CN103017998A - Wing-type test piece - Google Patents
Wing-type test piece Download PDFInfo
- Publication number
- CN103017998A CN103017998A CN2012104932631A CN201210493263A CN103017998A CN 103017998 A CN103017998 A CN 103017998A CN 2012104932631 A CN2012104932631 A CN 2012104932631A CN 201210493263 A CN201210493263 A CN 201210493263A CN 103017998 A CN103017998 A CN 103017998A
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- end wall
- bourdon
- testpieces
- tube
- sleeve pipe
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Abstract
The invention discloses a wing-type test piece. The wing-type test piece comprises a wing-type shell and a flute-shaped tubular test piece, wherein the wing-type shell comprises a first end wall part, a second end wall part corresponding to the first end wall part, and a side wall part, and the first end wall part, the second end wall part and the side wall part form a containing cavity; the flute-shaped tubular test piece is contained inside the containing cavity and used for protecting the wing-type shell against ice; and two ends of the flute-shaped tubular test piece are arranged on the first end wall part and the second end wall part respectively in a rotating manner. According to the wing-type test piece, the position of the flute-shaped tubular test piece in an anti-icing cavity of the wing-type test piece can be adjusted, so that the optimal position or the position near optimal position of the flute-shaped tubular test piece in the anti-icing cavity can be conveniently calculated and verified.
Description
Technical field
The present invention relates to the technical field of aircraft hot air anti-icing system icing tunnel test, relate to particularly a kind of Airfoil Testing spare.
Background technology
In order computation model to be provided Data support and anti-icing system usefulness to be checked etc., usually design the bourdon's tube testpieces and be fixed to and carry out the icing tunnel test in the Airfoil Testing spare.Yet, in the icing tunnel test of existing aircraft hot air anti-icing system, all the position of bourdon's tube testpieces is fixed on a certain position in the anti-icing chamber of Airfoil Testing spare, namely this bourdon's tube testpieces is not movable.
As everyone knows, when the anti-icing system development, the parameters such as the position of bourdon's tube testpieces in anti-icing chamber, gas orifice size, angle, row, pitch-row, array pitch need comprehensive assessment, obtain a preferred result.If the bourdon's tube testpieces can't translation and/or rotation, then just can't regulate the bourdon's tube testpieces to obtain the bourdon's tube testpieces with respect to the optimum position of anti-icing cavity space.
Summary of the invention
For the position of bourdon's tube testpieces in the anti-icing chamber of Airfoil Testing spare can be regulated obtain this bourdon's tube testpieces in anti-icing chamber the optimum position or near the optimum position, the invention discloses a kind of Airfoil Testing spare, it comprises: the aerofoil profile housing, it comprises the first end wall, second end wall and the side wall portion relative with the first end wall, and the first end wall, the second end wall and side wall portion form container cavity; And the bourdon's tube testpieces, it is interior for anti-icing to the aerofoil profile housing that it is contained in container cavity, and the two ends of bourdon's tube testpieces are set to respectively on the first end wall and the second end wall rotationally.
Particularly, be fixed with the first sleeve pipe on the first end wall of aerofoil profile housing, be fixed with the second sleeve pipe on the second end wall of aerofoil profile housing, the two ends of bourdon's tube testpieces are nested with respectively in the first sleeve pipe and the second sleeve pipe.
More specifically, Airfoil Testing spare comprises handle and nut, the end of handle is furnished with screw thread, the bourdon's tube testpieces is provided with the through hole suitable with handle, the second sleeve pipe upwards offer in week have the first slit of in predetermined angular range, rotating for handle and with centrosymmetric second slit of the first slit along the second sleeve pipe, handle passes the first slit, through hole and the second slit successively, and nut thread connects on the screw thread of fastening bolt so that relative the second sleeve pipe of bourdon's tube testpieces is fixed.
Preferably, the other scale that also is furnished with of the first slit of this second sleeve pipe and/or the second slit.
