A wing full-attitude dual-power opening and closing integrated anti-icing test wind tunnel

Abstract

The present application discloses a wing full-attitude dual-power opening and closing integrated anti-icing and deicing test wind tunnel, including a first cave body, a second cave body, an attitude adjustment device, a power device and an auxiliary component. The first cave body includes a test section, the test section is used to set the wing, the first cave body and the second cave body are detachably connected, when the first cave body and the second cave body are combined and connected, the inlet of the first cave body is connected to the outlet of the second cave body, and the outlet of the first cave body is connected to the inlet of the second cave body to form a closed wind tunnel, when the first cave body and the second cave body are separated, the first cave body forms an open wind tunnel; the test section is provided with an attitude adjustment device; the power device is arranged at the inlet of the first cave body, and the auxiliary component is used to cool the first cave body or provide spray; the wing full-attitude dual-power opening and closing integrated anti-icing and deicing test wind tunnel can switch between a closed wind tunnel and an open wind tunnel, has the advantages of both closed and open wind tunnels, and can adjust the wing attitude through the attitude adjustment device.

Description

Technical Field

[0001] The present application relates to the technical field of wind tunnel test equipment, and in particular to a wing full-attitude dual-power opening and closing integrated anti-icing test wind tunnel. Background Art

[0002] Wing icing is a potential safety hazard that cannot be ignored during flight. Wing icing may cause the aircraft's flight performance to deteriorate, and severe wing icing may even cause the aircraft to crash. Therefore, it is extremely important to study the mechanism and impact of aircraft icing. The wind tunnel test method using an anti-icing test wind tunnel combines the advantages of both icing numerical simulation and icing flight test. The test results are reliable, the parameters are controllable, and the cost is low. It is currently a widely used research method and airworthiness verification method.

[0003] In the related technology, anti-icing test wind tunnels usually adopt open or closed structures. The structure of an open wind tunnel is usually linear, with low-temperature airflow entering from one end and flowing out from the other end. An open wind tunnel utilizes the natural low-temperature environment, has a simple structure and low manufacturing cost, but because it is connected to the outside environment at both ends, it is greatly affected by the outside temperature, airflow, etc., and the test effect is poor. A closed wind tunnel can allow the test airflow to circulate in the pipeline. The closed wind tunnel has a relatively complex structure and high manufacturing cost, but because it can perform multi-stage acceleration and multi-stage cooling on the test airflow, the test effect is better.

[0004] However, closed wind tunnels are large in size, have high construction costs, and have complex operating systems, making them difficult to miniaturize and make them easy to use. Furthermore, during the anti-icing test wind tunnel test, the test object (wing) is generally fixedly installed, and has few adjustable postures, which cannot provide an anti-icing test environment for the wing under multiple working conditions. Furthermore, the power source of the anti-icing test wind tunnel is mostly axial flow fans, which have a single power form and are difficult to use with natural low temperatures or in conjunction with other low-temperature equipment. Summary of the invention

[0005] In order to solve at least one of the above technical problems, the present application provides a wind tunnel device that can switch between a closed wind tunnel and an open wind tunnel, thereby combining the advantages of both closed and open wind tunnels. The technical solution adopted is as follows.

[0006] The present application provides a wing full-attitude dual-powered opening and closing integrated anti-icing and deicing test wind tunnel, comprising a first hole body, a second hole body, a power device and an auxiliary component. The first hole body is detachably connected to the second hole body. The first hole body comprises a test section, and the test section is used to set the wing. When the first hole body and the second hole body are combined and connected, the entrance of the first hole body is connected to the exit of the second hole body, and the exit of the first hole body is connected to the entrance of the second hole body to form a closed wind tunnel. When the first hole body and the second hole body are separated, the first hole body forms an open wind tunnel. An attitude adjustment device is provided in the test section, and the attitude adjustment device is used to adjust the attitude of the wing. The power device is arranged at the entrance of the first hole body. The auxiliary component is connected to the first hole body and arranged outside the first hole body, and the auxiliary component is used to cool the first hole body or provide spray.

[0007] As an optional implementation, in some embodiments of the present application, the first hole body further includes a power section, a cooling section and a spray section connected in sequence, the outlet of the spray section is connected to the test section, the second hole body includes a reflux section, and the power device includes the power section;

[0008] When the first hole body and the second hole body are combined and connected, one end of the reflux section is connected to the inlet of the power section, and the other end is connected to the outlet of the test section, so that the first hole body and the second hole body form a continuous airflow channel; when the first hole body and the second hole body are separated, the inlet of the power section is connected to the outside world, and the outlet of the test section is connected to the outside world.

[0009] As an optional implementation, in some embodiments of the present application, the wing full-attitude dual-power opening and closing integrated anti-icing test wind tunnel also includes a low-temperature environment box. When the first hole body is separated from the second hole body, the inlet of the power section is connected to the low-temperature environment box, and the outlet of the test section is connected to the low-temperature environment box.

[0010] As an optional implementation, in some embodiments of the present application, the power device further includes a high-pressure gas source, and when the first hole body is separated from the second hole body, the inlet of the power section is connected to the high-pressure gas source.

[0011] As an optional implementation, in some embodiments of the present application, the wing full-attitude dual-power opening and closing integrated anti-icing test wind tunnel also includes a low-temperature environmental box, the high-pressure air source is arranged in the low-temperature environmental box, and the outlet of the test section is connected to the low-temperature environmental box.

[0012] As an optional implementation, in some embodiments of the present application, the power section includes a first acceleration section, a power connection section, and a second acceleration section connected in sequence, the outlet of the second acceleration section is connected to the cooling section, and when the first hole body is separated from the second hole body, the inlet of the first acceleration section is connected to the outside; or

[0013] The power section includes a power connection section, and the power device also includes a high-pressure air source. When the first hole body is separated from the second hole body, one end of the power connection section is connected to the high-pressure air source, and the other end is connected to the cooling section.

