CN113928553B - Blade structure and darkroom testing method - Google Patents
Blade structure and darkroom testing method Download PDFInfo
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- CN113928553B CN113928553B CN202111283526.1A CN202111283526A CN113928553B CN 113928553 B CN113928553 B CN 113928553B CN 202111283526 A CN202111283526 A CN 202111283526A CN 113928553 B CN113928553 B CN 113928553B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/473—Constructional features
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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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- 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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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Manufacturing & Machinery (AREA)
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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a blade structure and a darkroom testing method, and relates to the technical field of microwave darkroom tests. The method can simply and quickly change the coating condition of the front edge part so as to achieve the purpose of testing the RCS of the paddle under the combination form of various materials, and the front edge sections can be matched and recycled, so that the risk of damaging the appearance of the paddle by cleaning the coating layer is avoided, the manufacturing materials are saved, and the test cost is reduced.
Description
Technical Field
The invention relates to the technical field of microwave darkroom tests, in particular to a paddle structure and a darkroom test method.
Background
With the rapid development of modern radars, the combat environment of armed helicopters is more severe and complex, which makes the demand for low detection performance of advanced helicopters higher and higher. An important index for measuring the stealth capability of a helicopter Radar is RCS (Radar Cross Section), the fuselage is usually designed by adopting a polyhedral surface to reduce RCS in stealth design, but the rotor cannot meet the strict aerodynamic performance requirement when the rotor is designed by adopting a polyhedral shape, so that the RCS is usually reduced by coating a wave-absorbing material on the surface of the blade. The currently common methods for coating the wave-absorbing material on the blades mainly comprise two methods: (1) uniformly spraying a wave-absorbing material on the surface of the paddle; (2) and special adhesive tapes made of wave-absorbing materials are adhered to the surfaces of the blades. When the method is used for testing, the original coating layer needs to be thoroughly cleaned for multiple times, and the risk of damaging the aerodynamic appearance of the blade exists, so that the same blade is difficult to replace materials for multiple tests. Further considering the influence of the centrifugal force of the high-speed rotation of the blades on the adhesion of the wave-absorbing materials, the blades combined at different positions need to be coated with various wave-absorbing materials, so that the overall processing difficulty is increased, the production cost is increased, and a set of blade modular assembly mode which can be used for repeated experiments on a certain airfoil profile needs to be designed.
Disclosure of Invention
The invention aims to provide a blade structure and a darkroom testing method, which are used for solving the problems in the prior art, and the plurality of leading edge sections can be matched and recycled, so that the risk of damaging the blade appearance by cleaning a coating layer is avoided, the manufacturing material is saved, and the testing cost is reduced.
In order to achieve the purpose, the invention provides the following scheme:
the invention provides a blade structure which comprises a front edge module and a rear edge module, wherein the front edge module comprises a plurality of front edge parts, each front edge part is connected with the rear edge module in a sliding mode, and the surface of at least one front edge part is coated with a wave-absorbing material.
Preferably, a sliding groove is formed in the rear edge module, and a sliding block matched with the sliding groove is arranged on each front edge portion.
Preferably, a conductive aluminum foil is disposed between each front edge portion and the rear edge module and between adjacent front edge portions.
Preferably, the leading edge module and the trailing edge module are made of metal materials or are subjected to surface metallization treatment.
Preferably, the surface of the front edge part is coated with the wave-absorbing material by full coating, half coating or interval coating.
Preferably, the upper surface and the lower surface of the same front edge part are respectively coated with different wave-absorbing materials.
Preferably, the thickness of the wave-absorbing material coated on each front edge part is different.
Preferably, the surface of the trailing edge module is coated with a wave-absorbing material.
Preferably, one end of the trailing edge module is provided with a limiting part, and the limiting part is used for limiting the leading edge module.
The invention also provides a darkroom testing method adopting the paddle structure, which comprises the following steps:
selecting a required airfoil profile according to test requirements to generate a leading edge module and a trailing edge module of a blade structure, wherein the blade structure adopts a metal surface or surface metallization treatment;
step two, respectively coating wave-absorbing materials to be tested on different front edge parts, and coating the wave-absorbing materials on the rear edge module according to actual requirements if the rear edge module is required to be tested;
step three, carrying out working condition tests in different combination modes according to specific test contents, sequentially sliding the front edge part into the rear edge module along the sliding groove according to requirements during the test, and paving and sealing gaps among the front edge module, the rear edge module and the adjacent front edge module by using a conductive aluminum foil;
and fourthly, performing radar irradiation on the paddle structure to obtain a test result.
