Aerodynamic load testing device of airfoil sealing structure

Abstract

The aerodynamic load testing device of the airfoil sealing structure comprises a test box, a laser ranging device, a vacuum pump and a pressure gauge, and the test box comprises a box body and a front cover which are matched to form a sealing cavity; an opening and an annular mounting table corresponding to the opening are arranged at the bottom of the box body, a force value sensing device is further arranged on one side of the mounting table, one end of the airfoil sealing structure sample is fixed on the annular mounting table, and the other end of the airfoil sealing structure sample is lapped on the force value sensing device; an observation window is arranged on the front cover; the laser ranging device is arranged on the outer side of the front cover of the test box, and a laser ranging module of the laser ranging device is aligned to the mounting table through the observation window; the vacuum pump is communicated with the test box and is used for providing aerodynamic load; the pressure gauge is arranged on the side wall of the box body and used for monitoring the pressure intensity in the sealing cavity. The structure has the advantages of being adjustable in size, high in testing speed and high in accuracy, and is particularly suitable for testing the aerodynamic load resistance of the airfoil sealing structure in the aviation field.

Description

Technical Field

[0001] This invention belongs to the field of aerospace technology, and specifically relates to an aerodynamic load testing device for a wing sealing structure. Background Technology

[0002] The wing surface seal is a crucial feature of stealth aircraft, playing a vital role in maintaining the aerodynamic and electromagnetic continuity of the wing. The wing surface seal typically employs a single cantilever beam fixed configuration, with one end mounted to the wing using countersunk bolts, and the other end overlapping the movable control surface. As the control surface deflects, the wing surface seal maintains its shielding function over the gap between the movable control surface and the fixed wing surface. For the wing surface seal to work effectively, it must possess good elastic deformation capacity to accommodate control surface deflection, and sufficient structural rigidity to withstand aerodynamic loads during flight, preventing the overlapping end of the wing surface seal from being lifted and losing its shielding function.

[0003] To evaluate the aerodynamic load resistance of wing surface seals, the wing with the seals installed is typically measured in a wind tunnel. However, measuring the aerodynamic loads on seals in different wing surface locations usually requires fabricating control surface carriers that simulate the corresponding installation positions. These carriers are often large in size, have long testing cycles, and are costly, making them unsuitable for the efficient and low-cost measurement needs of wing surface seals in different locations.

[0004] Therefore, in view of the above shortcomings, this invention is proposed. Summary of the Invention

[0005] The purpose of this invention is to provide an aerodynamic load testing device for a wing-sealed structure, which at least partially solves the above-mentioned technical problems.

[0006] This invention proposes an aerodynamic load testing device for an airfoil sealing structure, comprising: The test chamber includes a box body and a front cover adapted to form a sealed cavity; the bottom of the box body is provided with an opening and an annular mounting platform corresponding to the opening, and a force sensing device is also provided on one side of the mounting platform; one end of the wing sealing structure sample is fixed to the annular mounting platform, and the other end is attached to the force sensing device; an observation window is provided on the front cover. A laser rangefinder is installed on the outside of the front cover of the test chamber, and the laser rangefinder module of the laser rangefinder is positioned facing the mounting platform through the observation window. A vacuum pump, which is connected to the test chamber and is used to provide a pneumatic load; A pressure gauge is installed on the side wall of the housing and is used to monitor the pressure inside the sealed cavity.

[0007] The aerodynamic load testing device for the wing-surface sealing structure proposed in this invention may also have the following additional technical features: In some specific embodiments of the present invention, the annular mounting platform is provided with a groove that is approximately the same shape as the wing sealing structure sample, one end of the groove is a connecting end, and the other end of the groove is provided with the force sensing device.

[0008] In some specific embodiments of the present invention, taking the fixed end to the overlapping end of the wing sealing structure sample as the first direction, the length difference between the groove and the wing sealing structure sample in the direction perpendicular to the first direction is 0~0.1mm.

