A wind tunnel test system for air-water separation in the air intake of a surface aircraft

Abstract

A wind tunnel testing system for air-water separation in the air intake of a surface aircraft belongs to the field of wind tunnel testing technology. It solves the problem in existing technologies where the air-water separation performance of the air intake cannot be accurately evaluated under different flight conditions. Key technical points: A water mist spraying device is located at the front of the wind tunnel test section; a support device is located in the uniform two-phase flow field region in the middle of the wind tunnel test section; the model is mounted on the support device; an environmental water content measuring device is located between the water mist spraying device and the support device; the outlet of the air intake is connected to the front end of the air intake water content measuring device, and the rear end of the air intake water content measuring device is connected to the air intake flow simulation device; the measurement and control system is located outside the wind tunnel test section. This invention can simultaneously reproduce the sea state, flight speed, flight attitude, and the working state of the air intake and propeller of the surface aircraft. The test scenario highly matches the actual working conditions, and the system simulation accuracy is high.

Description

Technical Field

[0001] This invention relates to the field of wind tunnel testing technology, specifically to a wind tunnel testing system for air-water separation in the air intake of a surface aircraft. Background Technology

[0002] Surface-to-surface aircraft, including seaplanes and ground-effect vehicles, operate under critical conditions such as takeoff and landing at sea and sea-skimming patrols. They are subjected to a complex flow field of air-water two-phase mixing due to the combined effects of breaking waves, airflow disturbances, airflow splash, and a humid environment. This complex two-phase flow environment places stringent demands on the air-water separation performance of the air intake. If air-water separation is incomplete, moisture and salt spray will intrude into the power system with the airflow, causing a series of problems such as air intake obstruction, reduced combustion efficiency, and corrosion and wear of power components. In severe cases, this can directly lead to power system failure, causing flight accidents and endangering flight safety.

[0003] Wind tunnel testing is an important technical means to evaluate the performance of air intakes. However, existing wind tunnel testing technologies cannot simultaneously reproduce real flight attitudes, sea wave conditions, and marine hot and humid salt spray environments. They cannot accurately test the actual working performance of existing protective structures and air-water separation structures, lack targeted and effective testing methods, and cannot provide reliable test data support.

[0004] Therefore, there is an urgent need to propose a wind tunnel test system for air-water separation in the air intake of a surface aircraft to solve the problem that the air-water separation performance of the air intake cannot be accurately evaluated under different flight conditions in the existing technology. Summary of the Invention

[0005] In view of the above facts, in order to solve the problem that the air-water separation performance of the air intake under different flight conditions cannot be accurately evaluated in the prior art, the present invention designs a wind tunnel test system for air-water separation of the air intake of a surface aircraft.

[0006] To achieve the above objectives, the present invention adopts the following technical solution:

[0007] A wind tunnel test system for air-water separation in the air intake of a surface aircraft includes a wind tunnel test section, a water mist spraying device, an environmental water content measuring device, a model, a support device, an air intake flow simulation device, an air intake water content measuring device, and a measurement and control system.

[0008] The water mist spraying device is located at the front of the wind tunnel test section, the support device is located in the middle section of the wind tunnel test section in the uniform two-phase flow field area, the model is installed on the support device, and the environmental water content measuring device is located between the water mist spraying device and the support device.

[0009] The model includes a propeller drive unit, an air intake, a propeller, a transmission unit, and a model shell;

[0010] The propeller drive device is installed inside the tail end of the model. The output end of the propeller drive device is connected to the input end of the transmission device. The output end of the transmission device is connected to the propeller. The propeller is set at the head end of the model. The air intake extends into the model shell. The model shell covers the propeller drive device, air intake, and transmission device.

[0011] The support device includes a ventilated support rod and a slide rail turntable mechanism. The model shell is mounted on the ventilated support rod, and the ventilated support rod is mounted on the slide rail turntable mechanism. The angle of attack is adjusted by the slide rail, and the side slip angle is adjusted by the turntable.