[0014] As an optional implementation, in some embodiments of the present application, the first acceleration section and / or the second acceleration section is provided with an axial flow fan, and the axial flow fan is used to accelerate the gas.

[0015] As an optional implementation, in some embodiments of the present application, the attitude adjustment device includes a driving mechanism and a connecting rod mechanism connected to the driving mechanism, the connecting rod mechanism is used to install the wing, and the driving mechanism is used to drive the connecting rod mechanism to adjust the attitude of the wing.

[0016] As an optional implementation, in some embodiments of the present application, the test section is provided with a plurality of the attitude adjustment devices, the lower wing surface of the wing is provided with a plurality of mounting parts at intervals, and the attitude adjustment devices are connected to the mounting parts one by one.

[0017] As an optional implementation, in some embodiments of the present application, the first hole body further includes a first corner segment and / or a second corner segment, the first corner segment is connected between the power segment and the cooling segment, and the second corner segment is connected between the cooling segment and the spray segment; and / or

[0018] The second hole body further includes a third corner section and / or a fourth corner section, wherein the third corner section is arranged at the inlet of the reflux section, and the fourth corner section is arranged at the outlet of the reflux section;

[0019] When the first hole body is connected to the second hole body, the third corner section is connected to the test section and the reflux section, and the fourth corner section is connected to the reflux section and the power section.

[0020] As an optional implementation, in some embodiments of the present application, the wing full-attitude dual-power opening and closing integrated anti-icing test wind tunnel also includes a guide vane, which is arranged at the first corner section, the second corner section, the third corner section and / or the fourth corner section, and the guide vane is used to guide the airflow through the corner.

[0021] As an optional implementation, in some embodiments of the present application, the guide vane is arranged on the angular bisector of the corner segment, the guide vane is bent along the flow direction of the airflow, and the thickness of the two ends of the guide vane is less than the thickness of the middle part; and / or

[0022] There are multiple guide plates, and the guide plates are arranged at intervals from the inner side to the outer side of the corner section.

[0023] As an optional implementation, in some embodiments of the present application, the first hole body further includes a contraction section and a diffusion section, the contraction section is connected between the spray section and the test section, and the inner diameter of the contraction section gradually decreases from the spray section to the test section, and the diffusion section is arranged at the outlet of the test section, and the inner diameter of the diffusion section gradually increases along the direction in which the airflow leaves the test section;

[0024] When the first hole body is connected to the second hole body, the diffuser section is connected between the test section and the reflux section.

[0025] As an optional embodiment, in some embodiments of the present application, the wing full-attitude dual-power opening and closing integrated anti-icing test wind tunnel also includes a movable base, and the movable base includes a first bracket and a second bracket, the first bracket is used to support the first hole body and the auxiliary component, and the second bracket is used to support the second hole body, when the first hole body is separated from the second hole body, the first bracket is separated from the second bracket.

[0026] As an optional embodiment, in some embodiments of the present application, the spray section is provided with a two-phase flow atomizing nozzle, and the two-phase flow atomizing nozzle is arranged on the inner walls on both sides of the spray section opposite to each other and is used to provide spray to the wing. The auxiliary component includes an air compressor and a water pump, and the two-phase flow atomizing nozzle is connected to the air compressor and the water pump, and the water pump is used to provide water flow to the two-phase flow atomizing nozzle, and the air compressor is used to provide air flow to the two-phase flow atomizing nozzle.

[0027] As an optional implementation, in some embodiments of the present application, the auxiliary component also includes a refrigeration device, and the refrigeration device is connected to the cooling section to cool the cooling section.

[0028] As an optional implementation, in some embodiments of the present application, the spray section is further provided with a honeycomb plate, and the honeycomb plate is arranged between the cooling section and the spray section to stabilize the airflow.

[0029] The embodiments of the present application have at least the following beneficial effects: by setting the first hole body and the second hole body in a detachably connected form, the wind tunnel equipment has two usage forms, namely a closed wind tunnel and an open wind tunnel. Since the closed wind tunnel can perform multiple accelerations and multiple coolings, it has the advantage of more accurate and reliable experimental results. Since the open wind tunnel does not need to connect the starting point and the end point of the gas, it has the advantages of simple structure and low manufacturing cost, and the open wind tunnel can use the low temperature of the outside world to achieve low temperature experimental conditions, which is easy to operate and reduces the energy consumption of the experiment. By setting the wind tunnel equipment in a switchable form between closed and open modes, the wind tunnel form can be flexibly set in combination with different experimental requirements, thereby meeting the requirements of efficiency, accuracy and convenience in the experiment.

[0030] The attitude adjustment device can be used to change the test attitude of the wing to meet the test requirements. The power device can provide the first cave body with the power required for the test. By integrating the auxiliary components outside the first cave body, the volume of the first cave body can be reduced, and the miniaturization design of the wind tunnel equipment can be realized. At the same time, the settings inside the first cave body can be simplified, the difficulty of operating the first cave body during the test can be reduced, and the ease and practicality of using the wind tunnel equipment can be improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] The aspects and advantages described and / or attached in the embodiments of the present application will become apparent and easy to understand in conjunction with the following drawings. It should be noted that the embodiments embodied in the following drawings are exemplary and are only used to explain the present application, and cannot be understood as limiting the present application.

[0032] Figure 1 A schematic diagram of the structure of a wind tunnel device provided in an embodiment of the present application;

[0033] Figure 2 A schematic diagram of the wind tunnel equipment provided in an embodiment of the present application in a closed wind tunnel use state;

[0034] Figure 3 A side view of a wind tunnel device provided in an embodiment of the present application;

[0035] Figure 4 A schematic diagram of the wind tunnel equipment provided in an embodiment of the present application in an open wind tunnel use state;

[0036] Figure 5 A schematic diagram of an implementation of the wind tunnel equipment provided in an embodiment of the present application in an open wind tunnel use state;

[0037] Figure 6 A schematic diagram of another implementation of the wind tunnel device provided in an embodiment of the present application in an open wind tunnel use state;

[0038] Figure 7 A schematic diagram of another implementation of the wind tunnel device provided in an embodiment of the present application in an open wind tunnel use state;

[0039] Figure 8 A schematic diagram of the connection between a wing and an attitude adjustment device provided in an embodiment of the present application.

