangement;
Fig. 6 is high aspect ratio and low aspect ratio aerodynamic arrangement 1ift-drag ratio and lift relation curve (abscissa L represents lift, and ordinate K represents 1ift-drag ratio).
The specific embodiment
Principle of design of the present invention: on the basis that does not increase the Flight Vehicle Structure complexity, take into account the high low-speed performance of aircraft, improve the fight capability of aircraft.
In Ma=0.2 and 0.4 scope.Telescopic wing aerodynamic arrangement can bring benefit to be based on following principle.The aerodynamic drag of unmanned plane mainly is made of two parts, useless resistance and induced drag.
C wherein
D0Be zero lift drag, be the function of wing area, A is the induced drag factor, is the function of aspect ratio.
High aspect ratio and low-aspect-ratio configuration wing area rate of change nearly reach 35%, reach 45% if consider the exposed area rate of change.The low-aspect-ratio configuration zero lift drag is littler than high aspect ratio thus.The induced drag factor of low aspect ratio aerodynamic arrangement is bigger than high aspect ratio on the other hand.This just causes, and during high-speed flight, required lift coefficient is less, C
D0Occupy leadingly, the low-aspect-ratio configuration 1ift-drag ratio is bigger.During low-speed operations, required lift coefficient is bigger, and induced drag occupies leading, and high aspect ratio layout 1ift-drag ratio is bigger.One of characteristics that the analysis showed that low aspect ratio are that the maximum lift-drag ratio position appears at than Low Angle Of Attack.When then being maximum lift-drag ratio is provided, the advantage of high aspect ratio can provide bigger lift coefficient.
Guaranteeing under the prerequisite that 1ift-drag ratio is dominant, by adjusting and optimize the aspect of wing, rational static stability marging when designing high speed and low-speed operations.High speed configuration low-aspect-ratio configuration requires quick arrival on the one hand, also will carry out strike mission over the ground, and this just requires manoevreability stronger, and static stability marging is less to be about 5%.The low speed configuration is used to spiral and scouts and compacting, is approximately 10% so its static stability marging is set.For satisfying this requirement, unmanned plane adopts sweepforward telescopic wing layout, and determines final distribution form and parameter by optimizing.As Fig. 5, shown in 6, in Ma=0.2 and 0.4 scope, during the unmanned plane low-speed operations, the high aspect ratio aerodynamic arrangement 1ift-drag ratio that cruises is higher more than 20% than low aspect ratio, during the unmanned plane high-speed flight, the low aspect ratio aerodynamic arrangement 1ift-drag ratio that cruises is higher by about 15% than high aspect ratio, compare with magnitude fixed-wing aircraft, the flexible variable geometry aircraft of the present invention can increase voyage 10%, possesses the energy ability of Ma0.2 and Ma0.4 cruising flight simultaneously.
The present invention is made up of five major parts of wing 3, the scalable outer wing 4 of sweepforward and vertical fin 5 etc. in fuselage 1, canard 2, the sweepforward as shown in Figure 1, 2.Wing 3 is inner in sweepforward installs telescoping mechanisms to drive the scalable outer wing of sweepforwards 4 electrodeless flexible, during high-performance cruise the scalable outer wing 4 of sweepforward is reduced to wing 3 the insides in the sweepforward, makes wing become low aspect ratio, the adaptation high-speed flight.When low speed cruises the scalable outer wing 4 of sweepforward is stretched out, make wing aspect ratio reach maximum, adapt to low-speed operations, the exhibition of the position change unmanned plane by the scalable outer wing 4 of control sweepforward is long, to adapt to the pneumatic requirement of the combat duty of flying.
Telescoping mechanism as shown in Figure 3, telescoping mechanism comprises driver train, hinge linkage, telescopic rail 67 and outer wing link span 64, telescopic rail 67, hinge linkage and outer wing link span 64 distribute in the driver train bilateral symmetry, driver train comprises motor 61, two synchronizer gears 62 and bearing 63, the guide-track groove of telescopic rail 67 for directly in sweepforward, processing on wing 3 twin beams, the rhombus-mechanism that hinge linkage is made up of some hinges 65 and pole 66, nose bar 68 is installed on the pole 66 of prismatic mechanism end, nose bar 68 is stuck in the telescopic rail 67, outer wing link span 64 is fixedly mounted on prismatic mechanism end, the scalable outer wing 4 of sweepforward is installed on the outer wing link span 64, the pole of prismatic mechanism front end is connected with synchronizer gear 62 gears, two synchronizer gears 62 are mediated mutually, one of them synchronizer gear 62 is connected with the transmission shaft of motor 61, motor 61 and two synchronizer gear 62 fixed installation bearings 63, bearing 63 is fixedly mounted on the axis of symmetry of fuselage 1, telescopic rail 67 front ends are installed inhibiting device, scalable outer wing 4 extended positions of restriction sweepforward.
