CN105253305B - A kind of detachable experiment wing structure of leading edge based on piezoelectricity deicing system - Google Patents
A kind of detachable experiment wing structure of leading edge based on piezoelectricity deicing system Download PDFInfo
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- CN105253305B CN105253305B CN201510652738.0A CN201510652738A CN105253305B CN 105253305 B CN105253305 B CN 105253305B CN 201510652738 A CN201510652738 A CN 201510652738A CN 105253305 B CN105253305 B CN 105253305B
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- 238000013461 design Methods 0.000 description 5
- 238000012360 testing method Methods 0.000 description 4
- 230000000875 corresponding effect Effects 0.000 description 3
- 239000011888 foil Substances 0.000 description 3
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- 238000005265 energy consumption Methods 0.000 description 1
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Abstract
A kind of detachable experiment wing structure of leading edge based on piezoelectricity deicing system, comprising two leading edge parts, leading portion crossbeam, two back segment parts and a back segment crossbeam, the leading edge part and back segment crossbeam are separately positioned on the two ends of back segment part, back segment part is connected with leading edge part by leading portion crossbeam, described two leading edge parts are parallel to each other, described two leading edge parts are symmetrical along the longitudinal centre line of the experiment wing structure, and the spacing between described two leading edge parts is arbitrarily adjustable.Leading edge part of the present invention can be dismantled and adjusted, and can be constituted different wings and be opened up wing model to size, thus can realize the diversity to the research of piezoelectricity de-icing method according to the different adjustment wing structure of research object.
Description
Technical field
The present invention relates to a kind of detachable experiment wing structure of leading edge based on piezoelectricity deicing system, belong to aircraft reality
Test the technical field of structure.
Background technology
Aircraft in the cloud layer containing super-cooling waterdrop during flight, windward before such as wing, empennage lifting surface, the air intake duct of surface
Edge etc. can be frozen, and serious threat is caused to flight safety, it is therefore desirable to take rational anti-icing, deicing measure.For existing
For the related anti-de-icing method in stage, piezoelectricity de-icing method as a kind of new de-icing method, because its energy consumption is low, efficiency
Advantage high, with vast potential for future development.
With piezoelectricity de-icing method to the piezoelectricity deicing system for combining, it is mainly used in some and small-sized is not suitable for calorifics deicing
The ice detachment of the plane wing surfaces of method.And the leading edge of a wing is used as the main icing area of aircraft, in anti-deicing system research
In have research status very high and researching value, in piezoelectricity deicing system, piezoelectric actuator is mainly distributed and the leading edge of a wing
Position, therefore corresponding research for air-foil leading edge is just particularly important, the difference for air-foil leading edge is fixed
The research of the piezoelectricity deicing effect under form and different size, it is necessary to which wing structure needs certain changeability and can adjust
Property, while can have the adaptability of research for different freezing environments.Also, the big portion of the research of piezoelectricity deicing system now
Divide the research for concentrating on flat board, research object and research model are simple, and little for the research of Practical Wings aerofoil profile, therefore,
Piezoelectricity de-icing method and deicing effect under the premise of research air-foil seem particularly critical.
The content of the invention
It is detachable the invention discloses a kind of leading edge based on piezoelectricity deicing system in order to solve above-mentioned problem
Experiment wing structure, there is provided a kind of detachable wing structure of leading edge, different wing dimensions, different wing can be adapted to
The requirement of the piezoelectricity de-icing method research under leading edge fixed form and icing tunnel environment.
A kind of detachable experiment wing structure of leading edge based on piezoelectricity deicing system, experiment wing structure surface paving
Covering is provided with, the covering includes being laid on the leading edge of a wing covering of the leading edge of a wing and is laid on the trailing edge illiteracy of trailing edge
Skin, the leading edge of a wing skin-surface pastes piezoelectric patches, encourages piezoelectric patches to vibrate by being powered to piezoelectric patches, and then encourages whole
Leading edge of a wing covering vibrates, and reaches deicing purpose,
The experiment wing structure includes two leading edge parts, leading portion crossbeam, two back segment parts and a back segment horizontal strokes
Beam,
The leading edge part and back segment crossbeam are separately positioned on the two ends of back segment part, and back segment part passes through with leading edge part
Leading portion crossbeam is connected,
Described two leading edge parts are parallel to each other, described two leading edge parts along the experiment wing structure longitudinal center
Line is symmetrical, and the spacing between described two leading edge parts is arbitrarily adjustable.
