CN114754971B - Method and device for testing height of anhydrous shielding area - Google Patents
Method and device for testing height of anhydrous shielding area Download PDFInfo
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- CN114754971B CN114754971B CN202210675800.8A CN202210675800A CN114754971B CN 114754971 B CN114754971 B CN 114754971B CN 202210675800 A CN202210675800 A CN 202210675800A CN 114754971 B CN114754971 B CN 114754971B
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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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B5/00—Measuring arrangements characterised by the use of mechanical techniques
- G01B5/02—Measuring arrangements characterised by the use of mechanical techniques for measuring length, width or thickness
- G01B5/06—Measuring arrangements characterised by the use of mechanical techniques for measuring length, width or thickness for measuring thickness
- G01B5/061—Measuring arrangements characterised by the use of mechanical techniques for measuring length, width or thickness for measuring thickness height gauges
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
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- Aviation & Aerospace Engineering (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention belongs to the field of icing wind tunnel experiments, and particularly relates to a method and a device for testing the height of a waterless shielding area. The method for testing the height of the waterless shielding area comprises the following steps: s100: obtaining a test model and an icing sensor model; s200: mounting the icing sensor model perpendicular to the wall surface to be tested of the test model; s300: setting icing meteorological conditions, and placing the test model in the icing meteorological conditions for icing test; s400: and after the test is finished, obtaining the icing condition on the icing sensor model, wherein the icing height of the icing sensor model, which protrudes out of the surface of the model to the set icing thickness, is the height of the anhydrous shielding area. The invention can find the water-free shielding area through experiments and can provide accurate reference for the installation position of the icing sensor.
Description
Technical Field
The invention belongs to the field of icing wind tunnel experiments, and particularly relates to a method and a device for testing the height of a waterless shielding area.
Background
The aircraft passes through a cloud layer containing supercooled water drops in flight, the supercooled water drops collide with the surface of the aircraft, and an icing phenomenon is likely to occur near the collision area. Icing is widely present in flight practice and seriously compromises flight safety. The airplane mainly depends on the onboard icing sensor to carry out icing detection, the performance of the icing sensor determines the icing detection effect, and if the icing sensor gives an alarm untimely, gives a false alarm, fails to give the alarm or has too large error, the airplane can cause flight safety hidden dangers. Therefore, the icing sensor is extremely important for flight safety and is an onboard equipment that is indispensable to most aircraft.
The windward side of the airplane is easier to freeze, the windward side comprises wing leading edges, an engine air inlet component and a cab windshield, the icing sensor is generally not arranged on the windward side but arranged on a wall surface adjacent to the windward side, however, due to the influence of air streaming, supercooled water drops in windward side environment are different from the wall surface environment where the icing sensor is arranged, the supercooled water drops in the peripheral flow field are not uniformly distributed due to the difference of the wall surface environment where the icing sensor is arranged, a water-free shielding area exists in a wide area close to the wall surface, and if the icing sensing area of the icing sensor is located in the area, icing cannot be detected, so that the condition is missed; if the icing sensing area of the icing sensor is in the area, the signal is over sensitive, and the signal is missed; the location of the ice signal sensing area of the ice sensor is very important.
In the prior art, the height of the anhydrous shielding region is mostly calculated by adopting a numerical simulation calculation method, but the error of the numerical simulation calculation is large under the influence of a calculation model, boundary condition setting and the like, and how to obtain the effective height of the anhydrous shielding region is always a topic searched by a person skilled in the art.
Disclosure of Invention
In order to solve the technical problems in the prior art, the invention provides a method for testing the height of a water-free shielding area. The invention can find the anhydrous shielding area through tests, can provide accurate reference for the mounting position of the icing sensor, and obtains more accurate height of the anhydrous shielding area relative to numerical simulation calculation.
The invention is realized by the following technical scheme:
a method for testing the height of a water-free shielding area is characterized by comprising the following steps:
s100: obtaining a test model and an icing sensor model;
s200: mounting the icing sensor model perpendicular to the wall surface to be tested of the test model;
s300, setting icing meteorological conditions, and placing the test model in the icing meteorological conditions to carry out an icing test;
s400: and after the test is finished, obtaining the icing condition on the icing sensor model, wherein the icing height of the icing sensor model, which is protruded out of the surface of the model to the set icing thickness, is the height of the anhydrous shielding area.
Further, in step S200, a plurality of icing sensor models are arranged along the set direction of the test model, and the icing sensor models are arranged in a staggered manner along the set direction.
Further, the heights of the anhydrous shielding areas obtained by multiple measurements are connected to obtain the anhydrous shielding area on the surface of the test model.
Further, the test model comprises an aircraft, an air inlet channel and a wind driven generator blade.
Further, the set icing meteorological conditions are determined by appendix C, part 25, of the china civil aviation regulations.
