A test piece for testing the influence of icing characteristics on a swept wing

Abstract

The application discloses a test piece for a swept wing icing characteristic influence test and relates to the technical field of aircraft wing test models. The test piece comprises a basic module, a flow guide module is detachably connected to the top of the basic module, a rough module is arranged on the side surface of the basic module, the rough module is at least partially embedded in the basic module, and the rough module is detachably connected with the basic module; the bottom of the basic module is arranged to be inclined to the center line of the rough module, and an angle module is detachably connected to the bottom of the basic module. The basic module is used as a basic structure, the rough module and / or the angle module are replaced, variables of the swept wing icing characteristic influence test can be effectively controlled, and space cost required by the test is reduced.

Description

Technical Field

[0001] This application relates to the field of aircraft wing test model technology, and in particular to a test piece for testing the effects of icing characteristics on swept wings. Background Technology

[0002] When an aircraft flies at sub-freezing temperatures, if it encounters clouds containing supercooled water droplets, the droplets will impact the aircraft's surface, causing icing. Aircraft icing is a widespread phenomenon in flight practice and one of the main hidden dangers causing flight safety accidents. Icing alters the airflow field around the aircraft, causing changes in component load distribution, thereby impairing aerodynamic performance, affecting the aircraft's handling and stability, and endangering flight safety. In mild cases, it reduces the safe flight range; in severe cases, it can lead to serious accidents resulting in the destruction of the aircraft and loss of life. Icing at swept wings is influenced by a combination of complex processes. The roughness of the condensed ice, due to its varying degrees of roughness, will have different effects on the aircraft's flight parameters, thus affecting flight safety.

[0003] The relevant technology primarily involves conducting icing wind tunnel tests on swept wings with varying roughness within the wind tunnel. These tests require experimenting with swept wings at different sweep angles. This technology typically involves fabricating multiple test specimens for the same test. However, using multiple test specimens necessitates replacing the entire specimen, which introduces significant interference errors into the collected data. Summary of the Invention

[0004] The embodiments of this application disclose a test piece for testing the influence of swept-wing icing characteristics, in order to solve the technical problem in related technologies where tests with different physical parameters require the replacement of multiple test pieces as a whole, resulting in large interference errors in experimental data.

[0005] To address the above problems, the embodiments of this application adopt the following technical solutions: An embodiment of this application provides a test piece for testing the influence of swept wing icing characteristics, specifically including a base module, a flow guiding module detachably connected to the top of the base module, a roughening module provided on the side of the base module, the roughening module being at least partially embedded in the base module, and the roughening module being detachably connected to the base module. The bottom of the base module is inclined to the center line of the rough module, and the bottom of the base module is detachably connected to an angle module.

[0006] Furthermore, the basic module has a first notch on its side, and a first socket is provided in the first notch. The rough module is embedded in the first notch and plugged into the first socket. The rough module and the first socket are detachably connected.

[0007] Furthermore, the first socket is distributed circumferentially along the edge of the first notch and has a first recess at the junction of the first notch and the side of the base module; When the rough module is inserted into the first socket, the rough module abuts against the first recess.

[0008] Furthermore, the base module has a first flange at its bottom and the angle module has a second socket at its top. The first flange is inserted into the second socket, and the first flange and the second socket are detachably connected.

[0009] Furthermore, the bottom of the basic module is provided with a second recess, which is circumferentially distributed outside the first flange; When the first flange is inserted into the second socket, the angle module abuts against the second recess.

[0010] Furthermore, the top of the base module is provided with a second flange, and the flow guiding module is plugged into and detachably connected to the second flange.

[0011] Furthermore, the top of the base module is provided with a third recess, which is circumferentially distributed outside the second flange. When the flow guide module is inserted into the second flange, the flow guide module abuts against the third recess.

[0012] Furthermore, the flow guiding module has a flow guiding surface on the side near the rough module, and the flow guiding surface smoothly transitions from the side of the flow guiding module to the top surface of the flow guiding module.

[0013] Furthermore, the basic module has a first cavity distributed around the circumference of the roughening module, and the angle module has a second cavity, with the first cavity and the second cavity connected.

[0014] Furthermore, a third socket is provided at the bottom of the second cavity, which is used for external insertion.

[0015] The technical solutions adopted in the embodiments of this application can achieve the following beneficial effects: When conducting experiments on the effects of swept-wing icing characteristics, related technologies typically employ the method of replacing the entire test specimen to test different roughnesses and sweep angles. However, replacing the entire test specimen occupies a large space, and the physical parameters of different test specimens differ, making it difficult to control experimental variables and leading to a significant risk of errors in the experimental results.