The leading portion crossbeam is an overall structure, and it includes upper cross plate, lower cross plate and connection upper cross plate and lower cross plate
Intermediate plate, the upper cross plate lower surface and lower cross plate upper surface are parallel to each other, and intermediate plate is vertically set on upper cross plate and lower cross plate
Longitudinal center's line position, the lateral cross section of the leading portion crossbeam is in I-shaped shape.
The leading edge part is in respectively " convex " with the connection end of leading portion crossbeam and back segment part and the connection end of leading portion crossbeam
Word shape.
The connection end of the leading edge part and leading portion crossbeam is inserted into the leading portion crossbeam of I-shaped shape, leading edge part with
The upper and lower surface of the connection end of leading portion crossbeam and end face are fitted with upper cross plate, lower cross plate and intermediate plate respectively, and respectively by connecting
Fitting is connected,
The connection end of the back segment part and leading portion crossbeam is inserted into the leading portion crossbeam of I-shaped, back segment part with it is preceding
The upper and lower surface of section crossbeam connection end and end face are fitted with upper cross plate, lower cross plate and intermediate plate respectively, and pass through connector respectively
It is connected.
The upper cross plate and lower cross plate are provided with several screwed holes, the upper cross plate towards a lateral edges of leading edge part
Screwed hole with lower cross plate is corresponded to up and down successively, and the position that the leading edge part is fitted with upper cross plate and lower cross plate is also equipped with spiral shell
Pit, and the screwed hole of leading edge part is consistent with the screwed hole specification of upper cross plate and lower cross plate, is revolved by the screw thread in screwed hole
Enter bolt to be connected leading edge part with upper cross plate and lower cross plate, the leading edge part can with upper cross plate and lower cross plate it is any on
Under corresponding screwed hole be bolted.
Operation principle of the invention is：
Because real aircraft wing dimension is than larger, for some Related Experimental Studies, the wing of large-size without
Method realizes the correlation theory research under laboratory condition, it is therefore desirable to carry out the scaling of wing model, i.e., Practical Wings according to
Certain proportion is zoomed in and out, and is scaled the less wing model of size, and this process is referred to as model contracting ratio.The less wing of size
Model is representative for studying the correlated phenomena of Practical Wings, for deicing mode, small size wing model
The deicing research process of research Practical Wings structure can be met, therefore, the invention can meet the piezoelectricity deicing of Practical Wings
Research process.
Practical Wings structure contains truss, wing cover and other associated support drive mechanisms.But for wing piezoelectricity
For vibration deicing, because real aircraft ice field is distributed mainly on leading edge of a wing region, therefore for the pressure of the leading edge of a wing
Electric oscillation research is just particularly important, so for the invention, it is integrally-built to be mainly designed to for leading edge portion
Piezoelectricity deicing research, it may be said that front edge area is important survey region.The invention propose wing structure be really
A kind of frame structure, for the unique design of frame structure, not only meets the experimental study under experiment condition, and meet reality
The structure distribution situation of wing.Because wing cover does not have invention, therefore certain configuration aspects are carried out to wing structure
Invention, the change of structure can then cause the change of covering size, and then meet the deicing research of different size lower wing structure.
The structure design of the invention is that the invention of experimental study structure is carried out on the basis of Practical Wings structural requirement is met, and is met
The process of laboratory research.
The leading edge of a wing is emphasis survey region, and wing icing and ice detachment are only relevant to leading edge of a wing part, rear end
Part does not influence on it, therefore for rear airfoil end part with regard to not required specifically, as long as ensureing certain structure shape
The effect of formula, i.e. rear end part is to ensure the complete of whole wing structure.Therefore leading edge portion is detachable, adjustable
Process do not influenceed by rear end part.It is considered that a support structures of the rear end part for leading edge portion, in practical study
In, regulation leading edge portion structure can complete whole process of experimental, it is not necessary to which rear end part is adjusted.Due to wing
Ice field is distributed mainly on leading edge portion, and the size of leading edge portion is different, and wing is different in the icing amount of leading edge, therefore only needs
Study leading edge portion, and piezoelectric vibration de-icing element is also distributed across skins front edges part, thus rear end part size
Wing icing is not influenceed with size, it is not necessary to specifically paid close attention to.