[0009] In some specific embodiments of the present invention, in the connected state, the minimum distance between the wing-face sealing structure sample and the inner wall of the test chamber is not less than 20 mm.

[0010] In some specific embodiments of the present invention, a vacuum buffer tank is also included, wherein the top wall and three side walls of the housing are each provided with a port communicating with the sealed cavity, and the vacuum buffer tank is connected between the vacuum pump and the plurality of the ports.

[0011] In some specific embodiments of the present invention, the volume of the vacuum buffer tank is not less than 0.5 m³. 3 .

[0012] In some specific embodiments of the present invention, the number of pressure gauges is four, and they are respectively located on the top wall and three side walls of the housing.

[0013] In some specific embodiments of the present invention, the minimum measurement accuracy of the force sensing device is not less than 0.1N; and / or The laser rangefinder has a measurement accuracy of not less than 0.05 mm; and / or The minimum measurement accuracy of the pressure gauge is not less than 1.0 kPa.

[0014] In some specific embodiments of the present invention, a sealing ring is provided on the front side of the box, and the box and the front cover are sealed by the sealing ring.

[0015] In some specific embodiments of the present invention, the observation window is transparent glass.

[0016] The aerodynamic load testing device provided by this invention can prepare a sample mounting platform according to the actual assembly relationship of the wing sealing structure. Therefore, the size of the tested wing sealing structure sample is flexibly adjustable and easy to disassemble and install. It can not only test the aerodynamic load resistance of the wing sealing structure sample, but also accurately measure the magnitude of the pre-tightening force at the overlapping end and the height after it is lifted under different aerodynamic loads. Therefore, it has important application value for measuring and evaluating the aerodynamic load resistance of a large number of wing sealing structures with different installation positions. Attached Figure Description

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

[0018] Figure 1 This is a schematic diagram of the aerodynamic load testing device for the wing-surface sealing structure in this invention; Figure 2 This is a schematic diagram of the test chamber in this invention.

[0019] Explanation of reference numerals in the attached figures: 1-Vacuum pump, 2-Vacuum buffer tank, 3-Test chamber, 31-Annular mounting platform, 32-Force sensing device, 33-Pressure gauge, 34-Pipe port, 35-Valve, 36-Observation window, 37-Sealing ring, 4-Laser rangefinder, 5-Flange sealing structure sample. Detailed Implementation

[0020] Exemplary embodiments of the invention will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the invention are shown in the drawings, it should be understood that the invention can be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided to enable a more thorough understanding of the invention and to fully convey the scope of the invention to those skilled in the art.

[0021] It should be understood that the terminology used herein is for the purpose of describing particular exemplary embodiments only and is not intended to be limiting. Unless the context clearly indicates otherwise, the singular forms “a,” “an,” and “described” as used herein may also include the plural forms. The terms “comprising,” “including,” “containing,” and “having” are inclusive and therefore indicate the presence of the stated features, steps, operations, elements, and / or components, but do not exclude the presence or addition of one or more other features, steps, operations, elements, components, and / or combinations thereof. The method steps, processes, and operations described herein are not construed as requiring them to be performed in a particular order described or illustrated unless the order of performance is explicitly indicated. It should also be understood that additional or alternative steps may be used.

[0022] Although terms such as first, second, third, etc., may be used in this document to describe multiple elements, components, regions, layers, and / or segments, these elements, components, regions, layers, and / or segments should not be limited by these terms. These terms may be used only to distinguish one element, component, region, layer, or segment from another. Unless the context clearly indicates otherwise, terms such as "first," "second," and other numerical terms used herein do not imply order or sequence. Therefore, the first element, component, region, layer, or segment discussed below may be referred to as the second element, component, region, layer, or segment without departing from the teachings of the exemplary embodiments.