[0012] The outlet of the air intake is connected to the front end of the air intake water content measuring device, and the rear end of the air intake water content measuring device is connected to the air intake flow simulation device.

[0013] The measurement and control system is located outside the wind tunnel test section. The water mist spraying device, the environmental water content measuring device, the air intake flow simulation device, and the air intake water content measuring device are all connected to the measurement and control system via signal lines.

[0014] Furthermore: the intake flow simulation device includes a suction device, a regulating valve, a flow meter, and a flexible hose;

[0015] The rear end of the air intake water content measuring device, the flow meter, the regulating valve, and the suction device are connected in series via a soft rubber tube.

[0016] Furthermore: the flow meter is a subcritical Venturi flow meter, the regulating valve is an annular slit regulating valve, the suction device is a 2kg / s ejector, and the inner diameter of the soft rubber tube is 120mm.

[0017] Furthermore: the maximum output flow rate of the suction device is not less than 1.2 times the maximum matching flow rate of the air inlet, and the flow rate adjustment accuracy and measurement accuracy are greater than 5‰.

[0018] Furthermore: the wind tunnel test section is an open test section with dimensions of 2.5m × 2.5m. The range of the uniform two-phase flow field region in the middle section of the wind tunnel test section is greater than or equal to 1.5 times the diameter of the propeller, and the wind speed is 5-150m / s. An interface for connecting to the test system is provided on the wind tunnel test section.

[0019] Furthermore, the water mist spraying device is a hydraulically driven array of 5 rows and 10 columns of detachable nozzles, with fresh water or salt solution as the water source, producing water droplets with a diameter of 1-1000μm.

[0020] Furthermore, the angle of attack can be adjusted from -25° to 25°, and the sideslip angle can be adjusted from -25° to 25°.

[0021] Furthermore: the environmental water content measuring device uses a Doppler particle analyzer, and the air intake water content measuring device uses a weighing water collection device. The measurement accuracy of both the environmental water content measuring device and the air intake water content measuring device is greater than 5%.

[0022] Furthermore, the diameter of the propeller is 0.8m.

[0023] Furthermore, the model is a scaled-down model of the propulsion system of a surface aircraft, and the propeller drive device is a turbine air motor or an electric motor, which meets the requirements for scaled-down simulation of the propeller dynamic characteristics of the real aircraft.

[0024] ;

[0025] RPM mod =RPM real ×ratio;

[0026] in: The power of the propeller drive unit;

[0027] The power of the propeller drive unit of the actual aircraft;

[0028] RPM mod The propeller speed of the model;

[0029] RPM real This represents the propeller speed of the actual aircraft.

[0030] ratio is the model scaling factor.

[0031] The beneficial effects of this invention are as follows:

[0032] 1. This invention can simultaneously reproduce the sea conditions, flight speed, flight attitude, air intake and propeller working status of a surface aircraft. The test scenario is highly consistent with the actual working conditions, and the system simulation accuracy is high.

[0033] 2. This invention allows for flexible adjustment of incoming flow velocity, sea state parameters, model attitude angle, air intake flow rate, propeller speed, and has good system adaptability.

[0034] 3. The measuring devices in each stage of this invention have excellent accuracy, and when combined with the integrated measurement and control system, the test results obtained by the system are highly reliable. Attached Figure Description

[0035] Figure 1 This is a schematic diagram of the structure of the present invention;

[0036] Figure 2 This is a schematic diagram of the support device in this invention;

[0037] Figure 3 This is a schematic diagram of the structure of the model in this invention;

[0038] Figure 4 This is a schematic diagram of the intake flow simulation device in this invention.

