CN108844710B - Icing wind tunnel test ice shape measuring method - Google Patents
Icing wind tunnel test ice shape measuring method Download PDFInfo
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- CN108844710B CN108844710B CN201810768271.XA CN201810768271A CN108844710B CN 108844710 B CN108844710 B CN 108844710B CN 201810768271 A CN201810768271 A CN 201810768271A CN 108844710 B CN108844710 B CN 108844710B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
- G01M9/065—Measuring arrangements specially adapted for aerodynamic testing dealing with flow
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
Abstract
The invention discloses an icing wind tunnel test ice shape measuring method, which comprises the steps of utilizing a metal sheet provided with a notch consistent with the wing profile, pushing the metal sheet along the horizontal direction, enabling a wing to be clamped into the notch along the notch of the metal sheet, drawing out the metal sheet after the metal sheet is completely contacted with the wing, leaving a tangent plane on an ice layer on the surface of the wing along the wing profile of the wing, inserting a surveying and mapping plate consistent with the shape of the metal sheet into the tangent plane of the ice layer, and drawing a curve on the surveying and mapping plate along the surface of the ice layer; drawing out the surveying and mapping plate, and measuring the curve on the observation plate to obtain the thickness and the shape of the ice layer; according to the invention, because the measuring metal sheet is not fixed, the ice layer can be cut quickly by heating the measuring metal sheet, the problem that the cutting metal sheet is clamped by ice in the traditional technology can be avoided, and the problem that the ice layer is damaged by shaking the metal sheet can be avoided.
Description
Technical Field
The invention relates to the field of low-speed icing wind tunnel measurement, in particular to an icing wind tunnel test ice shape measuring method.
Background
The icing of the airplane is a physical phenomenon widely existing in flight practice, and is one of the main hidden dangers of flight safety accidents. When an airplane flies under the icing meteorological condition that the environmental temperature is lower than the freezing point or is near the freezing point, supercooled water drops in the atmosphere impact the surface of the airplane, and the icing phenomenon is easy to occur on the surfaces of components such as wings, empennages, rotors, air inlet channels, windshield glass, antenna covers, instrument sensors and the like. The icing of the airplane not only increases the weight of the airplane, but also destroys the aerodynamic appearance of the surface of the airplane, changes the streaming flow field, destroys the aerodynamic performance, causes the descending of the maximum lift force of the airplane, the ascending of the flight resistance, the descending of the operating performance and the reduction of the stability performance, and causes great threat to the flight safety, the flight accidents caused by the icing are rare, and the serious icing can even lead to the death of the airplane.
After the icing test on the wing profile in the icing wind tunnel is finished, the thickness and the shape of icing on the wing profile need to be measured; the most common laser scanning 3D imaging technology at present cannot be used for measurement at all because of the reflection and transmission phenomena of the ice layer. Therefore, the measurement of the thickness and the shape of the ice layer can only be manually tested by an operator; the existing test mode is to fix the airfoil behind and measure the airfoil by a measuring tool fixed on the airfoil. The measuring method has the advantages that the measuring tool must be fixed in advance, so that measuring deviation can occur when the measuring tool is influenced by the ice layer in the testing process, and the tool can only measure the thickness of the ice layer at a fixed point and cannot measure other points because the tool is fixed. The most important disadvantage is that the fixing of the measuring tool on the airfoil profile in the wind tunnel test is a practice which greatly affects the measuring precision, the installation is very troublesome, the airfoil profile needs to be perforated, and the flow field on the surface of the airfoil profile is affected by excessive arrangement devices on the airfoil profile. Therefore, improvements to current measurement methods are needed.
Disclosure of Invention
The invention aims to provide a new measuring method, which solves various defects in the existing measuring method.
