CN102167155A - Aircraft with twistable wings - Google Patents
Aircraft with twistable wings Download PDFInfo
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- CN102167155A CN102167155A CN2011100813944A CN201110081394A CN102167155A CN 102167155 A CN102167155 A CN 102167155A CN 2011100813944 A CN2011100813944 A CN 2011100813944A CN 201110081394 A CN201110081394 A CN 201110081394A CN 102167155 A CN102167155 A CN 102167155A
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- 239000002131 composite material Substances 0.000 claims abstract description 27
- 239000000835 fiber Substances 0.000 claims abstract description 24
- 230000007935 neutral effect Effects 0.000 claims abstract description 9
- 230000004913 activation Effects 0.000 claims description 14
- 238000005452 bending Methods 0.000 claims description 12
- 230000005611 electricity Effects 0.000 claims description 9
- 230000011218 segmentation Effects 0.000 claims description 7
- 230000008901 benefit Effects 0.000 abstract description 9
- 239000000463 material Substances 0.000 abstract description 6
- 238000012423 maintenance Methods 0.000 abstract description 2
- 230000007246 mechanism Effects 0.000 abstract description 2
- 229920001746 electroactive polymer Polymers 0.000 abstract 2
- 239000000446 fuel Substances 0.000 abstract 1
- 230000008859 change Effects 0.000 description 7
- 238000000034 method Methods 0.000 description 7
- 230000008569 process Effects 0.000 description 6
- 238000005096 rolling process Methods 0.000 description 4
- 230000018109 developmental process Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 210000003050 axon Anatomy 0.000 description 2
- 230000005684 electric field Effects 0.000 description 2
- 239000004744 fabric Substances 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 239000004677 Nylon Substances 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 230000002452 interceptive effect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 229920001778 nylon Polymers 0.000 description 1
- 230000035484 reaction time Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
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Abstract
本发明提供一种智能材料驱动或机械驱动的速度快、航程远、油耗低、可垂直起降、可空中悬停的机翼可扭转飞行器。它是由机身、分段弯曲可扭转机翼、电致活性聚合物蒙皮、片状宏纤维压电复合材料条、变形蜂窝填芯、反转平台和可变桨距螺旋桨发动机组成的，两台可变桨距螺旋桨发动机对称装在机翼后缘，电致活性聚合物蒙皮作为机翼蒙皮，片状宏纤维压电复合材料条在机翼中性层上，变形蜂窝填芯填充在机翼蒙皮和片状宏纤维压电复合材料条之间，反转平台置于机身内部旋转中心处。本发明利用智能驱动器作为机翼扭转的驱动源，其质量轻、机构简单、效率高、维修方便，通过机翼扭转可以快速在平飞和悬停的飞行方式中切换。
The invention provides an intelligent material-driven or mechanically driven aircraft with twistable wings, which has the advantages of fast speed, long range, low fuel consumption, vertical take-off and landing, and hovering in the air. It is composed of fuselage, segmented curved twistable wing, electroactive polymer skin, sheet macrofiber piezoelectric composite strip, deformed honeycomb core, reversing platform and variable pitch propeller engine, Two variable-pitch propeller engines are symmetrically installed on the trailing edge of the wing, the electroactive polymer skin is used as the wing skin, the sheet-like macrofiber piezoelectric composite material strip is on the wing neutral layer, and the deformed honeycomb core is filled Filled between the wing skin and the sheet-like macro-fiber piezoelectric composite strip, the inversion platform is placed at the center of rotation inside the fuselage. The invention uses an intelligent driver as the driving source for wing twisting, which has light weight, simple mechanism, high efficiency and convenient maintenance, and can quickly switch between level flight and hovering flight mode through wing twisting.
Description
(1) technical field
The present invention relates to aeronautical and space technology, is exactly that a kind of wing can reverse aircraft specifically.