[0040] Reference numerals:

[0041] 100. Wing full-attitude dual-power opening and closing integrated anti-icing test wind tunnel; 10. First tunnel; 11. Test section; 110. Attitude adjustment device; 111. Driving mechanism; 112. Connecting rod mechanism; 12. Power section; 121. First power section; 122. Power connection section; 123. Second acceleration section; 13. Cooling section; 14. Spray section; 141. Two-phase flow atomizing nozzle; 142. Honeycomb plate; 15. First turning Corner section; 16. Second corner section; 17. Contraction section; 18. Diffuser section; 20. Second hole; 21. Reflux section; 22. Third corner section; 23. Fourth corner section; 30. Auxiliary components; 31. Air compressor; 32. Water pump; 33. Refrigeration equipment; 34. Low-temperature water tank; 40. Movable base; 41. First bracket; 42. Second bracket; 50. Low-temperature environment box; 60. High-pressure gas source; 200. Wing. DETAILED DESCRIPTION

[0042] Combine the following Figures 1 to 8 Embodiments of the present application are described in detail, and examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present application, and cannot be understood as limiting the present application.

[0043] In the description of the present application, it should be understood that if the terms "center", "middle", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "axial", "radial", "circumferential" and the like appear, the orientation or position relationship indicated is based on the orientation or position relationship shown in the drawings, which is only for the convenience of describing the present application and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present application. In addition, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present application, unless otherwise specified, "multiple" means two or more.

[0044] In the description of this application, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0045] The icing wind tunnel test method is to use wind tunnel equipment to accelerate, cool and humidify the airflow. By setting the simulated wing to be tested in the wind tunnel, the low-temperature and high-speed airflow with sufficient humidity in the wind tunnel hits the wing to simulate the icing process of the aircraft wing surface in flight, thereby realizing the study of the mechanism of aircraft icing.

[0046] The present application provides a wing full-attitude dual-power opening and closing integrated anti-icing test wind tunnel 100 (hereinafter referred to as wind tunnel equipment 100) for conducting icing wind tunnel tests. Figures 1 to 4 The wind tunnel device 100 includes a first cave body 10, a second cave body 20, a power device (not shown) and an auxiliary component 30. The first cave body 10 is detachably connected to the second cave body 20. The first cave body 10 includes a test section 11. The test section 11 is used to set the wing 200. When the first cave body 10 and the second cave body 20 are combined and connected, the inlet of the first cave body 10 is connected to the outlet of the second cave body 20, and the outlet of the first cave body 10 is connected to the inlet of the second cave body 20 to form a closed wind tunnel. When the first cave body 10 and the second cave body 20 are separated, the first cave body 10 forms an open wind tunnel. An attitude adjustment device 110 is provided in the test section 11. The attitude adjustment device 110 is used to adjust the attitude of the wing 200. The power device is arranged at the inlet of the first cave body 10. The auxiliary component 30 is connected to the first cave body 10 and arranged outside the first cave body 10. The auxiliary component 30 is used to cool the first cave body 10 or provide spray.

[0047] By setting the first hole body 10 and the second hole body 20 in a detachable connection form, the wind tunnel device 100 has two usage forms, namely a closed wind tunnel and an open wind tunnel. Among them, the closed wind tunnel means that the entrance of the first hole body 10 is used as the starting point and the exit of the second hole body 20 is used as the end point. The gas enters the second hole body 20 after passing through the first hole body 10 in the wind tunnel. After the gas flows out of the second hole body 20, since the exit of the second hole body 20 is connected to the entrance of the first hole body 10, that is, the end point of the gas coincides with the starting point, the gas enters the first hole body 10 again, thereby forming a circulating flow of airflow in the wind tunnel, which is conducive to the airflow in the wind tunnel to undergo multiple stages of acceleration or multiple stages of cooling to achieve the required experimental conditions. Since the closed wind tunnel can perform multiple accelerations and multiple coolings, it has the advantage of more accurate and reliable experimental results. An open wind tunnel refers to a wind tunnel with the entrance of the first cave body 10 as the starting point and the outlet of the first cave body 10 as the end point. After the gas enters the first cave body 10 from the outside and reaches the test section 11 for testing, it leaves the first cave body 10 from the outlet of the first cave body 10. The starting point and the end point of the gas do not overlap, and the first cave body 10 is connected to the outside through its starting point and the end point. Since the open wind tunnel does not need to connect the starting point and the end point of the gas, it has the advantages of simple structure and low manufacturing cost. The open wind tunnel can use the low temperature of the outside world to achieve low temperature experimental conditions, which is easy to operate and reduces the energy consumption of the experiment. In this embodiment, the wind tunnel equipment 100 is set to be switchable between closed and open modes. In this way, the wind tunnel form can be flexibly set in combination with different test requirements, thereby meeting the requirements of efficiency, accuracy and convenience in the test.

[0048] By using the attitude adjustment device 110, the test attitude of the wing 200 can be changed to meet the test requirements. The power device can provide the first cave body 10 with the power required for the test. By arranging the auxiliary component 30 outside the first cave body 10, the volume of the first cave body 10 can be reduced, and the miniaturized design of the wind tunnel equipment 100 can be achieved. At the same time, it can also simplify the internal settings of the first cave body 10, reduce the difficulty of operating the first cave body 10 during the test, and improve the simplicity and practicality of the use of the wind tunnel equipment 100. By using the first bracket 41 and the second bracket 42 to carry the first cave body 10 and the second cave body 20 respectively, it can further meet the setting requirements of the first cave body 10 and the second cave body 20 in both the combined connection and the split setting.