Compared with the prior art, the invention has the following technical effects:
the invention can simply and quickly change the coating condition of the front edge part to achieve the aim of testing the RCS of the blade under the combination form of various materials, and the front edge sections can be matched and recycled, thereby not only avoiding the risk of damaging the appearance of the blade by cleaning the coating layer, but also saving the manufacturing materials and reducing the test cost.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
FIG. 1 is a schematic view of a blade configuration of the present invention;
FIG. 2 is a front view of the blade structure of the present invention;
FIG. 3 is a top view of a blade structure of the present invention;
FIG. 4 is a side view of a blade structure of the present invention;
FIG. 5 is a schematic view of a leading edge portion of the present invention;
FIG. 6 is a schematic view of a trailing edge module of the present invention;
FIG. 7 is a side view of a leading edge module of the present invention;
FIG. 8 is a side view of a trailing edge module of the present invention;
FIG. 9 is a comparative RCS distribution diagram (3GHz) of blades under different working conditions
FIG. 10 is a comparison graph (10GHz) of RCS distribution of blades under different working conditions;
wherein: 100-blade structure, 1-leading edge module, 2-trailing edge module, 3-leading edge, 4-chute, 5-slide block and 6-limiting part.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be obtained by a person skilled in the art without inventive effort based on the embodiments of the present invention, are within the scope of the present invention.
The invention aims to provide a blade structure and a darkroom testing method, which are used for solving the problems in the prior art, and the plurality of leading edge sections can be matched and recycled, so that the risk of damaging the blade appearance by cleaning a coating layer is avoided, the manufacturing material is saved, and the testing cost is reduced.
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
Example one
As shown in fig. 1-8: the embodiment provides a blade structure 100, which includes a leading edge module 1 and a trailing edge module 2, wherein the leading edge module 1 includes a plurality of leading edge portions 3, each leading edge portion 3 is connected with the trailing edge module 2 in a sliding manner, and the surface of at least one leading edge portion 3 is coated with a wave-absorbing material.
In this embodiment, the rear edge module 2 is provided with the sliding groove 4, each front edge portion 3 is provided with the sliding block 5 matched with the sliding groove 4, and the front edge portion 3 of this embodiment adopts a connection mode of sliding in on one side, so that the degree of freedom of blade fixation can be reduced, and the function of fixing on one side is achieved.
In this embodiment, a conductive layer is provided between each leading edge 3 and the trailing edge module 2 and between adjacent leading edges 3.
In this embodiment, the conductive layer is made of conductive aluminum foil.
In this embodiment, the surface of the leading edge 3 is coated with the wave-absorbing material by full coating, half coating or interval coating.
In this embodiment, the adjacent leading edge portions 3 can be coated with different kinds of wave-absorbing materials, and the upper surface and the lower surface of the same leading edge portion 3 are coated with different wave-absorbing materials, respectively.
In this embodiment, the thickness of the wave-absorbing material coated on each leading edge portion 3 is different.
In this embodiment, due to the high aspect ratio of the blade, the edge of the trailing edge module 2 is highly diffracted, and the trailing edge module 2 may be coated with the wave-absorbing material.
In this embodiment, one end of the trailing edge module 2 is provided with a limiting portion 6, and the limiting portion 6 is used for limiting the leading edge module 1. The sum of the lengths of the limiting part 6 and the front edge module 1 is equal to the length of the rear edge module 2.
In this embodiment, the leading edge module 1 and the trailing edge module 2 are both made of metal materials or subjected to surface metallization, so that the reduction effect of a certain wave-absorbing material coating on the RCS of the blade can be accurately extracted, and the influence of different wave-absorbing materials and combination forms thereof on the RCS of the blade can be accurately measured.
Example two
The embodiment provides a darkroom testing method using the paddle structure 100 of the first embodiment, comprising the following steps:
firstly, selecting a required airfoil profile to generate a leading edge module 1 and a trailing edge module 2 of a blade structure 100 according to test requirements, wherein the blade structure 100 adopts a metal surface or surface metallization treatment;
step two, respectively coating wave-absorbing materials to be tested on different front edge parts 3, and coating the wave-absorbing materials on the rear edge module 2 according to actual needs if the test is needed;
step three, working condition tests in different combination modes are carried out according to specific test contents, the front edge part 3 is required to slide into the rear edge module 2 along the sliding groove 4 in sequence according to requirements during the tests, and gaps among the front edge module 1, the rear edge module 2 and the adjacent front edge module 1 are paved and sealed by using conductive aluminum foils so as to reduce the interference of the gaps on the RCS characteristics of the blade structure 100;
and fourthly, performing radar irradiation on the paddle structure 100 to obtain a test result.