Description of drawings
In order to explain the present invention, its illustrative embodiments will be described with reference to the drawings hereinafter,
In the accompanying drawing:
Fig. 1 schematically shows the skeleton view of Airfoil Testing spare of the present invention;
Fig. 2 schematically shows the partial enlarged drawing on the plane of Fig. 1;
The bourdon's tube testpieces that Fig. 3 schematically shows Airfoil Testing spare of the present invention with and the sleeve pipe at two ends;
Similar features among the different figure is by similar Reference numeral indication.
Embodiment
Fig. 1 schematically shows the skeleton view of Airfoil Testing spare of the present invention, and Fig. 2 schematically shows the partial enlarged drawing on the plane of Fig. 1.
In conjunction with Fig. 1 and Fig. 2, Airfoil Testing spare includes position adjustments assembly 100, bourdon's tube testpieces 200 and aerofoil profile housing 300.Wherein, this position adjustments assembly 100 is used for bourdon's tube testpieces 200 is carried out position adjustments.Wherein, alleged bourdon's tube testpieces 200 be in anti-icing system icing tunnel test for the anti-icing chamber of simulating wing in real bourdon's tube and the test element be processed into.At this, what be placed to that icing tunnel tests is the Airfoil Testing spare that special design is made, and this aerofoil profile housing 300 is testpieces of the aerofoil profile of wing slat that is virtually reality like reality.Why real bourdon's tube is arranged corresponding bourdon's tube testpieces and corresponding to the aerofoil profile of wing slat the aerofoil profile housing is set, this is because icing tunnel is tested unlikely take true aircraft as subjects, in order to verify the reliability of anti-icing system, can design and make corresponding testpieces in the practice.
This aerofoil profile housing 300 comprises the first end wall 302, second end wall 304 and the side wall portion 306 relative with this first end wall 302, and this first end wall 302, the second end wall 304 and side wall portion 306 form the container cavity that holds bourdon's tube testpieces 200 and position adjustments assembly 100.
Have at least two retaining thread circular hole (not shown) on the first end wall 302 of this aerofoil profile housing 300, its position is corresponding with draw-in groove 106,108 circular hole respectively, also have fixedly circular hole (not shown) of at least two screw threads on the second end wall 304 of Airfoil Testing spare 300, its position is corresponding with draw-in groove 118,120 circular hole respectively.
Bourdon's tube testpieces 200 two ends are nested with respectively in the first sleeve pipe 402 and the second sleeve pipe 404, and no-float, guarantee its relative sealing before the test, and the first sleeve pipe 402 and the second sleeve pipe 404 wherein an end be welded on the first cover plate 102 and the second cover plate 104, then the first cover plate 102 is fixed on the first end wall 302 of aerofoil profile housing 300 by two bolt (not shown), wherein, bolt pass in the draw-in groove 106 a circular hole (for example, first circular hole from left number) and another bolt pass the draw-in groove 108 one with the circular hole of aforementioned circular hole mirror image (for example, first circular hole from left number corresponding with aforesaid first circular hole), thus these the first cover plate 102 relative first end wall 302 firmly fix together; The second cover plate 104 is fixed on the second end wall 304 of Airfoil Testing spare 300 by two bolts 128,130, wherein, bolt 128 pass in the draw-in groove 118 a circular hole (for example, first circular hole from left number as shown in the figure) and another bolt 130 pass the draw-in groove 120 one with the circular hole of aforementioned circular hole mirror image (for example, first circular hole from left number corresponding with aforesaid first circular hole), thus these the second cover plate 104 relative second end wall 304 firmly fix together.
Like this, bourdon's tube testpieces 200 just is fixed on the position that is positioned at Airfoil Testing spare 300 by the first cover plate 102 and the second cover plate 104, namely, the leftmost position with respect to aerofoil profile housing 300 as shown in the figure, when needs are regulated the position of bourdon's tube testpieces 200 to the right so that bourdon's tube testpieces 200 during further from side wall portion 306 leading edge of aerofoil profile housing 300, can become flexible each bolt then the first cover plate 102 and the second cover plate 104 is promoted each bolt to be locked to respectively in draw-in groove 106,108,118, second circular hole of 120 or the 3rd circular hole again to the right.