[0016] The embodiments of this application employ a detachably connected base module, flow guiding module, roughening module, and angle module to reduce experimental errors. Because the base module serves as the load-bearing foundation, the main body of the test piece remains consistent across different experiments. The flow guiding module directs the gas flow, thereby simulating the gas flow of different types of swept wings. By replacing the roughening module and / or the angle module while keeping the flow guiding module and base module identical, the variables affecting the experiment's experimental properties related to swept wing icing characteristics can be effectively controlled, and the space required for the experiment can be reduced. Furthermore, experimental errors are effectively reduced due to variable control. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0018] Figure 1 This is a schematic diagram of the structure of the test specimen disclosed in the embodiments of this application; Figure 2 This is a schematic diagram of the structure of the test piece after the roughening module has been removed, as disclosed in the embodiments of this application; Figure 3 This is a cross-sectional view of the test specimen after the roughening module has been removed, as disclosed in the embodiments of this application; Figure 4 This is a cross-sectional schematic diagram of the basic module disclosed in the embodiments of this application; Figure 5 This is a cross-sectional schematic diagram of the first type of angle module disclosed in the embodiments of this application; Figure 6 This is a side view of the first type of angle module disclosed in the embodiments of this application; Figure 7 This is a cross-sectional schematic diagram of the second angle module disclosed in the embodiments of this application; Figure 8 This is a cross-sectional schematic diagram of the third angle module disclosed in the embodiments of this application.

[0019] In the picture: 100. Flow guiding module; 110. Flow guiding surface; 200, Basic module; 210, First socket; 220, First recess; 230, First flange; 240, Second recess; 250, First notch; 260, First cavity; 270, Second flange; 280, Third recess; 300, Angle Module; 310, Second Socket; 320, Second Cavity; 330, Third Socket; 400, Rough Module. Detailed Implementation

[0020] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions of this application will be described in detail below. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. Based on the embodiments in this application, all other implementation methods obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0021] The terms "first," "second," etc., used in the specification and claims of this application are used to distinguish similar objects and not to describe a specific order or sequence. It should be understood that such terms can be used interchangeably where appropriate so that embodiments of this application can be implemented in orders other than those illustrated or described herein, and the objects distinguished by "first," "second," etc., are generally of the same class and the number of objects is not limited; for example, a first object can be one or more. Furthermore, in the specification and claims, "and / or" indicates at least one of the connected objects, and the character " / " generally indicates that the preceding and following objects are in an "or" relationship.

[0022] Experiments on the effects of swept-wing icing characteristics are usually conducted in wind tunnels. Test specimens are set up in the wind tunnels, and flight simulations are performed on the test specimens to observe the changes in various parameters and icing states on the surface of the test specimens, in order to study the influence of swept-wing icing characteristics on flight parameters.

[0023] Unlike straight-wing icing, swept-wing icing exhibits a significant spanwise overflow effect, resulting in highly complex three-dimensional discrete shell-like ice formations. This poses a significant challenge to the icing safety assessment of swept-wing aircraft. The formation of swept-wing shell ice is influenced by a combination of complex processes, including multiphase flow, coupled heat and mass transfer, and unsteady ice formation evolution. Its growth mechanism remains unclear, and an accurate computational model has yet to be established.

[0024] Because the icing characteristics of swept wings are strongly correlated with their sweep angle, related technologies typically employ multiple test specimens to conduct the experiment. During the experiment, different test specimens are replaced to obtain experimental data for different sweep angles. However, significant errors often occur in the data results from multiple experiments, rendering the experimental data unusable. In severe cases, this can even lead to experimental failure.

[0025] In view of this, the following is in conjunction with the appendix Figures 1 to 8 This paper provides a detailed description of a test piece for testing the effects of icing characteristics on swept wings, through specific embodiments and application scenarios.

[0026] Please see Figure 1 As shown, an embodiment of this application provides a test piece for testing the effects of icing characteristics on swept wings, specifically including a base module 200, which serves as the stable load-bearing structure for the entire test piece. A flow guiding module 100 is detachably connected to the top of the base module 200, which guides the fluid to simulate the flight state of a swept wing.