The fore and aft motion mechanism of telescoping mechanism:
Telescoping mechanism adopts the integrated design of wing fuselage to realize.Adopt 3 groups of rhombus-mechanisms to realize the fore and aft motion of required about 580mm stroke, the connecting rod at two hinge places of main wing root is realized being synchronized with the movement by gear mesh, and the connecting rod by one of them hinge place of motor-driven rotates and drives entire mechanism and carry out dilatation.
Mechanism principle: 1) telescopic rail.Directly on the main wing twin beams, open guide-track groove, under the situation that does not increase structural weight, realize; 2) hinge linkage as shown in Figure 4.Left-right symmetric, the plane of symmetry are installed on the fuselage plane of symmetry and realize, outside direct connection is on outer wing.This mechanism is connected with telescopic rail, realizes that by the little nose bar that is installed on the outer wing wing root front and rear edge this nose bar is stuck in the telescopic rail groove.Realize the motion of outer wing on flexible direction thus, and limit the bending degree of freedom on its other several directions; 3) actuator.Employing is installed in the stepping motor on the fuselage.
Telescoping mechanism can not limit with said mechanism for other form, as long as it is flexible to satisfy the scalable outer wing 4 of sweepforward wing 3 in sweepforward.
The unspecified part of the present invention belongs to general knowledge as well known to those skilled in the art.
Claims (2)
1. a canard sweepforward becomes the telescopic wing aerodynamic arrangement of opening up long blade area, comprise fuselage (1), canard (2), wing and vertical fin (5), it is characterized in that: described wing comprises wing (3) and the scalable outer wing of sweepforward (4) in the sweepforward, the scalable outer wing of sweepforward (4) is by wing (3) internal connection in telescoping mechanism and the sweepforward, when unmanned plane Mach 2 ship 0.2, telescoping mechanism stretches the scalable outer wing of sweepforward (4) is reached wing (3) outside in the sweepforward, when unmanned plane Mach 2 ship 0.4, telescoping mechanism shrinks the scalable outer wing of sweepforward (4) is contracted in wing (3) inside in the sweepforward, and wherein the scalable outer wing of sweepforward (4) is 0.25～0.45 with the area ratio of the interior wing (3) of sweepforward.
2. a kind of canard sweepforward according to claim 1 becomes the telescopic wing aerodynamic arrangement of the long blade area of exhibition, it is characterized in that: described telescoping mechanism comprises driver train, hinge linkage, telescopic rail (67) and outer wing link span (64), telescopic rail (67), hinge linkage and outer wing link span (64) distribute in the driver train bilateral symmetry, driver train comprises motor (61), two synchronizer gears (62) and bearing (63), the guide-track groove of telescopic rail (67) for directly in sweepforward, processing on wing (3) twin beams, the rhombus-mechanism that hinge linkage is made up of some hinges (65) and pole (66), pole (66) going up at prismatic mechanism end installed nose bar (68), nose bar (68) is stuck in the telescopic rail (67), outer wing link span (64) is fixedly mounted on prismatic mechanism end, outer wing link span (64) is gone up the scalable outer wing of sweepforward (4) is installed, the pole of prismatic mechanism front end is connected with synchronizer gear (62) gear, two synchronizer gears (62) are mediated mutually, one of them synchronizer gear (62) is connected with the transmission shaft of motor (61), motor (61) and two synchronizer gears (62) fixed installation bearing (63), bearing (63) is fixedly mounted on the axis of symmetry of fuselage (1).