When testing in the icing tunnel that Airfoil Testing spare is put into the various meteorological conditions of simulation, it is anti-icing to be used for aerofoil profile housing 300 that this bourdon's tube testpieces 200 namely ejects the relatively high air-flow of temperature by a plurality of spray-holes that arrange on it.When bourdon's tube testpieces 200 needs more close or during away from side wall portion 306 leading edge of aerofoil profile housing 300, can regulate as described above so that the hot gas performance optimal performance of this bourdon's tube testpieces 200.
Those skilled in the art should be appreciated that be arranged on the first cover plate 102 and the second cover plate 104 each draw-in groove can be arranged on three of diverse location independently circular hole substitute.Selectable, can also be provided with gear in a side of the first cover plate 102 close the first end wall 302, correspondingly, be provided with tooth bar in the first end wall 302, add in addition again securing member, by this, but 300 translations of the first cover plate 102 opposed wings shell bodies, similarly, also can between the second cover plate 104 and the second end wall 304, adopt the structure of gear and tooth bar.In any case arrange, have at least two locus as long as can realize bourdon's tube testpieces 200 opposed wings shell bodies 300.
Those skilled in the art are further appreciated that aforesaid bolt 128,130 also can substitute with other securing members.More preferably, draw-in groove 106,108 and in addition the straight basic at two draw-in grooves 118, each place of 120 be parallel to leading edge of a wing line.Particularly, this aerofoil profile housing 300 is the slat model, and the first end wall 302 and the second end wall 304 are respectively the slat end rib of slat model.
The bourdon's tube testpieces that Fig. 3 schematically shows Airfoil Testing spare of the present invention with and the sleeve pipe at two ends.
In conjunction with Fig. 1-Fig. 3, the two ends of the bourdon's tube testpieces 200 in this aerofoil profile housing 300 can also be rotated relative to the first cover plate 102, the second cover plate 104.Easy speech, the two ends of this bourdon's tube testpieces 200 are set to respectively on the first end wall 302 and the second end wall 304 rotationally.
Particularly, be fixed with the first sleeve pipe 402 on the first end wall 302 of this aerofoil profile housing 300, be fixed with the second sleeve pipe 404 on the second end wall 304 of this aerofoil profile housing 300, the two ends of this bourdon's tube testpieces 200 are nested with respectively in this first sleeve pipe 402 and the second sleeve pipe 404.
More specifically, this Airfoil Testing spare also comprises handle 406 and nut 408, wherein, handle 406 is cylindric and is furnished with endways screw thread, this bourdon's tube testpieces 200 is provided with the through hole (not shown) suitable with handle 406, this second sleeve pipe 404 upwards offer in week have the first slit 410 of in predetermined angular range, rotating for handle 406 and with the centrosymmetric second slit (not shown) of the first slit 410 along the second sleeve pipe 404, this handle 406 passes the first slit 410 successively, through hole and the second slit, nut 408 are threaded on this handle 406 so that bourdon's tube testpieces 200 relative these second sleeve pipes 404 are fixing.Flow for fear of the hot gas that affects significantly bourdon's tube testpieces 200 inside, the external diameter that handle 406 can be positioned at bourdon's tube inside arranges to such an extent that less and the external diameter that will be positioned at bourdon's tube testpieces 200 outsides arrange relatively largely, like this, the boss that produces owing to reducing just in time can be stuck on the outside surface of bourdon's tube testpieces 200.
Preferably, the other scale 412 that also is furnished with of the first slit 410 of this second sleeve pipe 404 and/or the second slit.
Like this, when needs rotate this bourdon's tube testpieces 200, the experimenter can unclamp this nut 408, and hand-held this handle 406 rotates this bourdon's tube testpieces 200 counterclockwise or deasil to certain scale 412, and this bourdon's tube testpieces 200 just rotates in the angular range that this first slit 410 and the second slit limit.In addition, because the angle that the first slit 410 and the second slit limit is very little, so bourdon's tube testpieces 200 of the present invention can be realized fine setting.