[0039] In the diagram: 1-Wind tunnel test section, 2-Water mist spraying device, 3-Environmental water content measuring device, 4-Model, 5-Support device, 6-Propeller drive device, 7-Inlet flow simulation device, 8-Inlet water content measuring device, 9-Measurement and control system, 10-Inlet, 11-Propeller, 12-Transmission device, 13-Suction equipment, 14-Regulating valve, 15-Flow meter, 16-Soft hose; 17-Ventilation support rod, 18-Slide rail turntable mechanism. Detailed Implementation

[0040] To enable those skilled in the art to better understand the present application, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present application, and not all embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative effort should fall within the scope of protection of the present application.

[0041] The terms "set up," "connect," and "fix" should be interpreted broadly. For example, "connection" can be a fixed connection, a detachable connection, or an integral structure; it can be a mechanical connection, a direct connection, or an indirect connection through an intermediate medium, or an internal connection between two devices, components, or parts. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0042] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. This application will now be described in detail with reference to the accompanying drawings and embodiments.

[0043] Preferred embodiments of the present invention will now be described in detail with reference to the accompanying drawings.

[0044] Example 1: Reference Figure 1-4 This embodiment describes a wind tunnel test system for air-water separation in the air intake of a surface aircraft, comprising a wind tunnel test section 1, a water mist spraying device 2, an environmental water content measuring device 3, a model 4, a support device 5, an air intake flow simulation device 7, an air intake water content measuring device 8, and a measurement and control system 9.

[0045] The water mist spraying device 2 is set at the front of the wind tunnel test section 1, the support device 5 is set in the uniform two-phase flow field area in the middle section of the wind tunnel test section 1, the model 4 is installed on the support device 5, and the environmental water content measuring device 3 is set between the water mist spraying device 2 and the support device 5.

[0046] The model 4 includes a propeller drive unit 6, an air intake 10, a propeller 11, a transmission device 12, and a model shell;

[0047] The propeller drive device 6 is installed inside the tail end of the model 4. The output end of the propeller drive device 6 is connected to the input end of the transmission device 12. The output end of the transmission device 12 is connected to the propeller 11. The propeller 11 is located at the head end of the model 4. The air intake 10 extends into the model shell. The model shell covers the propeller drive device 6, the air intake 10, and the transmission device 12.

[0048] The support device 5 includes a ventilation support rod 17 and a slide rail turntable mechanism 18. The model shell is mounted on the ventilation support rod 17, and the ventilation support rod 17 is mounted on the slide rail turntable mechanism 18. The angle of attack is adjusted by the slide rail, and the side slip angle is adjusted by the turntable.

[0049] The outlet of the air intake duct 10 is connected to the front end of the air intake duct water content measuring device 8, and the rear end of the air intake duct water content measuring device 8 is connected to the air intake duct flow simulation device 7.

[0050] The measurement and control system 9 is located outside the wind tunnel test section 1. The water mist spraying device 2, the environmental water content measuring device 3, the air intake flow simulation device 7, and the air intake water content measuring device 8 are all connected to the measurement and control system 9 via signal lines.

[0051] More specifically: the intake flow simulation device 7 includes a suction device 13, a regulating valve 14, a flow meter 15, and a flexible hose 16;

[0052] The rear end of the air intake water content measuring device 8, the flow meter 15, the regulating valve 14, and the suction device 13 are connected in series via a soft rubber tube 16.

[0053] More specifically: the flow meter 15 is a subcritical Venturi flow meter, the regulating valve 14 is an annular slit regulating valve, the suction device 13 is a 2kg / s ejector, and the inner diameter of the soft rubber tube 16 is 120mm.

[0054] More specifically: the maximum output flow rate of the suction device 13 is not less than 1.2 times the maximum matching flow rate of the air inlet 10, and the flow rate adjustment accuracy and measurement accuracy are greater than 5‰.

[0055] More specifically: the wind tunnel test section 1 is an open test section with dimensions of 2.5m × 2.5m. The range of the uniform two-phase flow field region in the middle section of the wind tunnel test section 1 is greater than or equal to 1.5 times the diameter of the propeller 11, and the wind speed is 5-150m / s. The wind tunnel test section 1 is equipped with an interface for connecting to the test system.