[0027] One of the main reasons why icing on swept wings can develop into safety risks is that rough ice forms on the wing surface and periodically condenses, gradually developing into shell ice. In experiments on the effects of icing characteristics on swept wings, the safety risks caused by rough ice are an important research topic. Since rough ice cannot be stably obtained, this embodiment of the application includes a rough module 400 on the side of the base module 200 to simulate rough ice on the swept wing. The rough module 400 is at least partially embedded in the base module 200, and the rough module 400 and the base module 200 are detachably connected. Embedding the rough module 400 in the base module 200 improves the overall integrity of the rough module 400 and the base module 200, thus better reflecting the state of rough ice formation on the swept wing surface. The detachable connection between the rough module 400 and the base module 200 allows the rough module 400 to be replaced. By replacing the rough module 400 with one of different roughnesses, the roughness of the rough module 400 can be effectively changed, thereby conducting simulation experiments of rough ice with different roughnesses.

[0028] The bottom of the base module 200 is inclined to the centerline l of the roughness module 400, and an angle module 300 is detachably connected to the bottom of the base module 200. By removing and replacing the angle module 300, the inclination angle of the base module 200 can be effectively changed. However, since most wind tunnel tests are conducted in small to medium-sized icing wind tunnels, the test section size is small, and the tunnel walls have a significant impact. The area covered by the roughness module 400 is the ice-shape study area of ​​the test specimen. To ensure that the ice-shape study area remains at the wind tunnel centerline, the bottom of the base module 200 is inclined to the centerline l of the roughness module 400. This ensures that when the inclination angle of the base module 200 is changed, the position of the roughness module 400 remains at the wind tunnel centerline.

[0029] When replacing test specimens entirely, related technologies cannot guarantee that the physical parameters of different test specimens will be identical. For example, the surface configuration and overall roughness of the test specimens may differ. When studying the icing characteristics of swept wings, differences in multiple physical parameters between different test specimens may lead to significant deviations in experimental results, resulting in experimental failure. Furthermore, replacing test specimens entirely requires sufficient space to accommodate the replacement specimen, resulting in excessive expenditure in terms of both space utilization and material costs.

[0030] Based on this, a detachable connecting flow guiding module 100, roughening module 400, and angle module 300 are constructed using the basic module 200 as the structural foundation. This allows for the replacement of different modules while ensuring that the variables in the experimental process remain within a controllable range without replacing the main experimental component. For example, when the angle module 300 is replaced, the physical parameters of the remaining parts of the test piece remain unchanged, thus reducing experimental interference to a controllable range.

[0031] Moreover, by replacing different modules, experiments can be completed with less space and less material, effectively controlling experimental costs.

[0032] For some embodiments of this application, please refer to Figure 2 As shown, the base module 200 has a first notch 250 on its side, and a first insertion port 210 is provided within the first notch 250. The rough module 400 is embedded into the first notch 250 and plugged into the first insertion port 210. The rough module 400 and the first insertion port 210 are detachably connected. The first notch 250 allows the rough module 400 to be embedded in the base module 200 and at least partially located within the base module 200. In the swept-wing test specimen formed based on the base module 200, the rough module 400, as part of the swept-wing test specimen, represents the icing study area of ​​the test specimen. Furthermore, the rough module 400 is located on the centerline of the wind tunnel, therefore, it experiences significant wind force. Through the semi-enclosed protection of the first notch 250 and the plugging relationship between the first insertion port 210 and the rough module 400, the structural stability of the rough module 400 installed on the base module 200 can be effectively improved, thereby enhancing the ability of the rough module 400 to withstand wind force on the base module 200. The detachable connection between the rough module 400 and the first socket 210 can be a bolt connection, riveting, or snap-fit ​​connection, etc.

[0033] For some embodiments of this application, please refer to Figure 3 As shown, the first insertion port 210 is distributed circumferentially along the edge of the first notch 250, and a first recess 220 is provided at the junction of the first notch 250 and the side of the base module 200. The first recess 220 allows the roughening module 400 to utilize the platform formed at the first recess 220 to resist shear stress. The overall integrity between the roughening module 400 and the base module 200 is improved, and the increased structural strength in the wind tunnel also prevents the roughening module 400 from separating from the base module 200.

[0034] When the roughening module 400 is inserted into the first socket 210, the roughening module 400 abuts against the first recess 220. Based on the insertion, the roughening module 400, through abutting against the first recess 220, effectively enhances the structural strength of the test piece by improving its overall integrity, thereby enabling the embodiments of this application to complete the experiment under greater wind speeds.

[0035] For example, when subjected to external forces, if the first recess 220 is not provided, the roughening module 400 has no abutment. Thus, when the external force is transmitted from the roughening module 400 to the base module 200, it relies entirely on the connection at the first socket 210 for resistance. This results in a higher risk of deformation at the first socket 210, easily damaging the test piece. However, if the first recess 220 is provided, the external force acting on the roughening module 400 is absorbed by both the first recess 220 and the first socket 210, making the force transmitted from the roughening module 400 to the base module 200 more even. This improves the overall structural strength of the test piece and reduces the risk of deformation.