The present invention is limited to the illustrative embodiments that presents never in any form in instructions and accompanying drawing.All combinations of the embodiment that illustrates and describe (part) are interpreted as clearly to incorporate within this instructions and be interpreted as clearly and fall within the scope of the present invention.And in the scope of the present invention of summarizing such as claims, a lot of distortion are possible.In addition, any reference marker in claims should be configured to limit the scope of the invention.
Claims (4)
1. Airfoil Testing spare, it comprises:
The aerofoil profile housing, it comprises the first end wall, second end wall and the side wall portion relative with described the first end wall, described the first end wall, described the second end wall and described side wall portion form container cavity; And
The bourdon's tube testpieces, it is interior for anti-icing to described aerofoil profile housing that it is contained in described container cavity, and the two ends of described bourdon's tube testpieces are set to respectively on described the first end wall and the second end wall rotationally.
2. Airfoil Testing spare according to claim 1, it is characterized in that, be fixed with the first sleeve pipe on the first end wall of described aerofoil profile housing, be fixed with the second sleeve pipe on the second end wall of described aerofoil profile housing, the two ends of described bourdon's tube testpieces are nested with respectively in described the first sleeve pipe and described the second sleeve pipe.
3. Airfoil Testing spare according to claim 2, it is characterized in that, described Airfoil Testing spare comprises handle and nut, the end of described handle is furnished with screw thread, described bourdon's tube testpieces is provided with the through hole suitable with described handle, described the second sleeve pipe upwards offer in week have the first slit of in predetermined angular range, rotating for described handle and with centrosymmetric second slit of described the first slit along described the second sleeve pipe, described handle passes described the first slit successively, described through hole and described the second slit, described nut thread connect on the screw thread of described fastening bolt so that relatively described the second sleeve pipe of described bourdon's tube testpieces is fixed.
4. Airfoil Testing spare according to claim 3 is characterized in that, the other scale that also is furnished with of the first slit of this second sleeve pipe and/or the second slit.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012104932631A CN103017998A (en) | 2012-11-28 | 2012-11-28 | Wing-type test piece |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012104932631A CN103017998A (en) | 2012-11-28 | 2012-11-28 | Wing-type test piece |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103017998A true CN103017998A (en) | 2013-04-03 |
Family
ID=47966857
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012104932631A Pending CN103017998A (en) | 2012-11-28 | 2012-11-28 | Wing-type test piece |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103017998A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106644354A (en) * | 2017-02-20 | 2017-05-10 | 西北工业大学 | Miniature wing surface electric heating deicing system icing wind tunnel test device |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100176243A1 (en) * | 2009-01-15 | 2010-07-15 | Cessna Aircraft Company | Anti-Icing Piccolo Tube Standoff |
| CN101832446A (en) * | 2005-09-14 | 2010-09-15 | 悉尼水资源公司 | Attachment device for a sewer pipe cleaning system |
| US20120187254A1 (en) * | 2011-01-26 | 2012-07-26 | Wollaston Timothy | Aircraft slat assembly with anti-icing system |
| CN102756809A (en) * | 2012-07-07 | 2012-10-31 | 北京航空航天大学 | Opened type airplane hot-gas anti-icing test device |
-
2012
- 2012-11-28 CN CN2012104932631A patent/CN103017998A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101832446A (en) * | 2005-09-14 | 2010-09-15 | 悉尼水资源公司 | Attachment device for a sewer pipe cleaning system |
| US20100176243A1 (en) * | 2009-01-15 | 2010-07-15 | Cessna Aircraft Company | Anti-Icing Piccolo Tube Standoff |
| US20120187254A1 (en) * | 2011-01-26 | 2012-07-26 | Wollaston Timothy | Aircraft slat assembly with anti-icing system |
| CN102756809A (en) * | 2012-07-07 | 2012-10-31 | 北京航空航天大学 | Opened type airplane hot-gas anti-icing test device |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106644354A (en) * | 2017-02-20 | 2017-05-10 | 西北工业大学 | Miniature wing surface electric heating deicing system icing wind tunnel test device |
| CN106644354B (en) * | 2017-02-20 | 2019-02-05 | 西北工业大学 | A kind of small-sized aerofoil electrical heating deicing system icing mnncl tcst device |
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Application publication date: 20130403 |