CN101659321A - Inflatable wing with controllable sway trailing edge - Google Patents
Inflatable wing with controllable sway trailing edge Download PDFInfo
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- CN101659321A CN101659321A CN200910093522A CN200910093522A CN101659321A CN 101659321 A CN101659321 A CN 101659321A CN 200910093522 A CN200910093522 A CN 200910093522A CN 200910093522 A CN200910093522 A CN 200910093522A CN 101659321 A CN101659321 A CN 101659321A
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Abstract
The invention relates to an inflatable wing with a controllable sway trailing edge and is characterized in that: the inflatable wing adopts the structural design of split skin lacing wires and comprises a main wing, an auxiliary wing, a connection skin and a piezoelectric fibrous composite unit, wherein the main wing and the auxiliary wing are both of inflatable air bag structure, and form a common wing-shaped curve; the auxiliary wing is connected with the main wing as a body through wire joint; the inner parts of air bags of the main wing and the auxiliary wing are provided with a pluralityof lacing wires that divide the wing into bays which are mutually communicated; two ends of the connection skin are respectively bonded with the main wing and the auxiliary wing the two of which are connected together; and the piezoelectric fibrous composite unit is attached to the connection skin and the bottom edge of the piezoelectric fibrous composite unit is level with that of the connectionskin. The inflatable wing effectively solves the flight control problem of inflatable wings.
Description
Technical field
The present invention relates to a kind of wing, be specifically related to a kind of inflatable wing with controllable sway trailing edge, belong to the aerospace flight vehicle technical field.
Background technology
Inflatable wing is a kind of novel flexible wing with good development prospect.Inflatable wing can be folded in the fuselage in advance, is launched into the wing form when needing rapidly, for aircraft provides lift, but have when stacking volume little, in light weight, launch rapidly advantage such as repeated use.
The inflatable wing that great majority use is whole gas filed, does not have aileron, therefore uses the aircraft of inflatable wing to produce rolling moment by other means, and present research concentrates on the inflatable wing that makes non-firmization and produces distortion, so that lift-over control to be provided.
The propulsive effort that produces distortion adopts conventional steering wheel or intellectual material to provide more, as piezoelectric, marmem etc.Wherein piezoelectric has been studied and has been used to change arch and makes the leading edge trailing edge produce deformation.The quick response of piezoelectric and controllability make it have good effect.But the fragility of piezoelectric commonly used is big, with bulk material compatibility poor (when especially being applied to curved surface), easily cause damage and fracture etc. thereby be not suitable for large tracts of land at dividing range and use and arrange.
Summary of the invention
1, purpose: the purpose of this invention is to provide a kind of inflatable wing with controllable sway trailing edge, it uses piezoelectric fibre composite material as the propulsive effort element, to overcome the big deficiency that waits of piezoelectric ceramic fragility commonly used, this type piezo-electricity composite material has good toughness, is applicable to controlled objects such as curved surface.
In view of the rigidity of integral type inflatable wing is stronger, the deflection that piezoelectric fibre composite material provides is less, and the present invention has done improvement to the structure of inflatable wing.In the relevant position of trailing edge, shorten the lacing wire height, section is a connection structure, strengthens the rotating effect of rear edge part.
Simultaneously, in order to provide the piezoelectric fibre composite material paster required comparatively smooth surface, and the profile that keeps original wing, increase one deck high resiliency covering along the position of inflatable wing enveloping outer enclosure.
2, technical scheme
The inflatable wing of the controlled swing of a kind of trailing edge of the present invention adopts split type covering lacing wire structure design, and it is made up of host wing, secondary wing, connection covering, piezoelectric fibre composite material unit and corresponding control system;
Described host wing, secondary wing all are the air bags that processed by flexible high strength gummed cloth, have common wing curve; Secondary wing fuses by wire joint (being a connection on the section of aerofoil profile) and host wing; The air bag inside of host wing, secondary wing is provided with some lacing wires, wing is divided into the separation that is interconnected one by one.This lacing wire structure helps the tensioning aerofoil and forms needed aerofoil profile, can also increase the structural strength and the rigidity of wing simultaneously.Each bonding major and minor wing of described connection covering two ends couples together the two.Described piezoelectric fibre composite material unit is fitted in and connects on the covering, and its base is mutually neat with connection covering base.