In order to achieve the purpose, the invention adopts the following technical scheme:
an icing wind tunnel test ice shape measuring method comprises the following steps:
the method comprises the following steps: arranging a metal sheet for cutting an ice layer along the horizontal direction in any vertical direction, arranging a notch which is consistent with the wing profile at the position of the metal sheet opposite to the wing, and pushing the metal sheet along the horizontal direction to clamp the wing into the notch along the notch of the metal sheet;
step two: after the metal sheet is completely contacted with the wing, drawing out the metal sheet, and leaving a tangent plane on the ice layer on the surface of the wing along the wing profile of the wing;
step three: inserting a surveying and mapping plate with the shape consistent with that of the metal sheet into the section of the ice layer, and drawing a curve on the surveying and mapping plate along the surface of the ice layer;
step four: the survey plate is drawn out, and the thickness and the shape of the ice layer can be obtained by measuring the curve on the observation plate.
In the above technical solution, in the first step, before the metal sheet is pushed, the edge of the notch of the metal sheet is heated to ensure that the metal sheet cuts into the ice layer.
In the technical scheme, when the heated metal sheet is cut with the ice layer, the condensing agent is continuously sprayed to the cut on the ice layer.
In the above technical solution, the surveying and mapping board in step three includes a substrate and a sticker with a grid disposed on the substrate.
In the technical scheme, the shape of the paster is consistent with that of the substrate, and the paster can be separated from the substrate after the drawing is finished.
In the technical scheme, the metal sheet and the surveying and mapping plate are arranged on a horizontal support frame which can move up and down along the vertical direction in the wind tunnel.
In the technical scheme, the horizontal support frame comprises two horizontal support edges, and the two support edges and one connecting edge form a U-shaped structure.
In the technical scheme, the shape of the U-shaped structure is consistent with that of the wing airfoil, and the opening diameter of the U-shaped structure is larger than the thickness of the wing airfoil.
In summary, due to the adoption of the technical scheme, the invention has the beneficial effects that:
different from the traditional test method, the method firstly ensures that no measuring tool is fixed on the surface of the wing airfoil, and all measuring tools are horizontally fixed through the outside;
secondly, the horizontal support frame in the scheme can move randomly in the vertical direction, so that the support frame has universality and can be used for stepless testing of the thickness and the shape of an ice layer at any point on the wing profile;
finally, because the measuring metal sheet of this scheme is unsettled, consequently can make the cutting ice sheet quick through the processing of heating it, can not appear cutting metal sheet among the traditional art and blocked the problem by ice because thereby can not destroy the problem on ice layer because of the shake metal sheet.
Drawings
The invention will now be described, by way of example, with reference to the accompanying drawings, in which:
FIG. 1 is a schematic view of an airfoil configuration of an airfoil;
FIG. 2 is a schematic cut-away view of a metal sheet and an airfoil;
FIG. 3 is a schematic structural view of the support frame;
wherein: 1 is a support frame, 2 is a measured model, 3 is a horizontal support table, and 4 is a metal sheet cutter.
Detailed Description
All of the features disclosed in this specification, or all of the steps in any method or process so disclosed, may be combined in any combination, except combinations of features and/or steps that are mutually exclusive.
As shown in fig. 1, the schematic view of the wing airfoil structure to be measured in the present scheme is shown, in an icing wind tunnel test, the airfoil is in a low-temperature wind tunnel flow field, the surface of the wing can be quickly iced, and the main purpose is to measure the icing thickness and the icing shape of the surface of the wing after the icing test.
As shown in fig. 2, the present invention is a tool for cutting an ice layer, and is a thin metal sheet, wherein a notch is formed in the metal sheet, and the size of the notch is identical to the size of an airfoil of a wing, that is, the notch of the metal sheet can be completely clamped on the leading edge of the wing when the surface of the wing is not frozen, and after the surface of the wing and the leading edge are frozen, the metal sheet is cut and clamped with the wing, and the thickness and the shape of the ice layer can be obtained by measuring the cut size.
