A high Reynolds number single propeller aerodynamic force measurement test device and its measurement method

Abstract

The present invention discloses a high Reynolds number single propeller aerodynamic force measurement test device and its measurement method, belonging to the field of wind tunnel tests. It includes a rotating shaft balance, an extension shaft body, a torque sensor, a turbine air motor, a motor mounting seat and a strut. The propeller model is connected to the rotating shaft balance, the rotating shaft balance is connected to the torque sensor through the extension shaft body, the torque sensor is connected to the turbine air motor, the strain gauge measures the blade bending moment of the propeller model, the rotating shaft balance measures the aerodynamic force of the propeller model, and the torque sensor monitors the output shaft torque of the turbine air motor. The measurement method: Install the test device of the present invention into the test section of the pressurized wind tunnel, utilize the pressurized wind tunnel, by increasing the internal pressure of the wind tunnel, increase the density of the test flow field, thereby increasing the test Reynolds number, so as to realize the slipstream test of the high Reynolds number propeller aircraft. The present invention improves the accuracy of the propeller model wind tunnel test while reducing the test cost.

Description

Technical Field

[0001] The present invention relates to the field of wind tunnel tests, and particularly to a high Reynolds number single propeller aerodynamic force measurement test device and a measurement method thereof. Background Art

[0002] In the slipstream wind tunnel test of a propeller aircraft, the Reynolds number is one of the key simulation parameters of the wind tunnel test. Too low Reynolds number is an important reason affecting the consistency between the wind tunnel test data and the real flight data. Therefore, the wind tunnel test of a high Reynolds number propeller aircraft is necessary. There are two methods to increase the Reynolds number: increasing the test wind speed and increasing the model size. Among them, increasing the test wind speed is mainly used for simulating another simulation parameter of the wind tunnel test, the Mach number, and is not suitable for collecting the aerodynamic force of the propeller model under high Reynolds number conditions. Increasing the model size will increase the test cost.

[0003] In the slipstream wind tunnel test of a high Reynolds number propeller aircraft, first, it is necessary to measure the aerodynamic force of a single propeller model scaled consistent with the full aircraft model to determine the propeller simulation parameters. Due to the increase in the Reynolds number, the propeller simulation parameters also change accordingly, and the power and torque required for the propeller drive device are greater. Therefore, a high Reynolds number single propeller aerodynamic force measurement test device is needed to provide sufficient driving force for the propeller model. Summary of the Invention

[0004] To solve the above problems, the present invention provides a high Reynolds number single propeller aerodynamic force measurement test device, which solves the problem that the existing measurement test device provides insufficient driving force for the propeller model, and its external dimensions have little influence on the aerodynamic force of the propeller model.

[0005] The technical solution adopted by the present invention is as follows: A high Reynolds number single propeller aerodynamic force measurement test device, including a rotating shaft balance, an extension shaft sleeve, an extension shaft body, a torque sensor, a motor sleeve, a sensor connecting sleeve, a turbine air motor, a motor mounting seat, a strut and a strain gauge. The extension shaft body is supported inside the extension shaft sleeve through bearings. The rear end of the extension shaft body is connected to the front end of the torque sensor through a front coupling. The torque sensor is located inside the sensor connecting sleeve. The rear end of the torque sensor is connected to the output shaft of the turbine air motor through a rear coupling. The tail end of the extension shaft sleeve is fixedly connected to the front end of the sensor connecting sleeve. The tail end of the sensor connecting sleeve is fixedly connected to the front end of the motor sleeve. The turbine air motor is installed on the motor mounting seat. The tail end of the motor sleeve is fixedly connected to the motor mounting seat. The turbine air motor is located inside the enclosed space formed by the motor sleeve and the motor mounting seat. The motor mounting seat is fixedly connected to the strut. The front end of the rotating shaft balance is fixedly connected to the propeller model. Strain gauges are buried near the blade roots of the propeller model. The center inside of the rotating shaft balance is radially positioned with the front end of the extension shaft body through a key and is tightly connected to the front end of the extension shaft body through bolts. The turbine air motor drives the torque sensor, the extension shaft body, the rotating shaft balance and the propeller model to rotate synchronously. The strain gauges measure the blade bending moment of the propeller model. The rotating shaft balance measures the aerodynamic force of the propeller model. The torque sensor monitors the output shaft torque of the turbine air motor.