For piezoelectric vibration de-icing method, principle is shaking using the piezoelectric patches being pasted onto on leading edge of a wing covering
It is dynamic, the structural vibration of whole leading edge of a wing covering is encouraged, and then reach the purpose of deicing.For skins front edges vibration, shake
Dynamic form and effect can be influenceed by covering fixed form and covering size.Covering fixes both sides and fixes four sides, covering
Vibrating effect is different, is also different for the effect of deicing, it is therefore desirable to design the dismountable wing structure of leading edge, this
Sample can just change the fixed form of covering by changing leading edge portion structure type, and then study under different fixed forms
Covering vibrating effect.
The covering of Practical Wings is made up of the small covering of certain size, similar to Pork-pieces " patch " structure.It is right
For large-sized wing, the size of monolithic covering is also larger；For the wing of small size, the size of monolithic covering compared with
It is small.Wing cover size is previously noted to have an impact covering vibration, and width is different, and the icing amount of the leading edge of a wing is also
It is different, and wing cover size determines by wing structure, therefore the wing structure in the invention, can be by changing leading edge
Structure spacing in the direction of the width, realizes the change in the direction of the width of covering size, and then meet research purpose.
And for Practical Wings, truss structure and the wing cover of the inside can be regarded as by multiple similar modules
Composition, therefore the wing structure of the invention can regard a part of Practical Wings as.Because piezoelectric vibration device is distribution
Leading edge of a wing structure deicing mode with the ad-hoc location of whole Practical Wings skins front edges, therefore a research part can expire
The research process of sufficient whole wing.The research model different for other width dimensions, is referred to the wing structure of the invention
Design is designed, and can realize changing on width by two ways：One is section beam width side before and after changing
Upward size.Two can be the wing structure of the multiple same sections of design, then carry out splicing on width.Either
Which kind of process, the wing structure form that the invention is related to is constant.Thus whole invention is met described in technical requirements not
With the research purpose in fixed form and different width dimensions.
The beneficial effects of the invention are as follows：
1st, the research process and deicing compliance test result mistake for the piezoelectricity de-icing method under the conditions of experiment wing structure are realized
Journey；
2nd, leading edge part can be dismantled and adjusted, and realize the diversity to the research of piezoelectricity de-icing method；
3rd, due to test wing structure exterior region part adjustability, can constitute different wings open up to（Width）The machine of size
Wing model, thus the research contents of piezoelectricity de-icing method according to the different adjustment wing structure of research object, can be enriched.
Brief description of the drawings
Fig. 1 is structural representation of the invention,
Fig. 2 is the structural representation of leading edge part of the present invention,
Fig. 3 is the structural representation of leading portion crossbeam of the present invention,
Fig. 4 is the structural representation of back segment part of the present invention,
Fig. 5 is the structural representation of back segment crossbeam of the present invention,
Reference numerals list：1-leading edge part, 2-leading portion crossbeam, 3-back segment part, 4-back segment crossbeam.
Specific embodiment
With reference to the accompanying drawings and detailed description, the present invention is furture elucidated.It should be understood that following specific embodiments are only
For illustrating the present invention rather than limitation the scope of the present invention.
It is visible with reference to accompanying drawing, a kind of detachable experiment wing structure of this leading edge based on piezoelectricity deicing system, the reality
Test wing structure surface and be equipped with covering, the covering includes being laid on the leading edge of a wing covering of the leading edge of a wing and is laid on wing
The trailing edge covering of trailing edge, the leading edge of a wing skin-surface pastes piezoelectric patches, and piezoelectric patches is encouraged by being powered to piezoelectric patches
Vibration, and then whole leading edge of a wing covering vibration is encouraged, reach deicing purpose.
The experiment wing structure includes two 2, two, leading portion crossbeam back segment parts 3 of leading edge part 1, and a back segment
Crossbeam 4, the leading edge part 1 and back segment crossbeam 4 are separately positioned on the two ends of back segment part 3, back segment part 3 and leading edge part 1
Connected by leading portion crossbeam 2, installed by the connection of each part, form the experiment wing with Practical Wings structure scaled down
Structure.