When the blade structure 100 of the present embodiment is used for a microwave darkroom test, the leading edge portion 3 can be arbitrarily replaced and combined as needed. By replacing different front edge parts 3, the matching of the wave-absorbing materials of the front edge module 1 is changed, and the RCS (radar cross section) of the paddle with different wave-absorbing material combinations is tested. Through the blade structure 100 of the embodiment, the influence of multiple factors such as the type, the thickness and the relative position of the wave-absorbing material on the RCS of the blade can be researched.
Application example
Taking a straight blade as an example, as a reference blade platform, the straight blade is designed to be a modularized blade structure 100, and reference parameters of the straight blade are as follows: 2400mm in length, the airfoil NACA0012, 400mm in chord length.
Firstly, module position division needs to be carried out on a reference blade platform, and an airfoil section position is determined, in the embodiment, the airfoil section is selected to be divided at an 1/4 chord line position, so that the section shapes of a leading edge module 1 and a trailing edge module 2 are determined;
as shown in fig. 8, the shape parameters of the trailing edge module 2 are extracted, wherein the length of the trailing edge module 2 is 400mm, the length of the chute 4 for assembling the leading edge module 1 is 2000mm, and the trailing edge module 2 is made of metal material;
as shown in fig. 7, the size of the slider 5 on the section of the front edge module 1 is matched with the sliding slot 4 of the rear edge module 2, the front edge module 1 is made of metal material, the number of the front edge parts 3 is n, the length is l, and n x l satisfies the length of the sliding slot 4 of 2000 mm;
according to the test requirements, the type of the wave-absorbing material is determined, and each front edge part 3 is provided with a coating layer made of different wave-absorbing materials. When different wave-absorbing materials are coated, full coating, half coating, interval coating or the respective coating of the upper surface and the lower surface can be adopted at the same time, and the thickness of the materials is changed. Preparing a trailing edge module 2 based on the same blade structure 100, and using a plurality of leading edge parts 3 with different wave-absorbing material types, thicknesses and coating positions for a darkroom test;
the front edge parts 3 of the blade structure 100 are matched to form a plurality of combination forms of the front edge modules 1, and then the front edge modules are installed on the rear edge module 2 according to different assembling sequences, and conductive aluminum foils are used for paving and sealing gaps between the front edge modules 1 and the rear edge modules 2 and gaps between the adjacent front edge parts 3, so that a plurality of darkroom tests are carried out.
Specifically, two leading edge portions 3 are adopted, and the wave-absorbing material has the following properties: relative dielectric constant epsilon of wave-absorbing material I r 12.75-j.0.14, relative permeability mu r 1.20-j.0.88; relative dielectric constant epsilon of wave-absorbing material II r 100.58-j. 150.74, relative permeability mu r 1.49-j.1.67. The following five working conditions are established:
working condition 1: the blade structure 100 is made of metal, and the surfaces of the two front edge parts 3 are both free of wave-absorbing materials;
working condition 2: the blade structure 100 is made of metal, and the surfaces of the two front edge parts 3 are coated with a first wave-absorbing material with the thickness of 1 mm;
working condition 3: the metal paddle structure 100 is formed by sequentially coating a first wave-absorbing material and a second wave-absorbing material with the thickness of 1mm on the surfaces of two front edge parts 3 from left to right;
working condition 4: the metal paddle structure 100 is formed by sequentially coating a first wave-absorbing material and a second wave-absorbing material with the thickness of 5mm on the surfaces of two front edge parts 3 from left to right;
working condition 5: the metal paddle structure 100 is characterized in that the surfaces of two front edge parts 3 are coated with a second wave-absorbing material with the thickness of 1mm, and the surface of a rear edge module 2 is coated with a first wave-absorbing material with the thickness of 1 mm.