[0023] For ease of description, spatial relative terms may be used in the text to describe the relationship of one element or feature relative to another element or feature, as shown in the figure. These relative terms include, for example, "inside," "outside," "middle," "outer," "below," "below," "above," "over," etc. Such spatial relative terms are intended to include different orientations of the device in use or operation, other than those depicted in the figure. For example, if the device in the figure is flipped, an element described as "below other elements or features" or "below other elements or features" would subsequently be oriented as "above other elements or features" or "above other elements or features." Therefore, the example term "below" can include both upper and lower orientations. The device may be otherwise oriented (rotated 90 degrees or in other directions), and the spatial relative descriptors used in the text will be interpreted accordingly.

[0024] Reference Figure 1 and Figure 2 This invention proposes an aerodynamic load testing device for a wing-shaped sealing structure, comprising a test chamber 3, a laser rangefinder 4, a vacuum pump 1, and a pressure gauge 33. The test chamber 3 includes a housing and a front cover adapted to form a sealed cavity. The bottom of the housing has an opening and a corresponding annular mounting platform 31. A force sensing device 32 is also provided on one side of the mounting platform. One end of the wing-shaped sealing structure sample is fixed to the annular mounting platform 31, and the other end overlaps the force sensing device 32. An observation window 36 is provided on the front cover. The laser rangefinder 4 is located on the outside of the front cover of the test chamber 3, and its laser rangefinder module is aligned with the mounting platform through the observation window 36. The vacuum pump 1 is connected to the test chamber 3 and is used to provide the aerodynamic load. The pressure gauge 33 is located on the side wall of the housing and is used to monitor the pressure inside the sealed cavity.

[0025] Specifically, the test chamber 3 is roughly rectangular in shape and includes a box body with an opening on the front and a front cover that fits the opening. The box body and the front cover are fitted together to form a sealed cavity. The bottom wall of the box body has an opening, and an annular mounting platform 31 is disposed in the sealed cavity and mounted on the bottom wall of the box body. The central cavity of the annular mounting platform 31 corresponds to the opening, and a force sensing device 32 is disposed on the annular mounting platform 31. The annular mounting platform 31 is used to mount the wing sealing structure sample. Specifically, one end of the wing sealing structure sample is mounted on the annular sealing platform through a threaded connector (e.g., a countersunk bolt), and the other end overlaps the force sensing device 32. After installation, the wing sealing structure sample roughly covers the entire opening, so that the sealed cavity is in a near-sealed state.

[0026] Vacuum pump 1 is connected to test chamber 3 and is adapted to provide pneumatic load by evacuation. Pressure gauge 33 is used to detect the gas pressure in test chamber 3, thereby facilitating the adjustment of the pneumatic load intensity by assisting vacuum pump 1. Laser rangefinder 4 is located on the outside of the front cover of test chamber 3, and the laser rangefinder module of laser rangefinder 4 is aligned with the mounting platform through observation window 36. Specifically, it is aligned with the overlapping end of the wing seal structure sample and is used to monitor the height of the overlapping end of the wing seal structure sample lifted under the action of pneumatic load. With the force value sensing device 32, the magnitude of the preload of the overlapping end under the action of pneumatic load can be measured.

[0027] Based on the above settings, the aerodynamic load testing device provided by the present invention can prepare a sample mounting platform in a personalized manner according to the actual wing sealing structure assembly relationship. Therefore, the size of the tested wing sealing structure sample is flexibly adjustable and easy to disassemble and install. It can not only test the aerodynamic load resistance of the wing sealing structure sample, but also accurately measure the magnitude of the pre-tightening force at the overlapping end and the height after it is lifted under different aerodynamic loads. Therefore, it has important application value for measuring and evaluating the aerodynamic load resistance of a large number of wing sealing structures with different installation positions.

[0028] In some embodiments, the annular mounting platform 31 is provided with a groove that is approximately the same shape as the wing sealing structure sample. One end of the groove is a connecting end, and the other end of the groove is provided with a force sensing device 32.