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| CN104015922A (en) * | 2014-04-11 | 2014-09-03 | 南京航空航天大学 | Unmanned aerial vehicle with rotary wing body and variable aspect ratio |
| CN105922831A (en) * | 2016-05-23 | 2016-09-07 | 吉林大学 | Bionic morphing wing of water-air amphibious aircraft and diving control method of bionic morphing wing |
| CN106542085A (en) * | 2015-09-23 | 2017-03-29 | 陈康 | The Electric aircraft of many shrouded propeller retractable wings and fuselage |
| CN107187581A (en) * | 2017-04-27 | 2017-09-22 | 深圳爱飞科技有限公司 | Retractable wing and aircraft |
| CN107651185A (en) * | 2017-08-21 | 2018-02-02 | 上海机电工程研究所 | It is a kind of to press the heart be with the supersonic aircraft of control adjustment |
| CN108082471A (en) * | 2017-11-20 | 2018-05-29 | 中国航空工业集团公司西安飞机设计研究所 | A kind of variant supersonic plane |
| CN108248826A (en) * | 2016-12-29 | 2018-07-06 | 北京卓翼智能科技有限公司 | A kind of telescopic wing mechanism, telescopic method and include its aircraft |
| CN108408023A (en) * | 2018-03-08 | 2018-08-17 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Flight control method, flight control system based on canard and aircraft |
| CN108516091A (en) * | 2018-04-02 | 2018-09-11 | 南京航空航天大学 | A kind of novel changable aerodynamic arrangement aircraft |
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| CN108995803A (en) * | 2018-06-08 | 2018-12-14 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of folding Waverider aerodynamic arrangement of supersonic airliner |
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| CN112319813A (en) * | 2020-12-01 | 2021-02-05 | 李勇霖 | Sweepforward duck type flying wing pneumatic layout unmanned aerial vehicle |
| CN112758307A (en) * | 2021-02-02 | 2021-05-07 | 中国人民解放军火箭军工程大学 | Aircraft and telescopic wing |
| CN114872881A (en) * | 2022-07-08 | 2022-08-09 | 西安羚控电子科技有限公司 | Large-stroke telescopic wing and unmanned aerial vehicle |
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| CN104015922A (en) * | 2014-04-11 | 2014-09-03 | 南京航空航天大学 | Unmanned aerial vehicle with rotary wing body and variable aspect ratio |
| CN104015922B (en) * | 2014-04-11 | 2016-08-24 | 南京航空航天大学 | Wing body rotates and becomes aspect ratio unmanned vehicle |
| CN106542085A (en) * | 2015-09-23 | 2017-03-29 | 陈康 | The Electric aircraft of many shrouded propeller retractable wings and fuselage |
| CN105922831A (en) * | 2016-05-23 | 2016-09-07 | 吉林大学 | Bionic morphing wing of water-air amphibious aircraft and diving control method of bionic morphing wing |
| CN108248826A (en) * | 2016-12-29 | 2018-07-06 | 北京卓翼智能科技有限公司 | A kind of telescopic wing mechanism, telescopic method and include its aircraft |
| CN107187581A (en) * | 2017-04-27 | 2017-09-22 | 深圳爱飞科技有限公司 | Retractable wing and aircraft |
| CN107651185A (en) * | 2017-08-21 | 2018-02-02 | 上海机电工程研究所 | It is a kind of to press the heart be with the supersonic aircraft of control adjustment |
| CN108082471A (en) * | 2017-11-20 | 2018-05-29 | 中国航空工业集团公司西安飞机设计研究所 | A kind of variant supersonic plane |
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| CN111003146B (en) * | 2019-12-26 | 2024-05-24 | 中国航空工业集团公司西安飞机设计研究所 | Scalable conformal wing |
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| CN112319813A (en) * | 2020-12-01 | 2021-02-05 | 李勇霖 | Sweepforward duck type flying wing pneumatic layout unmanned aerial vehicle |
| CN112758307A (en) * | 2021-02-02 | 2021-05-07 | 中国人民解放军火箭军工程大学 | Aircraft and telescopic wing |
| CN114872881A (en) * | 2022-07-08 | 2022-08-09 | 西安羚控电子科技有限公司 | Large-stroke telescopic wing and unmanned aerial vehicle |
| CN114872881B (en) * | 2022-07-08 | 2022-09-20 | 西安羚控电子科技有限公司 | Large-stroke telescopic wing and unmanned aerial vehicle |
| CN115476885A (en) * | 2022-09-27 | 2022-12-16 | 兰州交通大学 | High-speed train flank lift regulation and control device |
| CN115675548A (en) * | 2022-09-27 | 2023-02-03 | 兰州交通大学 | Symmetrical synchronous multi-step tread balance wing of high-speed train |
| CN115817872A (en) * | 2022-12-16 | 2023-03-21 | 南京理工大学 | Variable aerodynamic layout aircraft with gravity center adjusting function |
| CN115817872B (en) * | 2022-12-16 | 2024-05-24 | 南京理工大学 | Variable pneumatic layout aircraft with gravity center adjusting function |
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