Further, the set icing thickness is calculated by setting icing meteorological conditions.
The invention also provides a device for testing the height of the anhydrous shielding area, which is characterized by being used for executing the method for testing the height of the anhydrous shielding area, and comprising the following steps: the icing sensor model is perpendicular to the wall surface to be measured of the test model and is mounted on the wall surface.
Further, a plurality of icing sensor model mounting holes are formed in the test model.
Furthermore, scale marks are arranged on the icing sensor model.
Further, the test model comprises an aircraft, an air inlet channel and a wind driven generator blade.
Compared with the prior art, the method and the device for testing the height of the waterless shielding area have the advantages that:
1. the height of the waterless shielding area on the surface of the model is obtained by the test method, so that reference is provided for the installation of the height of the icing sensor, and the detection precision of the icing sensor is improved.
2. The method has the advantages of simple operation, high experimental accuracy and low experimental cost.
3. The testing device provided by the invention can be used for obtaining the height experiment of the waterless shielding area on the wall surface of the airplane in the icing wind tunnel experiment, and provides reference for the height of the icing sensor.
4. The method is not only suitable for the height test of the waterless shielding area on the surface of aircrafts such as airplanes and the like, but also suitable for the height test of the waterless shielding area in an air inlet channel, and has wide application range.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the embodiments of the present invention or the description of the prior art will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
Fig. 1 is a schematic flow chart of a method for testing the height of an anhydrous shielding area in embodiment 1 of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments.
Example 1
As shown in fig. 1, the embodiment provides a method for testing height of a water-free shielding area, which includes the following steps:
s100: obtaining a test model and an icing sensor model;
the test model described in this embodiment may be an aircraft (such as an airplane), an air inlet duct, a wind turbine blade, and the like, and the aircraft model is taken as an example in this embodiment for description.
Carrying out scaling calculation on the basis of the airplane structure parameters (including parameters such as size and shape) to obtain parameters of an airplane scaling model, and manufacturing the airplane scaling model according to the parameters;
manufacturing an icing sensor model based on structural parameters of an icing sensor, wherein in order to save test cost, the icing sensor model is only manufactured into a structure with the appearance (shape and size) of the icing sensor;
s200: mounting the icing sensor model perpendicular to the wall surface to be measured of the airplane model;
in this embodiment, the sensor model that will freeze is perpendicular to the awaiting measuring of aircraft model and avoids the installation, is convenient for just obtain anhydrous district height through direct measurement thickness that freezes. It can be understood by those skilled in the art that if the icing sensor model is installed obliquely, on one hand, it is not guaranteed that the icing condition of the installation position is measured, and on the other hand, when the height of the water-free sheltered area is calculated, the icing condition needs to be multiplied by an inclination angle, so that the measurement work is more complicated.
S300, setting icing meteorological conditions, and placing the test model in the icing meteorological conditions for icing test;
in this embodiment, the icing weather condition may be set by a tester based on experience, or may be obtained according to annex C of section 25 of civil aviation regulations in china. The obtaining of such test conditions is routine for those skilled in the art and will not be described in detail herein.
S400: and after the test is finished, obtaining the icing condition on the icing sensor model, wherein the icing height of the icing sensor model, which protrudes out of the surface of the model to the set icing thickness, is the height of the anhydrous shielding area.
After the experiment, the icing condition on the icing sensor model can be measured by the icing thickness measuring method in the prior art, and under the general condition, the change rule from the root to the top of the icing sensor model is as follows: the ice formation is less and more, and an arc-shaped ice profile is presented. The area with less icing is the water-free shielding area, and the height of the water-free shielding area is determined by setting the icing thickness through experience or calculation.
The set icing thickness can be calculated according to the set icing meteorological conditions, and the specific calculation method is a conventional technical means in the field and is not described herein any more.
Preferably, a plurality of icing sensor models may be provided on the aircraft model surface to measure the water-free shaded area height at a plurality of locations. Under this condition, when aircraft model surface set up a plurality of sensor models that freeze, the sensor model mounted position that freezes and distance can influence the aerodynamic characteristics on aircraft model surface, produce certain influence to the air vortex of surface, consequently, in order to reduce the interference of freezing sensor model, need guarantee the distance between the sensor model that freezes, set up along setting for the direction dislocation simultaneously.
Therefore, the height of the anhydrous shielding areas with the same section and different sections can be measured according to requirements, and when the number of the measured points is large enough, the heights of the anhydrous shielding areas obtained through measurement are connected, so that the anhydrous shielding areas on the surface of the test model can be obtained.
Example 2
The embodiment provides a device for testing the height of a water-free shielding area, which is used for executing the method for testing the height of the water-free shielding area in embodiment 1.
The test model is provided with a plurality of icing sensor model mounting holes for mounting icing sensor models.