[0056] More specifically: the water mist spraying device 2 is a hydraulically driven array of 5 rows and 10 columns of detachable nozzles. The water source is fresh water or salt solution, which produces water droplets with a diameter of 1-1000μm. The size, concentration and distribution of water droplets in the uniform two-phase flow field in the middle section can be adjusted by changing the hydraulic strength, nozzle orifice diameter, number of nozzles, nozzle spatial position and combination nozzle model.

[0057] More specifically: the angle of attack can be adjusted from -25 to 25°, and the sideslip angle can be adjusted from -25 to 25°, meeting the angle simulation requirements for all flight states of the watercraft.

[0058] More specifically: the environmental water content measuring device 3 uses a Doppler particle analyzer for measurement, and the air intake water content measuring device 8 uses a weighing water collection device for measurement. The measurement accuracy of both the environmental water content measuring device 3 and the air intake water content measuring device 8 is greater than 5%.

[0059] More specifically: the diameter of the propeller 11 is 0.8m.

[0060] More specifically: Model 4 is a scaled-down model of the propulsion system of a surface aircraft, and the propeller drive device 6 is a turbine air motor or electric motor, meeting the requirements for scaled-down simulation of the propeller dynamic characteristics of the real aircraft.

[0061] ;

[0062] RPM mod =RPM real ×ratio;

[0063] in: The power of the propeller drive unit 6;

[0064] The power of the propeller drive unit of the actual aircraft;

[0065] RPM mod The propeller speed of Model 4;

[0066] RPM real This represents the propeller speed of the actual aircraft.

[0067] ratio is the model scaling factor.

[0068] More specifically: the scale of the model 4 is selected according to the size and power design of the selected propeller drive device 6, which can ensure that the volume of the propeller drive device 6 is adapted to the installation space inside the model 4.

[0069] More specifically: the wind tunnel test section 1 is used to construct the basic airflow environment; the water mist spraying device 2 is used to simulate water mist or salt mist fields under different wave levels on the sea surface, reproducing the water surface environment during the actual navigation of the seaplane; the environmental water content measuring device 3 is used to detect the water content of the external flow field; the support device 5 is used to stabilize the model 4 and realize attitude angle adjustment; the propeller drive device 6 is used to drive the propeller 11 to rotate; the air intake flow simulation device 7 is used to construct the internal flow field of the air intake; the air intake water content measuring device 8 is used to detect the water content of the separated air intake; and the measurement and control system 9 is used to coordinate the control of each device and the acquisition, processing and analysis of test data.

[0070] 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, 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 therein; as long as there is no structural conflict, the various features in the specific embodiments disclosed in this application can be combined with each other in any way, and will not cause the substance of the corresponding technical solutions to deviate from the scope of the technical solutions of the present invention.

[0071] Furthermore, it should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style is merely for clarity. Those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. A wind tunnel test system for air-water separation in the air intake of a surface aircraft, characterized in that, Includes wind tunnel test section (1), water mist spraying device (2), environmental water content measuring device (3), model (4), support device (5), air intake flow simulation device (7), air intake water content measuring device (8), and measurement and control system (9). The water mist spraying device (2) is set in the front section of the wind tunnel test section (1), the support device (5) is set in the uniform two-phase flow field area in the middle section of the wind tunnel test section (1), the model (4) is installed on the support device (5), and the environmental water content measuring device (3) is set between the water mist spraying device (2) and the support device (5). The model (4) includes a propeller drive unit (6), an air intake (10), a propeller (11), a transmission device (12), and a model shell; The propeller drive device (6) is installed inside the tail end of the model (4). The output end of the propeller drive device (6) is connected to the input end of the transmission device (12). The output end of the transmission device (12) is connected to the propeller (11). The propeller (11) is set at the head end of the model (4). The air intake (10) extends into the model shell. The model shell covers the propeller drive device (6), the air intake (10), and the transmission device (12). The support device (5) includes a ventilation support rod (17) and a slide rail turntable mechanism (18). The model shell is installed on the ventilation support rod (17), and the ventilation support rod (17) is installed on the slide rail turntable mechanism (18). The angle of attack is adjusted by the slide rail, and the side sliding angle is adjusted by the turntable. The outlet of the air intake (10) is connected to the front end of the air intake water content measuring device (8), and the rear end of the air intake water content measuring device (8) is connected to the air intake flow simulation device (7). The measurement and control system (9) is set outside the wind tunnel test section (1). The water mist spraying device (2), the environmental water content measuring device (3), the air intake flow simulation device (7), and the air intake water content measuring device (8) are all connected to the measurement and control system (9) via signal lines.