[0029] By setting a groove on the annular mounting platform 31 and installing the wing sealing structure sample into the groove, even if the overlapping end of the wing sealing structure sample is lifted during aerodynamic load testing, the two ends of the wing sealing structure sample relative to the overlapping end can still form a good seal with the annular mounting platform 31, which helps to improve the control accuracy of the pressure inside the test chamber 3, and thus improves the accuracy of aerodynamic load testing.

[0030] It should be noted that the line connecting the fixed end and the overlapping end of the wing sealing structure sample is roughly perpendicular to the front cover, and the overlapping end is close to the front cover. In this way, the overlapping end is directly facing the laser rangefinder 4, which is beneficial for observation.

[0031] In some embodiments, taking the fixed end to the overlapping end of the wing sealing structure sample as the first direction, the length difference between the groove and the wing sealing structure sample in the direction perpendicular to the first direction is 0~0.1mm.

[0032] Specifically, taking the direction from the fixed end to the overlapping end of the wing-shaped sealing structure sample as the first direction, and the direction perpendicular to the first direction in the horizontal plane as the second direction, the length of the groove in the second direction is 0~0.1mm larger than the length of the wing-shaped sealing structure sample in the second direction, for example, 0.01mm, 0.02mm, 0.05mm, 0.08mm, 0.1mm, etc. Thus, when the wing-shaped sealing structure sample is installed in the groove, it ensures that the wing-shaped sealing structure sample does not get stuck with the annular mounting platform, i.e., it does not affect the lifting of the overlapping end of the wing-shaped sealing structure sample, while also ensuring good sealing between the wing-shaped sealing structure sample and the annular mounting platform 31.

[0033] In some embodiments, in the connected state, the minimum distance between the wing-sealing structure specimen and the inner wall of the test chamber 3 is not less than 20 mm.

[0034] For example, the minimum distance between the wing-sealed structure sample and the inner wall of the test chamber 3 is 20mm, 25mm, 30mm, 40mm, 60mm, 100mm, etc.

[0035] This embodiment adjusts the size of the test chamber 3 by controlling the wing-sealing structure specimen, thus ensuring that the test chamber 3 has sufficient space, thereby ensuring the uniformity of pressure in the test chamber 3, and further ensuring the uniformity of stress on the wing-sealing structure specimen, thereby improving the accuracy of aerodynamic load testing.

[0036] In some embodiments, a vacuum buffer tank 2 is also included, and the top wall and three side walls of the tank are each provided with a port 34 communicating with the sealed cavity. The vacuum buffer tank 2 is connected between the vacuum pump 1 and the multiple ports 34.

[0037] Specifically, multiple ports 34 are connected to the vacuum buffer tank 2 through connecting pipes, and the vacuum buffer tank 2 is also connected to the vacuum pump 1 through connecting pipes. In this way, a vacuum pump 1 can control the vacuuming process from multiple ports 34, which helps to improve the pressure uniformity in the test chamber 3, thereby ensuring the stress uniformity of the wing sealing structure sample and improving the accuracy of aerodynamic load testing.

[0038] Furthermore, multiple ports 34 converge into a main pipeline and are connected to the vacuum buffer tank 2 via the main pipeline. A valve 35 is installed on the main pipeline to control the pumping pressure.

[0039] In some embodiments, the volume of the vacuum buffer tank 2 is not less than 0.5 m³. 3 .

[0040] For example, the volume of vacuum buffer tank 2 is 0.5m³. 3 0.6 m 3 0.8 m 3 1.0 m 3 1.5 m 3 2.0 m 3 By increasing the volume of the vacuum buffer tank 2, a continuous vacuum suction can be provided, reducing the impact of the vacuum pump 1 on the single port 34. This helps to improve the pressure uniformity in the test chamber 3, thereby ensuring the uniformity of stress on the wing-sealed structure specimen and improving the accuracy of aerodynamic load testing.

