CN102167155B - Aircraft with turnable wings - Google Patents
Aircraft with turnable wings Download PDFInfo
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- CN102167155B CN102167155B CN 201110081394 CN201110081394A CN102167155B CN 102167155 B CN102167155 B CN 102167155B CN 201110081394 CN201110081394 CN 201110081394 CN 201110081394 A CN201110081394 A CN 201110081394A CN 102167155 B CN102167155 B CN 102167155B
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Abstract
The invention provides an intelligent material driven or mechanical driven aircraft with turnable wings, and the aircraft provided by the invention has the advantages of high speed, long voyage, low oil consumption, capability of VTOL (vertical take-of and landing), and capability of hovering. The aircraft comprises an aircraft body, sectional bending turnable wings, electroactive polymer skins, sheet macro-fiber piezoelectric composite material bars, deformed honeycomb fillers, a reversal platform and variable pitch propeller engines, wherein the two variable pitch propeller engines are symmetrically mounted on the rear edges of the wings, the electroactive polymer skins are taken as wing skins, the sheet macro-fiber piezoelectric composite material bars are arranged on the neutral layers of the wings, the spaces between the wing skins and the sheet macro-fiber piezoelectric composite material bars are filled with the deformed honeycomb fillers, and the reversal platform is placed at a rotary center inside the aircraft body. According to the invention, an intelligent driver is utilized as the driving source for wing turning, and the aircraft has the advantages of light weight, simple mechanism, high efficiency and convenience for maintenance, and can be switched rapidly in flying modes of level flaying and hovering through wing turning.
Description
(1) technical field
The present invention relates to aeronautical and space technology, is exactly a kind of aircraft with turnable wings specifically.
(2) background technology
Fixed Wing AirVehicle is since coming out, and just advantage fast with speed, that voyage is far away develops rapidly, but takeoff and landing must rely on runway or ejector, and stops owing to not revolving, and is difficult to target is carried out uninterrupted scouting.But helicopter class hovering flight device is then without this shortcoming, but not enough be because being subjected to the restriction of rotor, flying speed is difficult to above 300km/h, voyage is also shorter.In recent years, some countries had started one upsurge, and competitively the feature performance benefit of development collection fixed wing aircraft and helicopter is vertically taking off and landing flyer all over the body.The accurate definition of vertically taking off and landing flyer (VTOL) is: can take off with zero velocity/land, possess hover capabilities, and can be with the mode horizontal flight of fixed wing aircraft.Compare with conventional airplane, vertically taking off and landing flyer without dependence, and has the advantage that can hover to runway; Compare with conventional helicopters, vertically taking off and landing flyer has much higher forward flight speed, and has larger voyage.Aircraft with vertical takeoff and landing or hovering ability can be carried out and comprise that battle reconnaissance monitors, in real time transmission of information; Air-borne early warning and coordinative command; Target indication, correction impact, combat success assessment, radio relay; Disturb, destroy enemy's communication commanding system, radar system, important goal is implemented a lot of tasks such as air strike.This class aircraft have advantages of have concurrently high low-speed performance, maneuverability, voyage far away, disguised strong, compatible with environment is strong, can become the arms aircraft behind the equipment precision guided weapon, greatly improves the assault ability to ground and naval target.
In the last few years, the vertical takeoff and landing technology was applied to unmanned vehicle and had obtained larger development.Compare with manned aircraft, vertical take-off and landing unmanned aerial vehicle size and power requirement are little, and flying speed is low.Present most VUAV belongs to rotor class aircraft.All be to make rotor commutation or fuselage commutate to realize hovering and the flat conversion that flies by some mechanical mechanisms.
(3) summary of the invention
But the object of the present invention is to provide a kind of intellectual material to drive or but mechanically operated speed is fast, voyage is far away, the aircraft with turnable wings of the low vertical takeoff and landing hovering of oil consumption.
The object of the present invention is achieved like this: it is by fuselage, but segmentation bending twisted wings, electricity activation poly-mer covering, the grand fiber piezo-electricity composite material of sheet bar, the distortion honeycomb is filled out core, but the fuselage that counter-rotating platform and variablepiston airscrew engine form forms the Flying-wing aircraft with twisted wings, two variablepiston airscrew engine symmetries are contained in trailing edge, electricity activation poly-mer covering is as wing cover, the grand fiber piezo-electricity composite material of sheet bar is on the wing neutral line, the distortion honeycomb is filled out core and is filled between wing cover and the grand fiber piezo-electricity composite material of the sheet bar, and counter-rotating platform places fuselage interior centre of gration place.