The solution is shown in fig. 3, which is a support frame for supporting a metal sheet, and when the metal sheet in fig. 2 is to be used for cutting an ice layer, it is necessary to ensure a premise that the metal sheet must be on the same horizontal plane with respect to a fixed wing, and the support frame must be fixed. Therefore, the adjustable stud is adopted at the top end of the support frame, the support frame is locked up and down in the wind tunnel by adjusting the extending distance of the stud, the support frame is ensured not to be displaced in the operation process, and when cutting is not needed, the wind tunnel can be removed from the support frame, so that the influence of the support frame on the flow field of the wind tunnel is reduced. The support frame in the scheme has the greatest advantage that the support frame can be adjusted at any position in the vertical direction, so that the thickness and the appearance of the ice layer on the surface of any position of the wing can be measured. The horizontal support frame for supporting the metal sheet comprises two support edges and a connecting edge for connecting the support edges, the support edges and the connecting edge form a U-shaped structure, the metal sheet is arranged on the U-shaped structure and is in a horizontal position, and the metal edge is pushed to advance to the wing along the horizontal direction of the metal sheet so as to realize cutting of an ice layer.
In this scheme, because consider that the metal sheet removes the cutting ice sheet simple, the metal sheet can be blocked by the ice sheet at the in-process of cutting, and the back of blocking can make the ice sheet of metal sheet upper and lower both sides appear breaking at the in-process of pulling the metal sheet, damages the ice sheet to lead to the measurement inaccuracy on ice sheet. Therefore, in the scheme, before the metal sheet is cut into the ice layer, the edge of the notch of the metal sheet is heated, and the ice layer is quickly melted by utilizing the temperature difference between the metal sheet and the ice, so that the purpose of cutting is achieved. In order to have better thermal conductivity, copper sheets are generally used as the metal sheets because copper has a larger heat capacity value. However, since the temperature of the metal sheet is not controllable, especially after contacting with the ice layer, the metal sheet with too high temperature may cause the ice layer to melt faster, thereby causing the thickness and shape of the ice layer to change. Therefore, in the process of cutting the metal sheet, the condensing agent needs to be sprayed on the cut ice layer, so that the ice layer is not melted due to overhigh temperature, and the appearance of the ice layer is not damaged.
After the heated sheet is cut through the ice layer, the sheet is removed and a mapping plate is replaced for mapping. The surveying and mapping plate comprises a thin sheet with the thickness equal to that of the metal plate, a piece of paper with a grid is pasted on the surface of the thin sheet, the surveying and mapping plate has the same structure and size as the metal sheet, the surveying and mapping plate is inserted into a cutting opening on an ice layer, and after the surveying and mapping plate is fixed, a pen is used for drawing lines on the surveying and mapping plate along the ice layer on the surface of the wing. After the line is drawn, the surveying and mapping plate is drawn out, the grid paper is taken down, and the thickness and the shape of the icing on the surface of the wing can be obtained by measuring the width on the grid paper and observing the shape of the grid paper.
The invention is not limited to the foregoing embodiments. The invention extends to any novel feature or any novel combination of features disclosed in this specification and any novel method or process steps or any novel combination of features disclosed.
Claims (3)
1. An icing wind tunnel test ice shape measuring method is characterized by comprising the following steps:
the method comprises the following steps: the support frame is placed at a proper position, the support frame is locked up and down in the wind tunnel by adjusting the extending distance of the stud, and the support frame is ensured not to displace in the operation process;
the support frame comprises two horizontal support edges, the two horizontal support edges and a connecting edge form a U-shaped structure, the shape of the U-shaped structure is consistent with that of an airfoil profile of the wing, and the opening diameter of the U-shaped structure is larger than the thickness of the airfoil profile of the wing; the U-shaped structure on the supporting frame can be adjusted randomly in the vertical direction;
arranging a metal sheet for cutting an ice layer on the U-shaped structure, keeping the metal sheet at any horizontal position to be measured, heating the edge of a notch of the metal sheet, pushing the metal sheet along the horizontal direction, cutting the ice layer, and uninterruptedly spraying condensing agent to the notch on the ice layer to enable the wing to be clamped into the notch along the notch of the metal sheet;
step two: after the metal sheet is completely contacted with the wing, drawing out the metal sheet, and leaving a tangent plane on the ice layer on the surface of the wing along the wing profile of the wing;
step three: taking down the metal sheet from the support frame, arranging a surveying and mapping plate with the shape consistent with that of the metal sheet on the U-shaped structure of the support frame, inserting the surveying and mapping plate into the section of the ice layer, and drawing a curve on the surveying and mapping plate along the surface of the ice layer;
step four: the survey plate is drawn out, and the thickness and the shape of the ice layer can be obtained by measuring the curve on the observation plate.