[0006] Further, the axes of the propeller model, the rotating shaft balance, the extension shaft body, the torque sensor and the turbine air motor are all on the same axis.

[0007] Further, the extension shaft body, the front coupling, the torque sensor, the rear coupling and the output shaft of the turbine air motor are all of hollow structure. The signal lines of the rotating shaft balance and the strain gauges sequentially pass through the internal cavities of the extension shaft body, the front coupling, the torque sensor, the rear coupling and the output shaft of the turbine air motor.

[0008] Further, a conductive slip ring is installed at the tail of the turbine air motor.

[0009] Further, spaces for installing high-pressure air inlet pipelines, exhaust pipelines and equipment wiring are reserved inside the strut.

[0010] Further, a high-pressure air inlet interface is installed on the upper plane of the motor sleeve and is connected to the high-pressure air inlet pipeline.

[0011] Further, fairings are installed on the outsides of the rotating shaft balance, the extension shaft sleeve, the sensor connecting sleeve, the motor sleeve and the motor mounting seat.

[0012] Another object of the present invention is to provide a high Reynolds number single propeller aerodynamic force measurement method obtained by the high Reynolds number single propeller aerodynamic force measurement test device as described above, which increases the Reynolds number by increasing the pressure in the wind tunnel to increase the flow field density, thereby solving the problem of high test cost in the existing test. The specific steps are as follows:

[0013] Step 1: After the wind tunnel is pressurized to the predetermined test pressure, in a windless state, the dynamic data acquisition system collects the initial reading of the rotation axis balance of the propeller model at the same angle as the wind tunnel blowing test;

[0014] Step 2: Start the wind tunnel, and control the supply of high-pressure air to make the propeller model rotate to the initial speed, continue to increase the wind tunnel wind speed to the predetermined wind speed of the test, and increase the supply of high-pressure air to make the propeller model speed reach the predetermined value of the test;

[0015] Step 3: After the wind tunnel flow field and propeller model speed feedback are stable, the dynamic data acquisition system collects the dynamic signals of the rotating shaft balance and torque sensor and the speed signal of the propeller model, and the initial reading obtained in step 1 is deducted from the rotating shaft balance data. After calculation and processing, the aerodynamic force data affected by the dead weight of the propeller model is obtained, and then the aerodynamic force of the propeller model under the high Reynolds number state is obtained after deducting the dead weight of the propeller model.

[0016] Beneficial effects and advantages of the present invention: The present invention improves the accuracy of the propeller model wind tunnel test while reducing the test cost. The test device of the present invention is installed in the test section of the supercharged wind tunnel, and the supercharged wind tunnel is used to increase the internal pressure of the wind tunnel to increase the density of the test flow field, thereby increasing the test Reynolds number, thereby realizing the slipstream test of a high Reynolds number propeller aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a structural schematic diagram of a high Reynolds number single propeller aerodynamic force measurement test device of the present invention;

[0018] Figure 2 for Figure 1 Cross-sectional structure diagram.

[0019] Among them: 1. propeller model, 2. rotating shaft balance, 3. extension shaft sleeve, 4. extension shaft body, 5. torque sensor, 6. front coupling, 7. motor sleeve, 8. sensor connecting sleeve, 9. turbine air motor, 10. rear coupling, 11. motor mounting seat, 12. support rod. DETAILED DESCRIPTION

[0020] The present invention is further described below with reference to the accompanying drawings:

[0021] Example 1

[0022] A high Reynolds number single propeller aerodynamic force measurement test device, comprising a rotating shaft balance 2, an extension shaft sleeve 3, an extension shaft body 4, a torque sensor 5, a motor sleeve 7, a sensor connection sleeve 8, a turbine air motor 9, a motor mounting seat 11, a strut 12 and strain gauges. The extension shaft body 4 is supported inside the extension shaft sleeve 3 by bearings. The rear end of the extension shaft body 4 is connected to the front end of the torque sensor 5 through a front coupling 6. The torque sensor 5 is located inside the sensor connection sleeve 8. The rear end of the torque sensor 5 is connected to the output shaft of the turbine air motor 9 through a rear coupling 10. The tail end of the extension shaft sleeve 3 is fixedly connected to the front end of the sensor connection sleeve 8 by screws. The tail end of the sensor connection sleeve 8 is fixedly connected to the front end of the motor sleeve 7 by screws. The turbine air motor 9 is installed on the motor mounting seat 11 by screws. The tail end of the motor sleeve 7 is fixedly connected to the motor mounting seat 11. The turbine air motor 9 is located inside the enclosed space formed by the motor sleeve 7 and the motor mounting seat 11. The motor mounting seat 11 is fixedly connected to the strut 12. The propeller model 1 includes blades, a front hub and a rear hub. The front hub and the rear hub clamp the blade roots by a screw fixation method. The front end of the rotating shaft balance 2 is fixedly connected to the rear hub. Strain gauges are buried near the blade roots of the propeller model 1. The center inside of the rotating shaft balance 2 is radially positioned with the front end of the extension shaft body 4 through a key and is tightly connected to the front end of the extension shaft body 4 by bolts. The turbine air motor 9 drives the torque sensor 5, the extension shaft body 4, the rotating shaft balance 2 and the propeller model 1 to rotate synchronously. The strain gauges measure the blade bending moment of the propeller model 1. The rotating shaft balance 2 measures the aerodynamic force of the propeller model 1. The torque sensor 5 monitors the output shaft torque of the turbine air motor 9.

[0023] The axes of the propeller model 1, the rotating shaft balance 2, the extension shaft body 4, the torque sensor 5 and the turbine air motor 9 are all on the same axis.

[0024] The extension shaft body 4, the front coupling 6, the torque sensor 5, the rear coupling 10 and the output shaft of the turbine air motor 9 are all of hollow structures. The signal lines of the rotating shaft balance 2 and the strain gauge signal lines sequentially pass through the internal cavities of the extension shaft body 4, the front coupling 6, the torque sensor 5, the rear coupling 10 and the output shaft of the turbine air motor 9. A conductive slip ring is installed at the tail of the turbine air motor 9. Inside the strut 12, there are reserved installation spaces for high-pressure air inlet pipelines, exhaust pipelines and equipment wiring. A high-pressure air inlet interface is installed on the upper plane of the motor sleeve 7 and is connected to the high-pressure air inlet pipeline. Fairings are installed outside the rotating shaft balance 2, the extension shaft sleeve 3, the sensor connection sleeve 8, the motor sleeve 7 and the motor mounting seat 11.

[0025] Example 2

[0026] This embodiment uses the test equipment provided in Example 1 to obtain a high Reynolds number single propeller aerodynamic measurement method, using a low-speed pressurized wind tunnel to increase the pressure in the wind tunnel and thus increase the flow field density to obtain a high Reynolds number environment for propeller testing. The specific steps are as follows:

[0027] Step 1: After the wind tunnel is pressurized to the predetermined test pressure, in a windless state, the dynamic data acquisition system collects the initial reading of the rotating axis balance 2 of the propeller model 1 at the same angle as the wind tunnel blowing test;

[0028] Step 2: Start the wind tunnel, and control the supply of high-pressure air to make the propeller model 1 rotate to the initial speed, continue to increase the wind tunnel wind speed to the predetermined wind speed of the test, and increase the supply of high-pressure air to make the speed of the propeller model 1 reach the predetermined value of the test;

[0029] Step 3: After the wind tunnel flow field and the speed feedback of the propeller model 1 are stabilized, the dynamic data acquisition system collects the dynamic signals of the rotating shaft balance 2 and the torque sensor 5 and the speed signal of the propeller model 1, and the initial reading obtained in step 1 is deducted from the data of the rotating shaft balance 2. After calculation and processing, the aerodynamic data with the deadweight of the propeller model 1 is obtained, and then the aerodynamic force of the propeller model 1 under the high Reynolds number state is obtained after deducting the deadweight of the propeller model 1.