But a kind of twisted wings aircraft of the present invention, have advantages of simultaneously Fixed Wing AirVehicle and helicopter class aircraft, compare with existing vertically taking off and landing flyer, have that quality is light, wing structure is simple, reliability is high, development cost is low, easy operation, airworthiness advantages of higher, thereby can improve widely operational performance and the safety of armament systems, reduce under arms risk and the maintenance cost in the process of weapon.Intellectual material actuator based on electric activation poly-mer and grand fiber piezo-electricity composite material of the present invention has fast response time, stability of motion is good, energy density is high, reliability is high and the advantage such as lower density.The slickness and the continuity that have kept the covering top layer before and after the wing twist of the present invention, in the twist process to drive can require low.The present invention not only can be applied to aircraft, utilize correlation technique of the present invention can also be used for robot, S. A. Load System, adjustable wing and patrol the civil and military structural systems such as fly bomb and naval vessel submarine, for implementation structure security of system, intellectuality, self adaptation provide strong basic guarantee, the various performances of structural system when work have been improved widely.
(4) description of drawings
Fig. 1 is integral structure schematic diagram of the present invention;
But Fig. 2 is the twisted wings section-drawing;
Fig. 3 is the grand fiber piezo-electricity composite material of sheet bar distribution schematic diagram;
Fig. 4 is wing twist and variable camber figure;
Fig. 5 is state of flight schematic diagram of the present invention.
(5) specific embodiment
The invention will be further described for example below in conjunction with accompanying drawing.
Embodiment 1: in conjunction with Fig. 1～Fig. 2, but a kind of twisted wings aircraft of the present invention, it is by fuselage (1), but segmentation bending twisted wings (2), electricity activation poly-mer covering (3), the grand fiber piezo-electricity composite material of sheet bar (4), the distortion honeycomb is filled out core (5), counter-rotating platform (6) and variablepiston airscrew engine (7) form, fuselage (1) but form the Flying-wing aircraft with segmentation bending twisted wings (2), two variablepiston airscrew engines (7) symmetry is contained in trailing edge, electricity activation poly-mer covering (3) is as wing cover, the grand fiber piezo-electricity composite material of sheet bar (4) is on the wing neutral line, the distortion honeycomb is filled out core (5) and is filled between wing cover and the grand fiber piezo-electricity composite material of the sheet bar (4), counter-rotating platform (6) places fuselage interior centre of gration place, be connected with body also and can be rotated around the shaft by motor-driven by rotating shaft, when aircraft with turnable wings is in spin states, counter-rotating platform makes itself and ground keep relative static with the same angular velocity opposite spin.Arrange navigation control device and earth observation equipment on the counter-rotating platform.
Embodiment 2: in conjunction with Fig. 2～Fig. 4, but a kind of twisted wings aircraft of the present invention, the grand fiber piezo-electricity composite material of described sheet bar is formed by piezoelectric fabric and fourchette electrode interactive structure.The grand fiber piezo-electricity composite material of a plurality of sheets bar is parallel to each other and prolongs spanwise and be attached on the wing neutral line.The grand fiber piezo-electricity composite material of above-mentioned sheet bar is induced lower at specific extra electric field, piezoelectric fabric produces mechanical strees, and the grand fiber piezo-electricity composite material of sheet bar shows initiatively crooked ability.It is crooked that the flexural deformation of the grand fiber piezo-electricity composite material of independent sheet bar can drive corresponding wing section, realize that the wing segmentation is crooked, the flexural deformation of the grand fiber piezo-electricity composite material of a plurality of sheets bar can drive wing combination bending and integrally bending, can change like this camber and the aerofoil profile of wing, increase 1ift-drag ratio.This grand fiber piezo-electricity composite material have flexible good, formedness is strong, electromechanical coupling factor is high, lightweight, the advantage such as easy to manufacture, and can be applicable to curved-surface structure.
Embodiment 3: in conjunction with Fig. 2～Fig. 4, skin material of the present invention is electric activation poly-mer, and the grand fiber piezo-electricity composite material of a plurality of sheets bar is parallel to each other and prolongs spanwise and be attached on the wing neutral line, and the distortion honeycomb is filled out core and is filled between covering and the neutral line.Above-mentioned electric activation poly-mer under extra electric field is induced, produces bending, stretching or compressive deformation by the material internal structural change.So arrange, electric activation poly-mer covering shows the ability of active twist distortion.The grand fiber piezo-electricity composite material of the sheet bar bending direction otherwise deformed that the wing front and rear edge is laid drives wing twist.Electricity activation poly-mer covering and the combined action of the grand fiber piezo-electricity composite material of sheet bar make wing can produce larger twist angle, change the angle of attack of wing.The distortion honeycomb is filled out the distortion that core is coordinated electric activation poly-mer and grand fiber piezo-electricity composite material, bears aerodynamic loading, keeps wing shapes.This electricity activation poly-mer has the characteristics such as super large distortion, high efficiency, ultrashort reaction time, high fatigue life, high cycle number.