Described two leading edge parts 1 are parallel to each other, in longitudinal direction of described two leading edge parts 1 along the experiment wing structure
Heart line is symmetrical, and the spacing between described two leading edge parts 1 is arbitrarily adjustable.By changing the spacing between two leading edge parts 1,
The change width of experiment wing structure leading edge portion is realized, the simulated experiment of the leading edge of a wing under various width is realized.
The leading portion crossbeam 2 includes the intermediate plate of upper cross plate, lower cross plate and connection upper cross plate and lower cross plate, the upper horizontal stroke
Plate and lower cross plate are parallel to each other, and intermediate plate is vertically set on longitudinal center's line position of upper cross plate and lower cross plate, and the leading portion is horizontal
The lateral cross section of beam 2 is in I-shaped shape.The end of leading edge part 1 and the end of back segment part 3 are inserted respectively into I-shaped
The both sides of shape, and then leading edge part 1 and back segment part 3 are connected with leading portion crossbeam 2 respectively, this kind of connection of position relationship
It is fixed.
The leading edge part 1 is in respectively with the connection end of leading portion crossbeam 2 with the connection end of leading portion crossbeam 2 and back segment part 3
"convex" shaped shape.The leading edge part 1 is inserted into the leading portion crossbeam 2 of I-shaped shape with the connection end of leading portion crossbeam 2, leading edge
Part 1 is fitted with upper cross plate, lower cross plate and intermediate plate respectively with the upper and lower surface of the connection end of leading portion crossbeam 2 and end face, and point
It is not connected by connector, the back segment part 3 is inserted into the leading portion crossbeam of I-shaped with the connection end of leading portion crossbeam 2
In 2, back segment part 3 is pasted with upper cross plate, lower cross plate and intermediate plate respectively with the upper and lower surface of the connection end of leading portion crossbeam 2 and end face
Close, and be connected by connector respectively.This kind of link position relation, stable connection, good stability.
The upper cross plate and lower cross plate are provided with several screwed holes, the upper horizontal stroke towards a lateral edges of leading edge part 1
The screwed hole of plate and lower cross plate is corresponded to up and down successively, and the position that the leading edge part 1 is fitted with upper cross plate and lower cross plate is also provided with
There is screwed hole, and the screwed hole of leading edge part 1 is consistent with the screwed hole specification of upper cross plate and lower cross plate, by the spiral shell in screwed hole
With upper cross plate and lower cross plate be connected leading edge part 1 by line precession bolt, and the leading edge part 1 can be with upper cross plate and lower cross plate
Any corresponding screwed hole up and down is bolted.Bolt connection is that a kind of conventional simple can realize repeatedly connecting and tearing open
The connected mode unloaded.
Technological means disclosed in the present invention program is not limited only to the technological means disclosed in above-mentioned technological means, also includes
Constituted technical scheme is combined by above technical characteristic.
With above-mentioned according to desirable embodiment of the invention as enlightenment, by above-mentioned description, relevant staff is complete
Various changes and amendments can be carried out without departing from the scope of the technological thought of the present invention' entirely.The technology of this invention
Property scope is not limited to the content on specification, it is necessary to its technical scope is determined according to right.
Claims (5)
1. the detachable experiment wing structure of a kind of leading edge based on piezoelectricity deicing system, experiment wing structure surface laying
There is covering, the covering includes being laid on the leading edge of a wing covering of the leading edge of a wing and is laid on the trailing edge illiteracy of trailing edge
Skin, the leading edge of a wing skin-surface pastes piezoelectric patches, encourages piezoelectric patches to vibrate by being powered to piezoelectric patches, and then encourages whole
Leading edge of a wing covering vibrates, and reaches deicing purpose,
It is characterized in that after the experiment wing structure is comprising two leading edge parts, a leading portion crossbeam, two back segment parts and one
Section crossbeam,
The leading edge part and back segment crossbeam are separately positioned on the two ends of back segment part, and back segment part passes through leading portion with leading edge part
Crossbeam is connected,
Described two leading edge parts are parallel to each other, described two leading edge parts along the experiment wing structure longitudinal centre line pair
Claim, the spacing between described two leading edge parts is adjustable.