Wherein, host wing and fuselage bonded assembly one end are provided with pore, and high pressure gas can enter wing by this pore.
Wherein, be realization inflation easily, the place that lacing wire slave wing root portion is arranged near wingtip always just disconnects, and makes whole wing in the mutual UNICOM of wingtip position energy, forms an integral gasbag.Such structure can make the carrying situation of whole wing more even, also can better prevent the blast distortion.
Wherein, the place that connection lead between host wing and the secondary wing is arranged near wingtip just disconnects, major and minor wing is realized at the wingtip place being communicated with, during inflation, high pressure gas can charge into whole wings then by host wing, and wing is launched in a short period of time, and keep predetermined pressure, the profile of inflatable wing is kept, for aircraft provides when flight required lift.
Wherein, connection lead central authorities also can have some apertures between the major and minor wing main body, are used for major and minor wing and realize being communicated with.
Wherein, secondary wing root is provided with pore, is connected with high-pressure gas circuit by flexible pipe, realizes the inflation of secondary wing.
Wherein, the inflation of secondary wing is perhaps realized by its combination in any mode by any one realization in above-mentioned three kinds of modes.
Wherein, the external voltage by control piezoelectric fibre composite material unit changes the length of piezoelectric fabric material, it is driven connect the flexible of covering.
Wherein, the secondary wing of flexible drive that connects covering swings up and down around its wire joint mechanism with host wing, thereby changes the aerodynamic configuration of whole wing, and it is controlled to realize that inflatable wing is flown.
3, beneficial effect
(1) inflatable wing with controllable sway trailing edge adopts split-type design, has increased wing pneumatic operation face, thereby has reached the purpose that the aircraft operating torque is provided;
(2) piezoelectric fibre composite material of Cai Yonging is fitted with being connected covering, transmits actuating force to wing by connecting covering, helps the cloth circuits, improves the wing aerodynamic configuration;
(3) host wing of inflatable wing with controllable sway trailing edge and secondary wing adopt a wire joint (be connected) on the section of aerofoil profile, and be efficient and compact, avoided the physical construction volume big, and complex structure is safeguarded the shortcoming of inconvenience.
Description of drawings
Figure 1 shows that structural representation of the present invention
Fig. 2 is the wing cross section of a present invention front view,
Fig. 3 is a birds-eye view of the present invention,
Fig. 4 is trailing edge distortion scheme drawing of the present invention.
Nomenclature is as follows among the figure:
1 host wing; 2 secondary wings; 3 connect covering; 4 piezoelectric fibre composite material unit; 5 lacing wires
The specific embodiment
Below in conjunction with accompanying drawing, technical scheme of the present invention is described further.
The inflatable wing of the controlled swing of a kind of trailing edge adopts split type covering lacing wire structure design, as shown in Figure 1, 2, 3, is made up of host wing 1, secondary wing 2, connection covering 3, piezoelectric fibre composite material unit 4 and corresponding control system;
Described host wing 1, secondary wing 2 all are the air bags that processed by flexible high strength gummed cloth, have common wing curve; Secondary wing fuses by wire joint (being a connection on the section of aerofoil profile) and host wing; The air bag inside of host wing, secondary wing is provided with some lacing wires 5, wing is divided into the separation that is interconnected one by one.This lacing wire structure helps the tensioning aerofoil and forms needed aerofoil profile, can also increase the structural strength and the rigidity of wing simultaneously.Each bonding major and minor wing of described connection covering 3 two ends couples together the two.Described piezoelectric fibre composite material unit 4 is fitted in and connects on the covering, and its base is mutually neat with connection covering base.
Wherein, host wing and fuselage bonded assembly one end are provided with the pore (not shown), and are connected with high-pressure gas circuit, and high pressure gas can enter wing by this pore.