Embodiment 4: in conjunction with Fig. 1～Fig. 5, the aircraft of a kind of turnable wings of the present invention, when taking off, left and right sides wing twist opposite direction produces the opposite angle of attack, one side trailing edge becomes leading edge, one side variablepiston airscrew engine becomes negative pitch, and two driving engines produce reverse couple makes the aircraft rotation, and aircraft with turnable wings will produce downward thrust as screw propeller, when thrust during greater than self gravitation, just realize taking off vertically.Change simultaneously pitch at vertical uplift both sides driving engine behind the certain altitude, make and freely stop fast, in dropping process, left and right sides wing reverses to same direction, and left and right sides wing camber changes simultaneously, produce the identical angle of attack and aerofoil profile, the both sides driving engine becomes positive pitch again, produces thrust in the same way, and aircraft with turnable wings becomes normal flying wing type aircraft, accumulating rate in dropping process becomes the flat state that flies.The subtle change of the left and right sides wing angle of attack and camber can produce the pitching of control torque control aircraft, lift-over and driftage.Aircraft with turnable wings flies in the journey flat, one side driving engine becomes negative pitch, aircraft begins driftage, and generation rolling trend, this moment, this side wing structure was reversed (this torsional direction is opposite with the rotor torsional direction), produce the moment balance aircraft opposite with rolling moment, reconditioner wing twisting angle constantly, make the aircraft orbit, and the initial flat speed that flies direction of minimizing, when reaching critical speed, left and right oppositely changes rapidly windup-degree (changing to the rotor torsional direction), strengthens engine thrust, complete machine will spin around fixing axon, produce lift, by changing windup-degree and engine thrust, realize hovering of aircraft with turnable wings.
Embodiment 5: the fuselage of aircraft with turnable wings is made by the high-strength carbon fiber composite material, but the neutral line of segmentation bending twisted wings is made and is connected on the fuselage by elasticity good aluminium flake or nylon material, neutral line is distributed with up and down the grand fiber piezo-electricity composite material of sheet bar, electricity activation poly-mer covering is coated on the distortion honeycomb and fills out the smooth aerofoil surface of formation on the core, and two brushless motor symmetries that the variablepiston screw propeller is installed are contained in trailing edge.Two meters of the aircraft with turnable wings spanes, 5 kilograms of take-off weights.When taking off, left and right sides wing twist opposite direction, produce 5 ° of opposite angles of attack, one side trailing edge becomes leading edge, and this side variablepiston screw propeller becomes negative pitch, and two brushless motors produce reverse couple makes the aircraft rotation, aircraft with turnable wings will produce downward thrust as screw propeller, when roll rate reached 300rpm, thrust just realized taking off vertically greater than self gravitation.Change simultaneously pitch at vertical uplift both sides screw propeller behind the certain altitude, make and freely stop fast, in dropping process, left and right sides wing reverses to same direction, and left and right sides wing camber changes simultaneously, produce the identical angle of attack and aerofoil profile, the both sides screw propeller becomes positive pitch again, produces thrust in the same way, and aircraft with turnable wings becomes normal flying wing type aircraft, accumulating rate in dropping process becomes the flat state that flies when speed reaches 60km/h.The subtle change of the left and right sides wing angle of attack and camber can produce the pitching of control torque control aircraft, lift-over and driftage.Aircraft with turnable wings flies in the journey flat, one side driving engine becomes negative pitch, aircraft begins driftage, and generation rolling trend, this moment, this side wing structure was reversed (this torsional direction is opposite with the rotor torsional direction), produce the moment balance aircraft opposite with rolling moment, continuous reconditioner wing twisting angle, make the aircraft orbit, and the initial flat speed that flies direction of minimizing, when reaching critical speed, left and right oppositely changes rapidly windup-degree (changing to the rotor torsional direction), strengthens engine thrust, complete machine will spin around fixing axon, produce lift, by changing windup-degree and engine thrust, realize hovering of aircraft with turnable wings.