[0041] In some embodiments, there are four pressure gauges 33, which are located on the top wall and three side walls of the chamber. By setting multiple pressure gauges 33, the pressure at different locations in the sealed cavity can be monitored, thereby determining the effectiveness and reliability of the structure and measures for the pressure uniformity in the test chamber 3, and ensuring the accuracy of the pneumatic load test.

[0042] In some embodiments, the minimum measurement accuracy of the force sensing device 32 is not less than 0.1N; and / or the measurement accuracy of the laser rangefinder 4 is not less than 0.05mm; and / or the minimum measurement accuracy of the pressure gauge 33 is not less than 1.0KPa.

[0043] This ensures the accuracy and precision of the aerodynamic load test.

[0044] In some embodiments, a sealing ring 37 is provided on the front side of the chamber, and the chamber and the front cover are sealed by fitting the sealing ring 37. This can enhance the sealing performance between the chamber and the front cover, thereby helping to ensure the uniformity of pressure in the test chamber 3, and thus ensuring the uniformity of stress on the wing-sealed structure specimen, and improving the accuracy of aerodynamic load testing.

[0045] In some embodiments, the viewing window 36 is transparent glass.

[0046] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. An aerodynamic load testing device for a wing-surface sealing structure, characterized in that, include: The test chamber includes a box body and a front cover adapted to form a sealed cavity; the bottom of the box body is provided with an opening and an annular mounting platform corresponding to the opening, and a force sensing device is also provided on one side of the mounting platform; one end of the wing sealing structure sample is fixed to the annular mounting platform, and the other end is attached to the force sensing device; an observation window is provided on the front cover. A laser rangefinder is installed on the outside of the front cover of the test chamber, and the laser rangefinder module of the laser rangefinder is positioned facing the mounting platform through the observation window. A vacuum pump, which is connected to the test chamber and is used to provide a pneumatic load; A pressure gauge is installed on the side wall of the housing and is used to monitor the pressure inside the sealed cavity.

2. The aerodynamic load testing device for the wing sealing structure according to claim 1, characterized in that, The annular mounting platform is provided with a groove that is approximately the same shape as the wing sealing structure sample. One end of the groove is a connecting end, and the other end of the groove is provided with the force sensing device.

3. The aerodynamic load testing device for the wing sealing structure according to claim 2, characterized in that, Taking the fixed end to the overlapping end of the wing sealing structure sample as the first direction, the length difference between the groove and the wing sealing structure sample in the direction perpendicular to the first direction is 0~0.1mm.

4. The aerodynamic load testing device for the wing sealing structure according to claim 1, characterized in that, In the connected state, the minimum distance between the wing-face sealing structure sample and the inner wall of the test chamber is not less than 20 mm.

5. The aerodynamic load testing device for the wing sealing structure according to claim 1, characterized in that, It also includes a vacuum buffer tank, and the top wall and three side walls of the housing are each provided with a pipe opening that communicates with the sealed cavity. The vacuum buffer tank is connected between the vacuum pump and the multiple pipe openings.

6. The aerodynamic load testing device for the wing sealing structure according to claim 5, characterized in that, The volume of the vacuum buffer tank is not less than 0.5m³. 3 .

7. The aerodynamic load testing device for the wing sealing structure according to claim 1, characterized in that, The pressure gauges are four in number and are located on the top wall and three side walls of the housing.

8. The aerodynamic load testing device for the wing sealing structure according to claim 1, characterized in that, The minimum measurement accuracy of the force sensing device is not less than 0.1N; and / or The laser rangefinder has a measurement accuracy of not less than 0.05 mm; and / or The minimum measurement accuracy of the pressure gauge is not less than 1.0 kPa.

9. The aerodynamic load testing device for the wing sealing structure according to claim 1, characterized in that, The front side of the box is provided with a sealing ring, and the box and the front cover are sealed by the sealing ring.

10. The aerodynamic load testing device for the wing sealing structure according to claim 1, characterized in that, The observation window is made of transparent glass.

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