Wherein, be realization inflation easily, the place that lacing wire slave wing root portion is arranged near wingtip always just disconnects, and makes whole wing in the mutual UNICOM of wingtip position energy, forms an integral gasbag.Such structure can make the carrying situation of whole wing more even, also can better prevent the blast distortion.
Wherein, the place that connection lead between host wing and the secondary wing is arranged near wingtip just disconnects, major and minor wing is realized at the wingtip place being communicated with, during inflation, high pressure gas can charge into whole wings then by host wing, and wing is launched in a short period of time, and keep predetermined pressure, the profile of inflatable wing is kept, for aircraft provides when flight required lift.
Connection lead central authorities have some apertures between the major and minor wing main body, are used for major and minor wing and realize being communicated with.
Wherein, secondary wing root is provided with the pore (not shown), is connected with high-pressure gas circuit by flexible pipe, realizes the inflation of secondary wing.
Wherein, the inflation of secondary wing is perhaps realized by its combination in any mode by any one realization in above-mentioned three kinds of modes.
Wherein, the external voltage by control piezoelectric fibre composite material unit changes the length of piezoelectric fabric material, it is driven connect the flexible of covering.
Wherein, the secondary wing of flexible drive that connects covering swings up and down around its wire joint mechanism with host wing, thereby changes the aerodynamic configuration of whole wing, and it is controlled to realize that inflatable wing is flown.
See also accompanying drawing 1,2,3,4, a kind of inflatable wing with controllable sway trailing edge of the present invention, its host wing links to each other with fuselage by the fuselage attaching parts, the position of this fuselage attaching parts respective hosts wing pore is provided with gas port, high pressure gas are injected among host wing, the secondary wing via gas port, reach specified air pressure, the wing aerodynamic configuration is formed, and certain intensity and rigidity are provided; Secondary wing not with the fuselage direct connection, external voltage by control piezoelectric fibre composite material unit, the piezoelectric fabric material is elongated or shortened, drive then and connect covering, make it secondary wing has been applied control effort, secondary wing is swung up and down around the connection lead of itself and host wing, thereby change the whole wing aerodynamic configuration, produce twist moment, handle the state of flight of aircraft.
Claims (8)
1, the inflatable wing of the controlled swing of a kind of trailing edge is characterized in that: this inflatable wing adopts split type covering lacing wire structure design, and it comprises host wing, secondary wing, connects covering, piezoelectric fibre composite material unit;
Described host wing, secondary wing all are inflatable airbag structures, have common wing curve; Secondary wing fuses by wire joint and host wing; The air bag inside of host wing, secondary wing is provided with some lacing wires, wing is divided into the separation that is interconnected one by one; Each bonding major and minor wing of described connection covering two ends couples together the two; Described piezoelectric fibre composite material unit is fitted in and connects on the covering, and its base is mutually neat with connection covering base.
2, the inflatable wing of the controlled swing of a kind of trailing edge according to claim 1 is characterized in that: this host wing and fuselage bonded assembly one end are provided with pore, and high pressure gas can enter wing by this pore.
3, the inflatable wing of the controlled swing of a kind of trailing edge according to claim 1, it is characterized in that: for realizing inflation easily, the place that lacing wire slave wing root portion is arranged near wingtip always just disconnects, and makes whole wing in the mutual UNICOM of wingtip position energy, forms an integral gasbag.
4, the inflatable wing of the controlled swing of a kind of trailing edge according to claim 1 is characterized in that: the place that the connection lead between host wing and the secondary wing is arranged near wingtip just disconnects, and major and minor wing is realized at the wingtip place being communicated with.
5, the inflatable wing of the controlled swing of a kind of trailing edge according to claim 1 is characterized in that: connection lead central authorities have some apertures between host wing, the secondary wing main body, are used for major and minor wing and realize being communicated with.
6, the inflatable wing of the controlled swing of a kind of trailing edge according to claim 1, it is characterized in that: the root of secondary wing is provided with pore, is connected with high-pressure gas circuit by flexible pipe, realizes the inflation of secondary wing.