2. The ice shape measuring method for icing wind tunnel test according to claim 1, wherein the mapping plate in the third step comprises a substrate and a sticker with a grid arranged on the substrate.
3. The ice shape measurement method for the icing wind tunnel test according to claim 2, wherein the shape of the sticker is consistent with that of the substrate, and the sticker can be separated from the substrate after being drawn.
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| CN201810768271.XA CN108844710B (en) | 2018-07-13 | 2018-07-13 | Icing wind tunnel test ice shape measuring method |
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| CN108844710B true CN108844710B (en) | 2021-02-09 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109653966B (en) * | 2019-02-18 | 2021-10-01 | 中国空气动力研究与发展中心低速空气动力研究所 | Test method for preventing and removing ice of wind turbine wing panel |
| CN109696289A (en) * | 2019-02-18 | 2019-04-30 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of wind energy conversion system wing panel icing test macro and method |
| CN111003209A (en) * | 2019-12-26 | 2020-04-14 | 中国航空工业集团公司西安飞机设计研究所 | Large-scale empennage deicing wind tunnel test device and method |
| CN111289206B (en) * | 2020-04-28 | 2020-08-14 | 中国空气动力研究与发展中心低速空气动力研究所 | Ice shape measurement auxiliary device and method |
| CN111351629B (en) * | 2020-05-09 | 2020-09-01 | 中国空气动力研究与发展中心低速空气动力研究所 | Icing wind tunnel test ice shape measuring device and method |
| CN111521131B (en) * | 2020-07-06 | 2020-10-16 | 中国空气动力研究与发展中心低速空气动力研究所 | Data acquisition device and data acquisition method for ice sample structural analysis |
| CN112729762B (en) * | 2021-03-29 | 2021-07-02 | 中国空气动力研究与发展中心低速空气动力研究所 | Method for measuring uniformity of icing grid and cloud and mist field |
| CN113483512B (en) * | 2021-09-07 | 2021-11-23 | 中国空气动力研究与发展中心低速空气动力研究所 | Icing wind tunnel test ice-shaped cutting device and cutting method |
| CN116448376B (en) * | 2023-06-16 | 2023-08-18 | 中国空气动力研究与发展中心低速空气动力研究所 | Spray air supply system for icing wind tunnel and adjusting method |
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| JP3749135B2 (en) * | 2001-03-13 | 2006-02-22 | 横河電子機器株式会社 | Temperature measuring device |
| CN101578515A (en) * | 2007-02-22 | 2009-11-11 | 伊利诺斯工具制品有限公司 | System and method for acoustically detecting ice |
| CN101285673A (en) * | 2008-06-06 | 2008-10-15 | 太原理工大学 | Capacitance ratio type ice-covering thickness sensor and its detection method |
| CN201318987Y (en) * | 2008-09-12 | 2009-09-30 | 北京大学 | Programmable control double-stage linkage movable measurement rack device for wind tunnel |
| CN202057472U (en) * | 2011-02-15 | 2011-11-30 | 成都飞机设计研究所 | Aerofoil profile leading edge ice melting device used for icing wind tunnel test |
| CN102494635B (en) * | 2011-12-13 | 2014-08-13 | 中国空气动力研究与发展中心设备设计及测试技术研究所 | Wind tunnel model ice shape measuring method and device |
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