Under the irradiation of vertically polarized radar waves at 3GHz and 10GHz, RCS distribution of five working conditions in the area (azimuth angle 90-270 ℃) of the leading edge module 1 of the blade structure 100 is calculated and shown in FIGS. 9 and 10. It can be seen that the five paddle structures 100 in different combination forms have different RCS distributions, and the types, thicknesses and relative positions of the wave-absorbing materials can generate certain reduction effects on the RCS, and in the case of 10GHz, compared with the metal paddle structure 100 with no coating on the surface, the wave-absorbing materials can reduce the RCS peak value of the paddle structure 100 by 6.67dB at most; in the area of the leading edge module 1 of the blade structure 100 (the azimuth angle is 150-210 degrees), the difference of RCS reduction of the blade structure 100 in different combination modes is fully reflected.
If the test requirement is based on other straight blades, the airfoil shape and the chord length of the blade reference parameters, the dividing positions of the leading edge module 1 and the trailing edge module 2 and the length of the blade are changed, and the test steps are not changed.
The principle and the implementation mode of the present invention are explained by applying specific examples in the present specification, and the above descriptions of the examples are only used to help understanding the method and the core idea of the present invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In view of the above, the present disclosure should not be construed as limiting the invention.
Claims (5)
1. A blade construction characterized by: the blade structure is used for a microwave darkroom test and comprises a front edge module and a rear edge module, wherein the front edge module comprises a plurality of front edge parts, each front edge part is connected with the rear edge module in a sliding manner, each front edge part is detachably connected with the rear edge module, and the surface of at least one front edge part is coated with a wave-absorbing material;
the front edge module and the rear edge module are both made of metal materials or subjected to surface metallization treatment;
the rear edge module is provided with a sliding groove, and each front edge part is provided with a sliding block matched with the sliding groove;
conductive aluminum foils are arranged between each front edge part and the rear edge module and between the adjacent front edge parts;
the surface of the front edge part is coated with wave-absorbing materials by full coating, half coating or interval coating;
one end of the rear edge module is provided with a limiting part, and the limiting part is used for limiting the front edge module.
2. The blade structure according to claim 1, wherein: and the upper surface and the lower surface of the same front edge part are respectively coated with different wave-absorbing materials.
3. The blade structure according to claim 1, wherein: the thickness of the wave-absorbing material coated on each front edge part is different.
4. The blade structure according to claim 1, wherein: and the surface of the trailing edge module is coated with wave-absorbing materials.
5. A darkroom testing method using a blade structure according to any one of claims 1 to 4, wherein: the method comprises the following steps:
selecting a required airfoil profile according to test requirements to generate a leading edge module and a trailing edge module of a blade structure, wherein the blade structure adopts a metal surface or surface metallization treatment;
step two, respectively coating wave-absorbing materials to be tested on different front edge parts, and coating the wave-absorbing materials on the rear edge module according to actual needs if the rear edge module is required to be tested;
step three, carrying out working condition tests in different combination modes according to specific test contents, sequentially sliding the front edge part into the rear edge module along the sliding groove according to requirements during the test, and paving and sealing gaps among the front edge module, the rear edge module and the adjacent front edge module by using a conductive aluminum foil;
and fourthly, performing radar irradiation on the paddle structure to obtain a test result.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111283526.1A CN113928553B (en) | 2021-11-01 | 2021-11-01 | Blade structure and darkroom testing method |
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|---|---|---|---|
| CN202111283526.1A CN113928553B (en) | 2021-11-01 | 2021-11-01 | Blade structure and darkroom testing method |
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| CN113928553A CN113928553A (en) | 2022-01-14 |
| CN113928553B true CN113928553B (en) | 2022-09-02 |
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| CN114987738A (en) * | 2022-05-31 | 2022-09-02 | 中国人民解放军总参谋部第六十研究所 | Blade with RCS reinforcement structure |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3901012A1 (en) * | 1989-01-14 | 1990-07-26 | Messerschmitt Boelkow Blohm | ROTOR BLADE |
| US5717397A (en) * | 1996-05-17 | 1998-02-10 | Lockheed Martin Corporation | Low observable shape conversion for aircraft weaponry |
| CN203512020U (en) * | 2013-10-18 | 2014-04-02 | 深圳光启创新技术有限公司 | Wing structure |
| KR101752299B1 (en) * | 2017-04-18 | 2017-06-30 | 국방과학연구소 | Structure with Radome for RCS reduction |
| CN113353287B (en) * | 2021-07-13 | 2022-06-28 | 南京航空航天大学 | Darkroom test device and paddle |
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