2. The wind tunnel test system for air-water separation in the air intake of a surface aircraft according to claim 1, characterized in that, The air intake flow simulation device (7) includes a suction device (13), a regulating valve (14), a flow meter (15), and a soft rubber tube (16). The rear end of the air intake water content measuring device (8), the flow meter (15), the regulating valve (14), and the suction device (13) are connected in series via a soft rubber tube (16).

3. The wind tunnel test system for air-water separation in the air intake of a surface aircraft according to claim 2, characterized in that, The flow meter (15) is a subcritical Venturi flow meter, the regulating valve (14) is an annular slit regulating valve, the suction device (13) is a 2kg / s ejector, and the inner diameter of the soft rubber tube (16) is 120mm.

4. The wind tunnel test system for air-water separation in the air intake of a surface aircraft according to claim 3, characterized in that, The maximum output flow of the suction device (13) is not less than 1.2 times the maximum matching flow of the air inlet (10), and the flow regulation accuracy and measurement accuracy are greater than 5‰.

5. A wind tunnel test system for air-water separation in the air intake of a surface aircraft according to claim 1, characterized in that, The wind tunnel test section (1) is an open test section with a size of 2.5m×2.5m. The range of the uniform two-phase flow field in the middle section of the wind tunnel test section (1) is greater than or equal to 1.5 times the diameter of the propeller (11), and the wind speed is 5-150m / s. An interface for connecting to the test system is provided on the wind tunnel test section (1).

6. The wind tunnel test system for air-water separation in the air intake of a surface aircraft according to claim 1, characterized in that, The water mist spraying device (2) is a hydraulically driven array of 5 rows and 10 columns of detachable nozzles. The water source is fresh water or salt solution, which produces water droplets with a diameter of 1-1000μm.

7. A wind tunnel test system for air-water separation in the air intake of a surface aircraft according to claim 1, characterized in that, The angle of attack can be adjusted from -25° to 25°, and the sideslip angle can be adjusted from -25° to 25°.

8. A wind tunnel test system for air-water separation in the air intake of a surface aircraft according to claim 1, characterized in that, The environmental water content measuring device (3) is measured using a Doppler particle analyzer, and the air intake water content measuring device (8) is measured using a weighing water collection device. The measurement accuracy of both the environmental water content measuring device (3) and the air intake water content measuring device (8) is greater than 5%.

9. A wind tunnel test system for air-water separation in the air intake of a surface aircraft according to claim 1, characterized in that, The diameter of the propeller (11) is 0.8m.

10. A wind tunnel test system for air-water separation in the air intake of a surface aircraft according to claim 1, characterized in that, The model (4) is a scaled-down model of the propulsion system of the watercraft, and the propeller drive device (6) is a turbine air motor or electric motor, which meets the requirements of scaled-down simulation of the propeller power characteristics of the real aircraft: ； RPM mod =RPM real ×ratio; in: The power of the propeller drive unit (6); This refers to the power of the propeller drive unit on the actual aircraft. RPM mod The propeller speed of model (4); RPM real This represents the propeller speed of the actual aircraft. ratio is the model scaling ratio.

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