[0049] Of course, in other examples, the first bracket 41 and the second bracket 42 can also be connected by a track. For example, the first bracket 41 and the second bracket 42 are simultaneously slidably set on the track on the ground, and the first bracket 41 and the second bracket 42 are slid to move closer to or farther from each other, thereby realizing the mutual connection or separation of the first hole body 10 and the second hole body 20.

[0050] In some embodiments, the first hole body 10 further includes a power section 12, a cooling section 13 and a spray section 14 connected in sequence, the outlet of the spray section 14 is connected to the test section 11, the second hole body 20 includes a return section 21, and the power device includes the power section 12. When the first hole body 10 and the second hole body 20 are combined and connected, one end of the return section 21 is connected to the inlet of the power section 12, and the other end is connected to the outlet of the test section 11, so that the first hole body 10 and the second hole body 20 form a continuous airflow channel; when the first hole body 10 and the second hole body 20 are separated, the inlet of the power section 12 is connected to the outside, and the outlet of the test section 11 is connected to the outside. In the first hole body 10, the power section 12, the cooling section 13 and the spray section 14 can be used to accelerate and cool the incoming gas in sequence, and mix with the sprayed spray in the spray section 14, so as to form low-temperature water droplets with a certain speed, so that the airflow containing water droplets reaches the conditions required for the test, and the airflow is used to hit the wing 200 in the test section 11, so as to achieve the purpose of the test. The reflux section 21 of the second hole body 20 can collect the gas flowing out of the outlet of the first hole body 10 and guide it to the inlet of the first hole body 10 (i.e., the power section 12), so as to facilitate re-acceleration and cooling of the gas. Of course, in other examples, a device for accelerating or cooling the gas can also be set in the second hole body 20, so as to further meet the test requirements for gas acceleration and cooling.

[0051] In order to better connect the first hole body 10 and the second hole body 20 into a ring shape, in some embodiments, the first hole body 10 also includes a first corner segment 15 and a second corner segment 16, the first corner segment 15 is connected between the power segment 12 and the cooling segment 13, and the second corner segment 16 is connected between the cooling segment 13 and the spray segment 14; the second hole body 20 also includes a third corner segment 22 and a fourth corner segment 23, the third corner segment 22 is arranged at the entrance of the reflux segment 21, and the fourth corner segment 23 is arranged at the outlet of the reflux segment 21; when the first hole body 10 and the second hole body 20 are combined and connected, the third corner segment 22 is connected to the test segment 11 and the reflux segment 21, and the fourth corner segment 23 is connected to the reflux segment 21 and the power segment 12. In this way, the power section 12, the cooling section 13, the spray section 14, the test section 11 and the reflux section 21 can be connected in sequence to form a ring structure by using four corner sections, so that when the first cave body 10 and the second cave body 20 are combined and connected, it is convenient to shorten the connection distance between the various functional sections in the wind tunnel equipment 100, so that the structure of the entire wind tunnel equipment 100 is more compact, which is conducive to the miniaturization design of the closed wind tunnel.

[0052] For example, Figure 2As shown, the angles of the four corner sections are all set to approximately 90°, and the wind tunnel device 100 is generally in a rectangular structure. The power section 12, the cooling section 13, the spray section 14, the test section 11 and the reflux section 21 are distributed on each side of the rectangular structure, and the four corner sections are arranged at the four corners of the rectangular structure, so that the structure of the wind tunnel device 100 can be more concise and orderly. Optionally, the auxiliary component 30 is arranged in the hollow part in the middle of the rectangular structure, which further makes the structure of the wind tunnel device 100 more compact.

[0053] Of course, in other examples, the corner segments can also be set to other angles, such as 45°, 60°, 120°, 180°, etc., and in the first cave body 10 and the second cave body 20, only any one, any two or any three of the first corner segment 15, the second corner segment 16, the third corner segment 22 and the fourth corner segment 23 can be set, so that the wind tunnel device 100 forms a circular ring, a runway, a triangle or other shaped structure, which also helps to form the wind tunnel device 100 into a ring structure and achieve the effect of a closed wind tunnel. There is no limitation on the number and form of the corner segments, which can be set according to actual needs.

[0054] In order to allow the airflow to pass through each corner section more smoothly, in some embodiments, the wind tunnel device 100 further includes a guide vane 151, which is disposed at the first corner section 15, the second corner section 16, the third corner section 22, and the fourth corner section 23. The guide vane 151 is used to guide the airflow through the corners. The guide vane 151 can be used to adjust the airflow angle of the structure connected to the upstream of the corner section and adapt to the setting angle of the structure connected to the downstream of the corner section. Figure 2 Taking the illustrated embodiment as an example, when the airflow enters the cooling section 13 from the power section 12, the direction of the airflow can be adjusted by using the first corner section 15 to adapt to the setting direction of the cooling section 13; similarly, when the airflow enters the spray section 14 from the cooling section 13 or enters the reflux section 21 from the test section 11, the second corner section 16 or the third corner section 22 can also be used to make the airflow flow more smoothly, thereby reducing the loss of the airflow in the corner section, ensuring the acceleration and cooling effect of the airflow, thereby improving the accuracy of the test.

[0055] Furthermore, the guide vane 151 is arranged on the angular bisector of the corner section, and the guide vane 151 is bent along the flow direction of the airflow, and the thickness of the two ends of the guide vane 151 is less than the thickness of the middle part. By using the curved shape of the guide vane 151 to guide the gas, the airflow can change its flow direction in the corner section, reducing the energy loss of the airflow. By arranging the guide vane 151 on the angular bisector of the corner section, the guide vane 151 can divert the airflow at a more appropriate time during the process of the airflow passing through the corner section, avoiding the airflow from generating a large impact force on the corner section due to turning too early or too late, resulting in the loss of the airflow. Exemplarily, the guide vane 151 can be arranged to have a wing profile structure, that is, the thickness of the two ends of the guide vane 151 is less than the thickness of the middle part, so that the guiding effect of the guide vane 151 on the airflow can be further improved, achieving a better diversion effect.