(2) background technology
The fixed-wing aircraft is since coming out, and advantage just 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 does not then have this shortcoming, but not enough be because of 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 a 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 does not have dependence to runway, and has the advantage that can hover; Compare with conventional helicopters, vertically taking off and landing flyer has much higher forward flight speed, and has bigger voyage.Aircraft with vertical takeoff and landing or hovering ability can be carried out and comprise that battle reconnaissance monitors, transmits information in real time; Air-borne early warning and coordinative command; Target indication, correction impact, combat success assessment, radio relay; Disturb, destroy enemy traffic guidance system, radar system, important goal is implemented a lot of tasks such as air strike.This class aircraft has and has high low-speed performance, maneuverability, voyage strong, advantage that compatible with environment is strong far away, disguised concurrently, can become the arms aircraft behind the equipment precision guided weapon, improves the assault ability to ground and naval target greatly.
In the last few years, the vertical takeoff and landing technology was applied to unmanned vehicle and had obtained bigger 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 by some mechanical mechanisms rotor commutation or fuselage to be commutated to realize hovering and the flat conversion that flies.
(3) summary of the invention
But the object of the present invention is to provide a kind of intellectual material to drive or mechanically operated speed is fast, voyage is far away, but the wing of the low vertical takeoff and landing hovering of oil consumption can reverse aircraft.
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 are formed is formed all-wing aircraft layout 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, the advantage that has fixed-wing aircraft and helicopter class aircraft simultaneously, compare with existing vertically taking off and landing flyer, have light weight, wing structure is simple, reliability is high, development cost is low, easy operation, airworthiness advantages of higher, thereby can improve the operational performance and the safety of armament systems widely, reduce weapon risk and the maintenance cost in the process under arms.Intellectual material actuator based on electric activation poly-mer and grand fiber piezo-electricity composite material of the present invention has that speed of response is fast, stability of motion good, energy density is high, reliability is high and 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 propelling energy 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 civil and military structural systems such as fly bomb and naval vessel submarine, for safe, intellectuality, the self adaptationization of implementation structure system provides strong basic guarantee, the various performances of structural system when work have been improved widely.
(4) description of drawings
Fig. 1 is an integral structure scheme drawing of the present invention;
But Fig. 2 is the twisted wings section-drawing;
Fig. 3 is the grand fiber piezo-electricity composite material of a sheet bar distribution schematic diagram;
Fig. 4 is wing twist and variable camber figure;
Fig. 5 is a state of flight scheme drawing 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) are formed, fuselage (1) but form all-wing aircraft layout 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 rotate around the shaft by rotating shaft by motor-driven, when wing can reverse aircraft and 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 down at specific extra electric field, and piezoelectric fabric produces mechanical strees, and the grand fiber piezo-electricity composite material of sheet bar shows initiatively crooked ability.The flexural deformation of the grand fiber piezo-electricity composite material of independent sheet bar can drive corresponding wing section bending, realize wing segmentation bending, 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 the camber and the aerofoil profile of wing like this, increase 1ift-drag ratio.This grand fiber piezo-electricity composite material have flexible good, formedness is strong, electromechanical coupling factor is high, lightweight, 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 is induced down at extra electric field, produces bending, stretching or compressive deformation by the material internal structural change.So be provided with, electric activation poly-mer covering shows the initiatively ability of torsional deflection.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 big 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 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 coilable aircraft of a kind of wing of the present invention, when taking off, left and right sides wing twist direction is opposite, 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 wing can reverse aircraft will produce downward thrust as screw propeller, when thrust during, just realize taking off vertically greater than self gravitation.Change pitch simultaneously 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 wing can reverse aircraft and become 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 controlling aircraft, lift-over and driftage.Wing can reverse aircraft and fly in the journey flat, one side driving engine becomes negative pitch, aircraft begins driftage, and produce the trend of rolling, this moment, this side wing structure was reversed (this torsional direction is opposite with the rotor torsional direction), produce the moment balance aircraft opposite, constantly adjust the wing twist angle, make the aircraft orbit with rolling moment, and the initial flat speed that flies direction of minimizing, when reaching critical speed, left and right oppositely changes windup-degree (changing to the rotor torsional direction) rapidly, strengthens engine thrust, complete machine will spin around fixing axon, produce lift,, realize that wing can reverse hovering of aircraft by changing windup-degree and engine thrust.