2. the detachable experiment wing structure of a kind of leading edge based on piezoelectricity deicing system according to claim 1, its
Be characterized in the leading portion crossbeam it is an overall structure, it is included in upper cross plate, lower cross plate and connection upper cross plate and lower cross plate
Between plate, the upper cross plate lower surface and lower cross plate upper surface be parallel to each other, and intermediate plate is vertically set on upper cross plate and lower cross plate
Longitudinal center's line position, the lateral cross section of the leading portion crossbeam is in I-shaped shape.
3. the detachable experiment wing structure of a kind of leading edge based on piezoelectricity deicing system according to claim 2, its
It is characterized in the leading edge part and the connection end of leading portion crossbeam and back segment part and the connection end of leading portion crossbeam are in respectively " convex " word
Shape.
4. the detachable experiment wing structure of a kind of leading edge based on piezoelectricity deicing system according to claim 3, its
Be characterized in the leading edge part and the connection end of leading portion crossbeam is inserted into the leading portion crossbeam of I-shaped shape, leading edge part with it is preceding
The upper and lower surface of the connection end of section crossbeam and end face are fitted with upper cross plate, lower cross plate and intermediate plate respectively, and respectively by connection
Part is connected, and the back segment part is inserted into the leading portion crossbeam of I-shaped with the connection end of leading portion crossbeam, back segment part
Fitted with upper cross plate, lower cross plate and intermediate plate respectively with the upper and lower surface of leading portion crossbeam connection end and end face, and respectively by connecting
Fitting is connected.
5. the detachable experiment wing structure of a kind of leading edge based on piezoelectricity deicing system according to claim 4, its
Be characterized in the upper cross plate and lower cross plate is provided with several screwed holes towards a lateral edges of leading edge part, the upper cross plate and
The screwed hole of lower cross plate is corresponded to up and down successively, and the position that the leading edge part is fitted with upper cross plate and lower cross plate is also equipped with screw thread
Hole, and the screwed hole of leading edge part is consistent with the screwed hole specification of upper cross plate and lower cross plate, is threaded into by screwed hole
With upper cross plate and lower cross plate be connected leading edge part by bolt, the leading edge part can with upper cross plate and lower cross plate it is any up and down
Corresponding screwed hole is bolted.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510652738.0A CN105253305B (en) | 2015-10-10 | 2015-10-10 | A kind of detachable experiment wing structure of leading edge based on piezoelectricity deicing system |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510652738.0A CN105253305B (en) | 2015-10-10 | 2015-10-10 | A kind of detachable experiment wing structure of leading edge based on piezoelectricity deicing system |
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| CN105253305A CN105253305A (en) | 2016-01-20 |
| CN105253305B true CN105253305B (en) | 2017-05-31 |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105923145A (en) * | 2016-03-25 | 2016-09-07 | 哈尔滨飞机工业集团有限责任公司 | Detachable leading edge structure of airplane |
| CN110606208B (en) * | 2019-09-26 | 2020-12-18 | 山东大学 | Giant magnetostrictive material aircraft wing ice preventing and removing device and control system and application thereof |
| CN112623187B (en) * | 2020-12-30 | 2022-11-29 | 吉林大学 | Detachable and replaceable wing-shaped trailing edge device and manufacturing method thereof |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4458865A (en) * | 1980-12-09 | 1984-07-10 | Lockheed Corporation | Nose-torquer electro-impulse deicing systems |
| US4501398A (en) * | 1980-12-09 | 1985-02-26 | Lockheed Corporation | Beam balancer electro-impulse deicing systems |
| CN102570368B (en) * | 2012-01-16 | 2014-11-05 | 南京航空航天大学 | Traveling wave type piezoelectric material vibration anti-icing/deicing device based on in-plane or out-of-plane mode and deicing method |
| CN102941924B (en) * | 2012-11-20 | 2016-02-10 | 南京航空航天大学 | A kind of piezoelectric elasticity ripple de-icing method |
| DE102013020496A1 (en) * | 2013-12-11 | 2015-06-11 | Airbus Defence and Space GmbH | Actuator mounting method and manufacturing method for an ice protection device and mounting device |
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