[0056] Optionally, a plurality of guide vanes 151 are provided, and the plurality of guide vanes 151 are arranged at intervals from the inner side to the outer side of the corner section. By using the plurality of guide vanes 151 arranged at intervals, the gaps between the guide vanes 151 can be used for gas to pass through, thereby reducing the blocking effect of the guide vanes 151 themselves on the airflow and improving the guiding effect.

[0057] In some embodiments, the auxiliary component 30 further includes a refrigeration device 33, which is connected to the cooling section 13 to cool the cooling section 13. In this way, when the gas passes through the cooling section 13, the refrigeration device 33 can be used to perform heat exchange with the gas, thereby cooling the gas in the cooling section 13 to obtain low-temperature gas to meet the setting requirements of the test conditions.

[0058] In some embodiments, the wind tunnel device 100 further includes a movable base 40 including a first bracket 41 and a second bracket 42, wherein the first bracket 41 is used to carry the first hole body 10 and the auxiliary assembly 30, and the second bracket 42 is used to carry the second hole body 20. When the first hole body 10 is separated from the second hole body 20, the first bracket 41 is separated from the second bracket 42. When the wind tunnel device 100 needs to switch from a closed wind tunnel to an open wind tunnel, by separating the first bracket 41 from the second bracket 42, and removing the second hole body 20 using the second bracket 42, the entrance and exit of the first hole body 10 can be exposed, and an open wind tunnel can be obtained. The first bracket 41 and the second bracket 42 are arranged in a movable form, which can reduce the difficulty of removing the second hole body 20 and improve the convenience of operation. Optionally, universal wheels can be arranged at the bottom of the second bracket 42 to facilitate the movement of the second bracket 42. Or in other examples, universal wheels are also arranged at the bottom of the first bracket 41 to facilitate the movement of the first hole body 10. In this way, the first hole body 10 and the second hole body 20 are both arranged on a movable bracket, thereby realizing a movable design of the wind tunnel device 100 and improving the convenience of the wind tunnel device 100 when in use.

[0059] Exemplarily, when the first hole body 10 and the second hole body 20 are combined and connected, the first bracket 41 and the second bracket 42 can be connected to each other. For example, the bearing surface of the first bracket 41 and the bearing surface of the second bracket 42 are spliced ​​and flush with each other, so that the first hole body 10 and the second hole body 20 are approximately located on the same horizontal plane. The first bracket 41 and the second bracket 42 can be fixedly connected by auxiliary fixing components (such as latches, buckles, bolts, etc.) to avoid mutual sliding between the first bracket 41 and the second bracket 42, which affects the stability of the wind tunnel device 100 during use. Of course, in other examples, when the first hole body 10 and the second hole body 20 are combined and connected, the first bracket 41 and the second bracket 42 may not be directly connected, and only the first hole body 10 and the second hole body 20 are fixed to each other.

[0060] For example, in order to make full use of the space of the movable base 40, the movable base 40 can be provided with two layers of space, wherein the first hole body 10 and the second hole body 20 are provided on the top layer of the movable base 40, and the auxiliary component 30 is provided on the bottom layer, so that the auxiliary component 30 and the first hole body 10 and the second hole body 20 can not interfere with each other, and the auxiliary component 30 is connected to the first hole body 10 or the second hole body 20 upwardly through connecting pipes and other components to ensure the normal operation of the wind tunnel device 100. Specifically, the auxiliary component 30 can be provided on the bottom layer of the first bracket 41, for example, the water tank, the air compressor 31 and the refrigeration equipment 33 are provided on the bottom layer of the first bracket 41, and are provided corresponding to the hollow part of the annular channel enclosed by the first hole body 10 and the second hole body 20, so that it is convenient to provide connecting pipes and the like, so as to connect the auxiliary component 30 with the first hole body 10.

[0061] Since the wind tunnel device 100 provided in this embodiment can be switched between closed and open use states, when switched to an open wind tunnel, the wind tunnel device 100 can utilize a low temperature environment or be connected to a device capable of creating a low temperature environment, thereby achieving the required test conditions. The following will introduce the use of the wind tunnel device 100 when switched to an open device.

[0062] See also Figure 5In some embodiments, the wind tunnel device 100 further includes a low temperature environment box 50. When the first cave body 10 is separated from the second cave body 20, the inlet of the power section 12 is connected to the low temperature environment box, and the outlet of the test section 11 is connected to the low temperature environment box. By using the low temperature environment box, low temperature gas can be provided to the first cave body 10. After the low temperature gas enters the first cave body 10, the power section 12 in the first cave body 10 accelerates the low temperature gas, thereby obtaining low temperature and high speed gas to meet the setting requirements of the test conditions. Under the premise of using the low temperature environment box, the first cave body 10 can also use the refrigeration equipment 33 to further cool the gas, thereby meeting the requirements of the test conditions of lower temperature. Of course, after using the low temperature environment box, the refrigeration equipment 33 can also be stopped, and the gas can be cooled only by the low temperature environment box. Exemplarily, the low temperature environment box can be a device that uses equipment such as an air conditioner to provide a low temperature environment, and the device can be connected to the wind tunnel device 100. Of course, in other examples, the low temperature environment box can be used instead of providing low temperature gas, but the wind tunnel device 100 can be set in a natural low temperature environment to obtain low temperature gas.