Furthermore, scale marks are arranged on the icing sensor model. Therefore, the height reaching the set icing thickness can be conveniently and directly observed, and the measurement difficulty is simplified.
The test model comprises an aircraft, an air inlet channel, a wind driven generator blade and the like.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and should not be taken as limiting the scope of the present invention, which is intended to cover any modifications, equivalents and improvements made within the spirit and scope of the present invention.
Claims (8)
1. A method for testing the height of a water-free shielding area is characterized by comprising the following steps:
s100: obtaining a test model and an icing sensor model;
s200: mounting the icing sensor model perpendicular to the wall surface to be tested of the test model;
s300, setting icing meteorological conditions, and placing the test model in the icing meteorological conditions for icing test;
s400: after the test is finished, obtaining the icing condition on the icing sensor model, wherein the icing height of the icing sensor model, which protrudes out of the surface of the model to the set icing thickness, is the height of the anhydrous shielding area;
in step S200, a plurality of icing sensor models are arranged along a set direction of the test model, and the icing sensor models are arranged in a staggered manner along the set direction;
the set icing thickness is obtained by calculating set icing meteorological conditions.
2. The method for testing the height of the anhydrous shielding area according to claim 1, wherein the anhydrous shielding areas on the surface of the test model are obtained by connecting a plurality of the measured anhydrous shielding area heights.
3. The method for testing the height of the waterless sheltered area according to claim 1 or 2, characterized in that the test model comprises an aircraft, an air intake duct and a wind turbine blade.
4. The method for testing the height of a water-free sheltered area according to claim 3, characterized in that said set icing meteorological conditions are determined according to appendix C of China civil aviation regulations, part 25.
5. A waterless shelter height testing apparatus for performing a waterless shelter height testing method as claimed in any one of claims 1-4: the icing sensor model is perpendicular to the wall surface to be measured of the test model.
6. The waterless shelter height testing apparatus of claim 5, wherein said test pattern includes a plurality of said ice sensor pattern mounting holes.
7. The waterless shelter height testing apparatus of claim 6, wherein said ice sensor pattern has graduations disposed thereon.
8. The waterless shelter height test apparatus of claim 6, wherein said test model comprises an aircraft, an air intake, and a wind turbine blade.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210675800.8A CN114754971B (en) | 2022-06-15 | 2022-06-15 | Method and device for testing height of anhydrous shielding area |
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| CN202210675800.8A CN114754971B (en) | 2022-06-15 | 2022-06-15 | Method and device for testing height of anhydrous shielding area |
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Citations (3)
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| FR2958622A1 (en) * | 2010-04-09 | 2011-10-14 | Airbus Operations Sas | METHOD AND SYSTEM FOR CONTROLLING ICE FORMATION ON A FLIGHT AIRCRAFT. |
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| CN112678189A (en) * | 2021-03-09 | 2021-04-20 | 中国空气动力研究与发展中心低速空气动力研究所 | Improved icing sensor installation position determining method |
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| JP6377315B2 (en) * | 2012-03-08 | 2018-08-22 | ザ・ボーイング・カンパニーＴｈｅ Ｂｏｅｉｎｇ Ｃｏｍｐａｎｙ | Icing condition detection system for supercooled large droplets |
| US8650944B2 (en) * | 2012-03-13 | 2014-02-18 | The Boeing Company | Supercooled large drop icing condition simulation system |
| US10611488B2 (en) * | 2017-05-05 | 2020-04-07 | Rosemount Aerospace Inc. | Ice accretion boundary locator |
| CN206876374U (en) * | 2017-06-07 | 2018-01-12 | 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 super-cooling waterdrop ice detection |
| US10435161B1 (en) * | 2018-05-02 | 2019-10-08 | Rosemount Aerospace Inc. | Surface sensing for droplet size differentiation |
| CN213580521U (en) * | 2020-08-31 | 2021-06-29 | 中铁建科检测有限公司 | Experimental device for sprayed concrete under erosion action |
| CN113761773B (en) * | 2021-11-10 | 2022-01-25 | 中国空气动力研究与发展中心低速空气动力研究所 | Method for calculating height of anhydrous area |
| CN114132512B (en) * | 2022-02-07 | 2022-04-29 | 中国空气动力研究与发展中心低速空气动力研究所 | Optical fiber icing sensor probe and adjusting method |
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| FR2958622A1 (en) * | 2010-04-09 | 2011-10-14 | Airbus Operations Sas | METHOD AND SYSTEM FOR CONTROLLING ICE FORMATION ON A FLIGHT AIRCRAFT. |
| CN111307406A (en) * | 2020-05-06 | 2020-06-19 | 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 liquid water content measuring method |
| CN112678189A (en) * | 2021-03-09 | 2021-04-20 | 中国空气动力研究与发展中心低速空气动力研究所 | Improved icing sensor installation position determining method |
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