Claims (1)
1. aircraft with turnable wings, it is by fuselage (1), but segmentation bending twisted wings (2), electricity activation poly-mer covering (3), the grand fiber piezo-electricity composite material of sheet bar (4), the distortion honeycomb is filled out core (5), counter-rotating platform (6) and variablepiston airscrew engine (7) form, it is characterized in that: the grand fiber piezo-electricity composite material of described sheet bar (4) is formed by piezoelectric fabric and fourchette electrode interactive structure, fuselage (1) but form the Flying-wing aircraft with segmentation bending twisted wings (2), two variablepiston airscrew engines (7) symmetry is contained in trailing edge, electricity activation poly-mer covering (3) is as wing cover, the grand fiber piezo-electricity composite material of sheet bar (4) is on the wing neutral line, the distortion honeycomb is filled out core (5) and is filled between wing cover and the grand fiber piezo-electricity composite material of the sheet bar (4), counter-rotating platform (6) places fuselage interior centre of gration place, be connected with body and pivoted by motor-driven by rotating shaft, when aircraft with turnable wings is in spin states, counter-rotating platform (6) is with the same angular velocity opposite spin, make itself and ground keep relative static, upper navigation control device and the earth observation equipment arranged of counter-rotating platform (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110081394 CN102167155B (en) | 2011-04-01 | 2011-04-01 | Aircraft with turnable wings |
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| Application Number | Priority Date | Filing Date | Title |
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| CN 201110081394 CN102167155B (en) | 2011-04-01 | 2011-04-01 | Aircraft with turnable wings |
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| CN102167155A CN102167155A (en) | 2011-08-31 |
| CN102167155B true CN102167155B (en) | 2013-01-09 |
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| CN 201110081394 Active CN102167155B (en) | 2011-04-01 | 2011-04-01 | Aircraft with turnable wings |
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Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103123293A (en) * | 2012-12-24 | 2013-05-29 | 中国航空工业空气动力研究院 | Drive-embedded dynamic folding morphing wing |
| CN103158859A (en) * | 2013-04-07 | 2013-06-19 | 哈尔滨工业大学 | Transformable inflatable extensible wing driven by piezoelectric fiber composite material |
| CN103171757B (en) * | 2013-04-13 | 2015-07-29 | 哈尔滨工业大学 | A kind of self adaptation trailing edge actuating device using piezoelectric fibre composite material |
| CN103241364B (en) * | 2013-05-24 | 2015-05-06 | 哈尔滨工业大学 | Control device of self-adaptive trailing edge structure based on MFC (microfunction circuit) |
| CN104590558B (en) * | 2014-12-04 | 2017-05-24 | 湖南大学 | Control method for piezoelectric composite material helicopter blade structure |
| CN105691594A (en) * | 2016-01-19 | 2016-06-22 | 高萍 | Novel control method and device for flying wing aircraft |
| CN106741820A (en) * | 2016-12-20 | 2017-05-31 | 中国科学院长春光学精密机械与物理研究所 | A kind of VTOL fixed-wing unmanned vehicle |
| CN108557054B (en) * | 2018-04-20 | 2021-03-26 | 大连理工大学 | Control method of control system suitable for high-aspect-ratio wing aircraft |
| CN109533280B (en) * | 2018-12-04 | 2022-04-08 | 南京航空航天大学 | Twistable inflatable wing structure and design method thereof |
| CN109823534B (en) * | 2019-03-05 | 2020-11-13 | 西北工业大学太仓长三角研究院 | Flapping wing for ornithopter |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101028867A (en) * | 2007-03-30 | 2007-09-05 | 哈尔滨工业大学 | Aircraft with changeable wing shape |
| CN101513931A (en) * | 2009-03-27 | 2009-08-26 | 哈尔滨工业大学 | Deformable aerofoil |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040245393A1 (en) * | 2002-12-09 | 2004-12-09 | University Of Florida | Bendable wing for micro air vehicle |
| GB0624580D0 (en) * | 2006-12-08 | 2007-01-17 | Imp Innovations Ltd | Aerofoil member |
| US8464979B2 (en) * | 2009-06-02 | 2013-06-18 | Sunstar IM | Foldable swan-wings aircraft |
-
2011
- 2011-04-01 CN CN 201110081394 patent/CN102167155B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101028867A (en) * | 2007-03-30 | 2007-09-05 | 哈尔滨工业大学 | Aircraft with changeable wing shape |
| CN101513931A (en) * | 2009-03-27 | 2009-08-26 | 哈尔滨工业大学 | Deformable aerofoil |
Non-Patent Citations (3)
| Title |
|---|
| 冷劲松等.新型智能复合材料的研究及其应用.《第十五届全国复合材料学术会议论文集（上册）》.2008,全文. * |
| 新型人工关节驱动器材料研究;王莉等;《科技创新导报》;20101120;全文 * |
| 王莉等.新型人工关节驱动器材料研究.《科技创新导报》.2010,全文. |
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| CN102167155A (en) | 2011-08-31 |
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