[0063] It can be understood that the inlet of the power section 12 is connected to the low-temperature environment box, and the outlet of the test section 11 is connected to the low-temperature environment box. In the case of an open wind tunnel, the gas enters the first cave body 10 from the low-temperature environment, and leaves the first cave body 10 and enters the low-temperature environment after the test is completed. Then the low-temperature gas in the low-temperature environment enters the first cave body 10 again for acceleration and testing. In this way, the gas forms a flow cycle in the low-temperature environment and the first cave body 10.

[0064] For higher test airflow velocities, see Figure 6 In some embodiments, the power device further includes a high-pressure gas source 60. When the first cavity 10 is separated from the second cavity 20, the inlet of the power section 12 is connected to the high-pressure gas source 60. For example, the high-pressure gas source 60 may be an air compressor 31, which can compress the gas to increase the gas pressure, thereby accelerating the gas to meet the requirements of the test conditions.

[0065] Optionally, see Figure 7 The high-pressure gas source 60 can be used in conjunction with a low-temperature environment box, that is, the high-pressure gas source 60 is disposed in the low-temperature environment box, and the outlet of the test section 11 is connected to the low-temperature environment box. In this way, the first hole 10 can obtain high-speed gas while the gas has low-temperature characteristics, thereby better meeting the requirements of the test conditions.

[0066] Exemplarily, the first cave body 10 can obtain high-speed airflow only by relying on the high-pressure gas source 60, and can also further accelerate the airflow by relying on the power section 12 at the same time. Specifically, the power section 12 includes a first acceleration section 121, a power connection section 122, and a second acceleration section 123 connected in sequence, and the outlet of the second acceleration section 123 is connected to the cooling section 13. The first acceleration section 121 and the second acceleration section 123 can accelerate the airflow twice, so as to achieve the required airflow speed. The first acceleration section 121 and the second acceleration section 123 are connected by the power connection section 122, so as to facilitate the smooth connection of airflows of different speeds in the first acceleration section 121 and the second acceleration section 123. Exemplarily, an axial flow fan can be set in the first acceleration section 121 and the second acceleration section 123 to achieve the acceleration of the airflow. Optionally, an axial flow fan can also be set in the power connection section 122 to facilitate the smooth acceleration of the gas. Alternatively, the axial flow fan is only set in either the first acceleration section 121 or the second acceleration section 123. The number of axial flow fans can be flexibly set according to the requirements of test conditions.

[0067] In one example, when the first hole 10 accelerates the gas only by the power section 12, when the first hole 10 is separated from the second hole 20, the entrance of the first acceleration section 121 is connected to the outside. In another example, when the first hole 10 accelerates the gas by the power section 12 and the high-speed gas source, the entrance of the first power section 12 can be connected to the high-pressure gas source 60. In another example, when the first hole 10 accelerates the gas only by the high-pressure gas source 60, one end of the power connection section 122 is connected to the high-pressure gas source 60, and the other end is connected to the cooling section 13. That is, at this time, the first hole 10 may not be provided with the first acceleration section 121 and the second acceleration section 123, and only the power connection section 122 is used to connect the first hole 10 to the high-speed gas source, and obtain high-speed gas by using the effect of the high-speed gas source. In summary, the high-speed gas source and the first acceleration section 121 and the second acceleration section 123 can be used alone or in combination, and the combination method can be flexibly set according to the requirements of the test conditions, so as to meet the requirements of obtaining high-speed gas or saving energy in the test.

[0068] During the wind tunnel test of the wing 200 using the wind tunnel device 100, the different wind angles and wind postures of the wing 200 will affect the icing results of the wing 200. Therefore, the posture of the wing 200 is also an important research variable in the icing experiment. Therefore, the wing 200 that can adjust its posture can better meet the needs of the test. In some embodiments, please refer to Figure 8 The test section 11 is provided with an attitude adjustment device 110, which is used to adjust the attitude of the wing 200. The attitude adjustment device 110 can change the angle at which the wing 200 contacts the airflow in the wind tunnel, thereby obtaining different test conditions to meet the test requirements of the wind tunnel device 100.

[0069] Furthermore, the attitude adjustment device 110 includes a driving mechanism 111 and a connecting rod mechanism 112 connected to the driving mechanism 111, the connecting rod mechanism 112 is used to install the wing 200, and the driving mechanism 111 is used to drive the connecting rod mechanism 112 to adjust the attitude of the wing 200. The driving mechanism 111 drives the connecting rod mechanism 112, and the connecting rod mechanism 112 can drive the wing 200 to move, thereby adjusting the attitude of the wing 200 to meet the test requirements. By setting the attitude adjustment device 110 in the test section 11 and adjusting it by driving the driving mechanism 111, the attitude adjustment of the wing 200 can be achieved without opening the test section 11, thereby ensuring the airtightness of the test section 11 and ensuring that the test conditions in the test section 11 (such as airflow speed, temperature and other parameters) are not destroyed, so that the test results are more reliable.

[0070] Exemplarily, the driving mechanism 111 may be a power component such as a servo, a motor or a cylinder, and the connecting rod structure may be one or more connecting rods hinged to the driving mechanism. The connecting rods may be connected to each other in a hinged manner, and the position and angle of the wing 200 may be adjusted by adjusting the mutual stretching or folding of the connecting rods.

[0071] Optionally, the test section 11 is provided with a plurality of attitude adjustment devices 110, and a plurality of mounting portions (not shown) are provided at intervals on the lower wing surface of the wing 200, and the attitude adjustment devices 110 are connected to the mounting portions one by one. By providing a plurality of mounting portions, it is possible to adjust a plurality of positions on the wing 200, thereby improving the accuracy of attitude adjustment of the wing 200 and better meeting the requirements of the test conditions.