7, the inflatable wing of the controlled swing of a kind of trailing edge according to claim 1 is characterized in that: the piezoelectric fibre composite material unit, under the control of voltage, realize the variation of piezoelectric fabric length of material, and drive the flexible of connection covering.
8, the inflatable wing of the controlled swing of a kind of trailing edge according to claim 1 is characterized in that: the controlled of trailing edge is by telescopic variation that connects covering and the realization that swings up and down that consequent power drives secondary wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910093522A CN101659321A (en) | 2009-10-12 | 2009-10-12 | Inflatable wing with controllable sway trailing edge |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910093522A CN101659321A (en) | 2009-10-12 | 2009-10-12 | Inflatable wing with controllable sway trailing edge |
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| CN101659321A true CN101659321A (en) | 2010-03-03 |
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| CN200910093522A Pending CN101659321A (en) | 2009-10-12 | 2009-10-12 | Inflatable wing with controllable sway trailing edge |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101870359A (en) * | 2010-06-02 | 2010-10-27 | 南京航空航天大学 | Method and device for driving trailing edge winglet of rotor blade of helicopter |
| CN102642611A (en) * | 2012-04-24 | 2012-08-22 | 哈尔滨工业大学 | Actively deformed stressed-skin structure based on pneumatic muscles |
| 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 |
| CN103192980A (en) * | 2013-04-09 | 2013-07-10 | 中国人民解放军国防科学技术大学 | Longitude and latitude network-based inflatable wing and manufacture method thereof |
| CN107458600A (en) * | 2017-08-10 | 2017-12-12 | 北京航空航天大学 | A kind of flapping wing that folding and unfolding is driven using inflation/deflation |
| 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 kind of flapping-wing aircraft wing of fluttering |
| CN113716035A (en) * | 2021-09-07 | 2021-11-30 | 南京航空航天大学 | Inflatable rotor blade and helicopter |
| CN113928551A (en) * | 2021-09-18 | 2022-01-14 | 南京航空航天大学 | Novel-structure combined type unmanned helicopter in near space and flight control method thereof |
| RU2821148C1 (en) * | 2023-08-23 | 2024-06-17 | Петр Николаевич Старков | Method of lifting to starting position of flex-wing of aircraft |
-
2009
- 2009-10-12 CN CN200910093522A patent/CN101659321A/en active Pending
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101870359A (en) * | 2010-06-02 | 2010-10-27 | 南京航空航天大学 | Method and device for driving trailing edge winglet of rotor blade of helicopter |
| CN102642611A (en) * | 2012-04-24 | 2012-08-22 | 哈尔滨工业大学 | Actively deformed stressed-skin structure based on pneumatic muscles |
| CN102642611B (en) * | 2012-04-24 | 2014-10-01 | 哈尔滨工业大学 | Actively deformed stressed-skin structure based on pneumatic muscles |
| 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 |
| CN103192980A (en) * | 2013-04-09 | 2013-07-10 | 中国人民解放军国防科学技术大学 | Longitude and latitude network-based inflatable wing and manufacture method thereof |
| 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 |
| 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 |
| CN107458600A (en) * | 2017-08-10 | 2017-12-12 | 北京航空航天大学 | A kind of flapping wing that folding and unfolding is driven using inflation/deflation |
| 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 kind of flapping-wing aircraft wing of fluttering |
| 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 |
| CN113716035A (en) * | 2021-09-07 | 2021-11-30 | 南京航空航天大学 | Inflatable rotor blade and helicopter |
| CN113716035B (en) * | 2021-09-07 | 2024-01-30 | 南京航空航天大学 | Inflatable rotor blade and helicopter |
| CN113928551A (en) * | 2021-09-18 | 2022-01-14 | 南京航空航天大学 | Novel-structure combined type unmanned helicopter in near space and flight control method thereof |
| RU2821148C1 (en) * | 2023-08-23 | 2024-06-17 | Петр Николаевич Старков | Method of lifting to starting position of flex-wing of aircraft |
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Open date: 20100303 |