[0036] The surface roughness of the roughening module 400 is achieved through shot blasting. Different sized steel shot is used to bombard the skin surface, creating varying degrees of roughness. For example, 0.2mm and 0.4mm shot are used to bombard the skin surface, resulting in different roughness levels. Normally finished skin can be used as a comparison with smooth skin. The roughening module 400 surfaces with different roughness levels can simulate the roughness of different icing surfaces, thus providing an initial rough ice state for experiments on the influence of icing characteristics on swept wings. Based on this, flight conditions are simulated in an icing wind tunnel, effectively obtaining the influence of rough ice of different roughness levels on the flight parameters of the swept wing. The sweep angle is then adjusted using the angle module 300, allowing for the collection of more complete data on the influence of icing characteristics on swept wings.

[0037] In some embodiments of this application, the test piece needs to be replaced with angle modules 300 at different angles to adapt to icing characteristic experiments with different sweep angles. Please refer to [link to relevant documentation]. Figure 5 , Figure 7 and Figure 8As shown, different angle modules 300 maintain structural consistency on the side that docks with the base module 200, but the angles α, β, and γ between the inclined surface and the bottom surface of the angle module 300 are different. When the bottom surface of the angle module 300 is used as the bottom surface of the test piece, the tilt angle of the test piece corresponding to different angle modules 300 is different, but the test pieces using different angle modules 300 can all keep the rough module 400 located at the center line of the wind tunnel. Therefore, the embodiments of this application can effectively complete icing characteristic experiments with different sweep angles on the test piece by replacing the angle modules 300. Angles α, β, and γ can be 0°, 15°, 30°, or 45°, etc. The angle modules 300 with corresponding angles are prepared and replaced according to the specific needs of the experiment. The embodiments of this application do not impose specific limitations on the number and angle of the angle modules 300.

[0038] For some embodiments of this application, please refer to Figure 4 As shown, the base module 200 has a first flange 230 at its bottom, and the angle module 300 has a second socket 310 at its top. The first flange 230 is inserted into the second socket 310, and the first flange 230 and the second socket 310 are detachably connected. The first flange 230 is inserted into the second socket 310 to form an insertion state. By replacing different angle modules 300, test pieces with different sweep angles can be formed in combination with the base module 200, thus facilitating experiments with different sweep angles. Placing the first flange 230 on the base module 200 effectively transfers the force of the base module 200 to the angle module 300. During wind tunnel testing, the first flange 230 inserted into the second socket 310 has stronger structural stability, thus being able to withstand greater wind forces.

[0039] In some embodiments of this application, the base module 200 has a second recess 240 at its bottom, which is circumferentially distributed outside the first flange 230. When the first flange 230 is inserted into the second socket 310, the angle module 300 abuts against the second recess 240. The second recess 240 creates a circumferential force-bearing platform outside the first flange 230, increasing the force-bearing area and thus improving the structural strength at the first flange 230. After the first flange 230 is inserted into the second socket 310, the angle module 300 can effectively enhance the ability of the first flange 230 to withstand external forces using the second recess 240. This improves the overall integrity of the base module 200 and the angle module 300, thereby increasing the overall structural strength of the test piece and enabling experiments to be completed under higher wind speeds.

[0040] In some embodiments of this application, please refer to... Figure 4 and Figure 5As shown, the top of the base module 200 is provided with a second flange 270, and the flow guiding module 100 is plugged into and detachably connected to the second flange 270. Through the plugging of the flow guiding module 100 and the second flange 270, the external force acting on the flow guiding module 100 can be effectively transferred to the base module 200 when connecting the flow guiding module 100 and the base module 200. The second flange 270 increases the contact area at the connection point, thereby improving the connection stability between the base module 200 and the flow guiding module 100. During the experiment, the overall strength of the test piece can also be guaranteed.

[0041] In some embodiments of this application, the top of the base module 200 is provided with a third recess 280, which is circumferentially distributed outside the second flange 270. When the flow guiding module 100 is inserted into the second flange 270, the flow guiding module 100 abuts against the third recess 280. The third recess 280 effectively provides a force-bearing platform circumferentially around the second flange 270, improving the structural strength of the edge position of the second flange 270. The third recess 280 also enhances the overall integrity of the connection between the second flange 270 and the flow guiding module 100, strengthening the ability of the second flange 270 to withstand external forces.