[0072] In some embodiments, the first hole body 10 further includes a contraction section 17 and a diffuser section 18, the contraction section 17 is connected between the spray section 14 and the test section 11, and the inner diameter of the contraction section 17 gradually decreases from the spray section 14 to the test section 11. The diffuser section 18 is arranged at the outlet of the test section 11, and the inner diameter of the diffuser section 18 gradually increases along the direction in which the airflow leaves the test section 11; when the first hole body 10 and the second hole body 20 are combined and connected, the diffuser section 18 is connected between the test section 11 and the reflux section 21. By using the contraction section 17 with a gradually decreasing inner diameter, the speed of the airflow can be further increased, thereby obtaining an airflow with a higher speed. By using the diffuser section 18 with a gradually increasing inner diameter, the high-speed airflow can be decelerated, thereby reducing the energy loss of the airflow during the reflux process.

[0073] In some embodiments, the spray section 14 is provided with a two-phase flow atomizing nozzle 141, which is arranged on the inner walls of the opposite sides of the spray section 14 and is used to provide spray to the wing 200. The auxiliary component 30 includes an air compressor 31 and a water pump 32. The two-phase flow atomizing nozzle 141 is connected to the air compressor 31 and the water pump 32. The water pump 32 is used to provide water flow to the two-phase flow atomizing nozzle 141, and the air compressor 31 is used to provide air flow to the two-phase flow atomizing nozzle 141. By connecting the air compressor 31 and the water pump 32 to the two-phase flow atomizing nozzle 141, the two-phase flow atomizing nozzle 141 can obtain a spray with adjustable particle size to meet the needs of simulating the high-altitude environment of the wing 200 flying. It can be understood that the two-phase flow atomizing nozzle 141 can be connected to the air compressor 31 and the water pump 32 at the same time to realize the manufacture of sprays of different particle sizes. Furthermore, by providing a plurality of two-phase flow atomizing nozzles 141 , the amount of mist output can be changed by adjusting the number of the two-phase flow atomizing nozzles 141 , thereby changing the test conditions and meeting more diverse sample condition requirements.

[0074] Optionally, the water pump 32 is connected to a low temperature water tank 5034, and low temperature water or ice water mixture can be stored in the low temperature water tank 5034, so that the spray can better meet the test conditions. Exemplarily, the low temperature water tank 5034 and the air compressor 31 can be arranged on the first bracket 41, so as to facilitate the orderly arrangement and movement of the entire wind tunnel device 100.

[0075] In some embodiments, the spray section 14 is further provided with a honeycomb plate 142, which is provided between the cooling section 13 and the spray section 14. The honeycomb plate 142 can stabilize the airflow leaving the cooling section 13, especially when the second corner section 16 is provided, the airflow enters the second corner section 16 after leaving the cooling section 13, and the flow direction of the airflow changes when leaving the second corner section 16. In order to make the airflow more stable before entering the spray section 14 or the test section 11, the honeycomb plate 142 is provided, which can make the airflow smoother and ensure the accuracy of the test effect.

[0076] The following will explain the use principle of the wind tunnel device 100 in a closed wind tunnel state: After the wind tunnel device 100 is started, the airflow in the wind tunnel device 100 passes through the power section 12 (such as the first acceleration section 121 and the second acceleration section 123) for one or more accelerations, thereby forming an airflow with a certain speed. The airflow passes through the first corner section 15 and enters the cooling section 13, and forms a low-temperature airflow with a certain speed after cooling in the cooling section 13. The low-temperature airflow passes through the third corner section 22 and enters the spray section 14. The two-phase flow atomizing nozzle 141 of the spray section 14 uses the low-temperature water extracted by the water pump 32 and the water flow compressed by the air compressor 31 to produce supercooled water droplets. The supercooled water droplets are mixed with the low-temperature airflow to form supercooled water droplets (or water mist). The supercooled water droplets are accelerated by the contraction section 17, and the speed is further increased on the basis of the original speed, and high-speed atomized water droplets are formed. The high-speed atomized droplets hit the surface of the wing 200 in the test section 11 to simulate the process of icing on the aircraft wing surface in the air, thereby forming relevant test data. The humidity and speed of the high-speed supercooled water droplets after hitting the wing 200 are reduced, forming a high-speed airflow. The high-speed airflow reduces its speed after passing through the diffuser section 18, and enters the reflow section 21 through the third corner. After flowing through the reflow section 21, it re-enters the power section 12 through the fourth corner to carry out the next cycle.

[0077] When the wind tunnel equipment 100 is used in an open state, the difference from the closed wind tunnel use state is that after the airflow leaves the test section 11 (or the diffuser section 18), the airflow does not directly enter the power section 12, but flows into the external (low-temperature) environment, or a low-temperature environmental box. The airflow enters the power section 12 from the external (low-temperature) environment or the low-temperature environmental box, or from the high-pressure air source 60.

[0078] In the description of this specification, if the reference terms "one embodiment", "some examples", "some embodiments", "illustrative embodiment", "example", "specific example", or "some examples" appear, it means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner.

[0079] The above describes the implementation methods of the present application in detail in conjunction with the accompanying drawings, but the present application is not limited to the above implementation methods. Various changes can be made within the knowledge scope of ordinary technicians in the technical field without departing from the purpose of the present application.

[0080] In the description of this application, if "," appears in the patent name, it means an "and" relationship, not an "or" relationship. For example, if the patent name is "A, B", it means that the content protected by this application is: the technical solution with the subject name A and the technical solution with the subject name B.