Embodiment 5: wing can reverse the fuselage of aircraft and be 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 the grand fiber piezo-electricity composite material of sheet bar up and down, 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.Wing can reverse two meters of aircraft span, 5 kilograms of take-off weights.When taking off, left and right sides wing twist direction is opposite, 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, wing can reverse aircraft will produce downward thrust as screw propeller, when roll rate reached 300rpm, thrust just realized taking off vertically greater than self gravitation.Change pitch simultaneously 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 wing can reverse aircraft and become 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 controlling aircraft, lift-over and driftage.Wing can reverse aircraft and fly in the journey flat, one side driving engine becomes negative pitch, aircraft begins driftage, and produce the trend of rolling, this moment, this side wing structure was reversed (this torsional direction is opposite with the rotor torsional direction), produce the moment balance aircraft opposite, constantly adjust the wing twist angle, make the aircraft orbit with rolling moment, and the initial flat speed that flies direction of minimizing, when reaching critical speed, left and right oppositely changes windup-degree (changing to the rotor torsional direction) rapidly, strengthens engine thrust, complete machine will spin around fixing axon, produce lift,, realize that wing can reverse hovering of aircraft by changing windup-degree and engine thrust.
Claims (1)
1. a wing can reverse aircraft, 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) are formed, it is characterized in that: fuselage (1) but form all-wing aircraft layout 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), and counter-rotating platform (6) places fuselage interior centre of gration place.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110081394 CN102167155B (en) | 2011-04-01 | 2011-04-01 | Aircraft with turnable wings |
Applications Claiming Priority (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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| CN102167155A true CN102167155A (en) | 2011-08-31 |
| CN102167155B 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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Cited By (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 the embedded dynamic folding variant 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 |
| CN103171757A (en) * | 2013-04-13 | 2013-06-26 | 哈尔滨工业大学 | Self-adaptive rear-edge driving device applying piezoelectric fiber composite materials |
| CN103241364A (en) * | 2013-05-24 | 2013-08-14 | 哈尔滨工业大学 | Control device of self-adaptive trailing edge structure based on MFC (microfunction circuit) |
| CN104590558A (en) * | 2014-12-04 | 2015-05-06 | 湖南大学 | Piezoelectric composite material helicopter blade structure and control method thereof |
| 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 |
| CN108557054A (en) * | 2018-04-20 | 2018-09-21 | 大连理工大学 | Control system and control method suitable for large aspect ratio wing aircraft |
| CN109533280A (en) * | 2018-12-04 | 2019-03-29 | 南京航空航天大学 | Coilable inflatable wing structure and its design method |
| CN109823534A (en) * | 2019-03-05 | 2019-05-31 | 西北工业大学太仓长三角研究院 | A flapping wing for a flapper |
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Cited By (15)
| 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 the embedded dynamic folding variant 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 |
| CN103171757A (en) * | 2013-04-13 | 2013-06-26 | 哈尔滨工业大学 | Self-adaptive rear-edge driving device applying piezoelectric fiber composite materials |
| CN103241364A (en) * | 2013-05-24 | 2013-08-14 | 哈尔滨工业大学 | Control device of self-adaptive trailing edge structure based on MFC (microfunction circuit) |
| 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) |
| CN104590558A (en) * | 2014-12-04 | 2015-05-06 | 湖南大学 | Piezoelectric composite material helicopter blade structure and control method thereof |
| 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 |
| CN108557054A (en) * | 2018-04-20 | 2018-09-21 | 大连理工大学 | Control system and control method suitable for large aspect ratio wing aircraft |
| 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 |
| CN109533280A (en) * | 2018-12-04 | 2019-03-29 | 南京航空航天大学 | Coilable inflatable wing structure and its design method |
| CN109533280B (en) * | 2018-12-04 | 2022-04-08 | 南京航空航天大学 | Twistable inflatable wing structure and design method thereof |
| CN109823534A (en) * | 2019-03-05 | 2019-05-31 | 西北工业大学太仓长三角研究院 | A flapping wing for a flapper |
| 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 |
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| CN102167155B (en) | 2013-01-09 |
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