[0042] In some embodiments of this application, the airflow guiding module 100 has an airflow guiding surface 110 on its side near the roughening module 400, and the airflow guiding surface 110 smoothly transitions from the side of the airflow guiding module 100 to the top surface of the airflow guiding module 100. By guiding the airflow through the airflow guiding surface 110, the test piece can better conform to the flight simulation state of a swept wing.

[0043] For some embodiments of this application, please refer to Figures 3 to 6 As shown, the base module 200 has a first cavity 260, which is distributed circumferentially around the roughening module 400. The angle module 300 has a second cavity 320, and the first cavity 260 and the second cavity 320 are connected. The arrangement of the first cavity 260 and the second cavity 320 effectively isolates the heat transfer of the roughening module 400 on the base module 200, allowing the roughening module 400 to be more prominently used as the ice-forming research area for icing experiments. This effectively avoids the increased experimental observation difficulty caused by rapid heat transfer around the ice-forming research area on the test piece. Furthermore, the structural design of the connected first cavity 260 and the second cavity 320 better matches the actual structure of the swept wing.

[0044] In some embodiments of this application, a third socket 330 is provided at the bottom of the second cavity 320 for external connection. The third socket 330 is used for external connection, thereby enabling the test piece to be effectively fixed in the icing wind tunnel to complete the experiment.

[0045] It should be noted that, in this document, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Unless otherwise specified, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes that element.

[0046] Furthermore, it should be noted that the scope of the methods and apparatus in the embodiments of this application is not limited to performing functions in the order shown or discussed, but may also include performing functions substantially simultaneously or in the reverse order, depending on the functions involved. For example, the described methods may be performed in a different order than described, and various steps may be added, omitted, or combined. In addition, features described with reference to certain examples may be combined in other examples.

[0047] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in this application should be included within the scope of protection of this application.

Claims

1. A test specimen for testing the influence of swept-wing icing characteristics, characterized in that, Includes a base module (200), a flow guide module (100) is detachably connected to the top of the base module (200), and a rough module (400) is provided on the side of the base module (200). The rough module (400) is at least partially embedded in the base module (200), and the rough module (400) is detachably connected to the base module (200). The bottom of the base module (200) is inclined to the centerline of the rough module (400), and the bottom of the base module (200) is detachably connected to an angle module (300). The basic module (200) has a first notch (250) on its side, and a first socket (210) is provided in the first notch (250). The rough module (400) is embedded in the first notch (250) and plugged into the first socket (210). The rough module (400) and the first socket (210) are detachably connected. The base module (200) has a first flange (230) at its bottom and the angle module (300) has a second socket (310) at its top. The first flange (230) is inserted into the second socket (310) and the first flange (230) and the second socket (310) are detachably connected. The base module (200) has a second flange (270) on its top, and the flow guiding module (100) is plugged into and detachably connected to the second flange (270).

2. The test specimen for testing the influence of swept-wing icing characteristics according to claim 1, characterized in that, The first socket (210) is distributed circumferentially along the edge of the first notch (250) and has a first recess (220) at the junction of the first notch (250) and the side of the base module (200). When the rough module (400) is inserted into the first socket (210), the rough module (400) abuts against the first recess (220).

3. The test specimen for testing the influence of swept-wing icing characteristics according to claim 1, characterized in that, The bottom of the base module (200) is provided with a second recess (240), which is circumferentially distributed outside the first flange (230); When the first flange (230) is inserted into the second socket (310), the angle module (300) abuts against the second recess (240).

4. The test specimen for testing the influence of swept-wing icing characteristics according to claim 1, characterized in that, The top of the base module (200) is provided with a third recess (280), which is circumferentially distributed outside the second flange (270). When the flow guide module (100) is inserted into the second flange (270), the flow guide module (100) abuts against the third recess (280).

5. The test specimen for testing the influence of swept-wing icing characteristics according to claim 4, characterized in that, The flow guiding module (100) has a flow guiding surface (110) on the side near the rough module (400), and the flow guiding surface (110) smoothly transitions from the side of the flow guiding module (100) to the top surface of the flow guiding module (100).

6. The test specimen for testing the influence of swept-wing icing characteristics according to claim 1 or 2, characterized in that, The basic module (200) has a first cavity (260) which is distributed circumferentially around the rough module (400). The angle module (300) has a second cavity (320) which is connected to the first cavity (260) and the second cavity (320).

7. The test specimen for testing the influence of swept-wing icing characteristics according to claim 6, characterized in that, The bottom of the second cavity (320) is provided with a third socket (330), which is used for external insertion.

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