Claims

1. A wing full-attitude dual-power opening and closing integrated anti-icing test wind tunnel, characterized by: include a first hole body and a second hole body, wherein the first hole body and the second hole body are detachably connected, the first hole body comprises a test section, the test section is used to set a wing, when the first hole body and the second hole body are combined and connected, the inlet of the first hole body is connected to the outlet of the second hole body, and the outlet of the first hole body is connected to the inlet of the second hole body to form a closed wind tunnel, and when the first hole body and the second hole body are separated, the first hole body forms an open wind tunnel; The test section is provided with an attitude adjustment device, and the attitude adjustment device is used to adjust the attitude of the wing; A power device, the power device is arranged at the entrance of the first hole; an auxiliary component, connected to the first hole body and arranged outside the first hole body, the auxiliary component is used to cool the first hole body or provide spray; The first hole body further comprises a power section, a cooling section and a spray section connected in sequence, the outlet of the spray section is connected to the test section, the second hole body comprises a reflux section, and the power device comprises the power section; When the first hole body and the second hole body are combined and connected, one end of the return section is connected to the inlet of the power section, and the other end is connected to the outlet of the test section, so that the first hole body and the second hole body form a continuous airflow channel; when the first hole body and the second hole body are separated, the inlet of the power section is connected to the outside world, and the outlet of the test section is connected to the outside world; The wing full-attitude dual-power opening and closing integrated anti-icing test wind tunnel also includes a low-temperature environment box. When the first tunnel body is separated from the second tunnel body, the inlet of the power section is connected to the low-temperature environment box, and the outlet of the test section is connected to the low-temperature environment box; and / or The power device further comprises a high-pressure gas source, and when the first hole body is separated from the second hole body, the inlet of the power section is connected to the high-pressure gas source; The wing full-attitude dual-power opening and closing integrated anti-icing test wind tunnel also includes a movable base, the movable base includes a first bracket and a second bracket, the first bracket is used to carry the first hole body and the auxiliary component, the second bracket is used to carry the second hole body, when the first hole body is separated from the second hole body, the first bracket is separated from the second bracket; The spray section is provided with a two-phase flow atomizing nozzle, which is arranged on the inner walls on both sides of the spray section opposite to each other and is used to provide spray to the wing, the auxiliary component includes an air compressor and a water pump, the two-phase flow atomizing nozzle is connected to the air compressor and the water pump, the water pump is used to provide water flow to the two-phase flow atomizing nozzle, and the air compressor is used to provide air flow to the two-phase flow atomizing nozzle; The auxiliary component further comprises a refrigeration device, which is connected to the cooling section for cooling the cooling section.

2. The wing full-attitude dual-power opening and closing integrated anti-icing test wind tunnel according to claim 1 is characterized by: The high-pressure gas source is disposed in the low-temperature environment box, and the outlet of the test section is connected to the low-temperature environment box.

3. The wing full-attitude dual-power opening and closing integrated anti-icing test wind tunnel according to claim 1 is characterized by: The power section comprises a first acceleration section, a power connection section and a second acceleration section connected in sequence, the outlet of the second acceleration section is connected to the cooling section, and when the first hole body is separated from the second hole body, the inlet of the first acceleration section is connected to the outside; or The power section includes a power connection section, and the power device also includes a high-pressure air source. When the first hole body is separated from the second hole body, one end of the power connection section is connected to the high-pressure air source, and the other end is connected to the cooling section.

4. The wing full-attitude dual-power opening and closing integrated anti-icing test wind tunnel according to claim 3 is characterized by: The first acceleration section and / or the second acceleration section is provided with an axial flow fan, and the axial flow fan is used to accelerate the gas.

5. The wing full-attitude dual-power opening and closing integrated anti-icing test wind tunnel according to claim 1 is characterized by: The attitude adjustment device comprises a driving mechanism and a connecting rod mechanism connected to the driving mechanism, the connecting rod mechanism is used to install the wing, and the driving mechanism is used to drive the connecting rod mechanism to adjust the attitude of the wing.

6. The wing full-attitude dual-power opening and closing integrated anti-icing test wind tunnel according to claim 5 is characterized by: The test section is provided with a plurality of the attitude adjustment devices, and a plurality of mounting parts are arranged at intervals on the lower wing surface of the wing, and the attitude adjustment devices are connected to the mounting parts in a one-to-one correspondence.

7. The wing full-attitude dual-power opening and closing integrated anti-icing test wind tunnel according to any one of claims 1 to 6, characterized in that: The first hole body further comprises a first corner section and / or a second corner section, the first corner section is connected between the power section and the cooling section, and the second corner section is connected between the cooling section and the spray section; and / or The second hole body further includes a third corner section and / or a fourth corner section, wherein the third corner section is arranged at the inlet of the reflux section, and the fourth corner section is arranged at the outlet of the reflux section; When the first hole body is connected to the second hole body, the third corner section is connected to the test section and the reflux section, and the fourth corner section is connected to the reflux section and the power section.

8. The wing full-attitude dual-power opening and closing integrated anti-icing test wind tunnel according to claim 7 is characterized by: The wing full-attitude dual-power opening and closing integrated anti-icing test wind tunnel also includes a guide vane, which is arranged at the first corner section, the second corner section, the third corner section and / or the fourth corner section, and the guide vane is used to guide the airflow through the corner.

9. The wing full-attitude dual-power opening and closing integrated anti-icing test wind tunnel according to claim 8 is characterized by: The guide plate is arranged on the bisector of the corner section, the guide plate is bent along the flow direction of the airflow, and the thickness of the two ends of the guide plate is smaller than the thickness of the middle part; and / or There are multiple guide plates, and the guide plates are arranged at intervals from the inner side to the outer side of the corner section.

10. The wing full-attitude dual-power opening and closing integrated anti-icing test wind tunnel according to any one of claims 1 to 6, characterized in that: The first hole body further includes a contraction section and a diffusion section, wherein the contraction section is connected between the spray section and the test section, and the inner diameter of the contraction section gradually decreases from the spray section to the test section, and the diffusion section is arranged at the outlet of the test section, and the inner diameter of the diffusion section gradually increases along the direction in which the airflow leaves the test section; When the first hole body is connected to the second hole body, the diffuser section is connected between the test section and the reflux section.

11. The wing full-attitude dual-power opening and closing integrated anti-icing test wind tunnel according to any one of claims 1 to 6, characterized in that: The spray section is further provided with a honeycomb plate, which is arranged between the cooling section and the spray section to stabilize the airflow.

Images