Claims

1. A high Reynolds number single propeller aerodynamic force measurement test device, comprising a rotating shaft balance (2), an extension shaft sleeve (3), an extension shaft body (4), a torque sensor (5), a motor sleeve (7), a sensor connecting sleeve (8), a turbine air motor (9), a motor mounting seat (11), a strut (12) and strain gauges, characterized in that: The extended shaft body (4) is supported inside the extended shaft sleeve (3) through a bearing, the rear end of the extended shaft body (4) is connected to the front end of the torque sensor (5) through a front coupling (6), the torque sensor (5) is located in the sensor connecting sleeve (8), the rear end of the torque sensor (5) is connected to the output shaft of the turbine air motor (9) through a rear coupling (10), the tail end of the extended shaft sleeve (3) is fixedly connected to the front end of the sensor connecting sleeve (8), the tail end of the sensor connecting sleeve (8) is fixedly connected to the front end of the motor sleeve (7), the turbine air motor (9) is installed on the motor mounting seat (11), the tail end of the motor sleeve (7) is fixedly connected to the motor mounting seat (11), and the turbine air motor (9) is located between the motor sleeve (7) and the motor mounting seat. (11), the motor mounting seat (11) is fixedly connected to the support rod (12); the front end of the rotating shaft balance (2) is fixedly connected to the propeller model (1), and a strain gauge is buried near the root of the blade of the propeller model (1). The center of the rotating shaft balance (2) is radially positioned with the front end of the extended shaft body (4) through a key, and is fastened to the front end of the extended shaft body (4) through bolts; the turbine air motor (9) drives the torque sensor (5), the extended shaft body (4), the rotating shaft balance (2) and the propeller model (1) to rotate synchronously; the strain gauge measures the blade bending moment of the propeller model (1), the rotating shaft balance (2) measures the aerodynamic force of the propeller model (1), and the torque sensor (5) monitors the output shaft torque of the turbine air motor (9).

2. The high Reynolds number single propeller aerodynamic force measurement test device according to claim 1, characterized in that: The axes of the propeller model (1), the rotating shaft balance (2), the extended shaft body (4), the torque sensor (5) and the turbine air motor (9) are all located on the same axis.

3. The high Reynolds number single propeller aerodynamic force measurement test device according to claim 2, characterized in that: The extended shaft body (4), the front coupling (6), the torque sensor (5), the rear coupling (10) and the output shaft of the turbine air motor (9) are all hollow structures, and the signal line of the rotating shaft balance (2) and the signal line of the strain gauge pass through the internal cavity of the extended shaft body (4), the front coupling (6), the torque sensor (5), the rear coupling (10) and the output shaft of the turbine air motor (9) in sequence.

4. A high Reynolds number single propeller aerodynamic force measurement test device according to claim 3, characterized in that: A conductive slip ring is installed at the tail of the turbine air motor (9).

5. A high Reynolds number single propeller aerodynamic force measurement test device according to claim 4, characterized in that: The support rod (12) is internally reserved with a high-pressure air intake pipeline installation space, an exhaust pipeline installation space, and an equipment wiring installation space.

6. The high Reynolds number single propeller aerodynamic force measurement test device according to claim 5, characterized in that: The upper plane of the motor sleeve (7) is provided with a high-pressure air intake interface, and is connected to the high-pressure air intake pipeline.

7. A high Reynolds number single propeller aerodynamic force measurement test device according to any one of claims 1-6, characterized in that: The rotating shaft balance (2), the extended shaft sleeve (3), the sensor connecting sleeve (8), the motor sleeve (7) and the motor mounting seat (11) are all equipped with fairings on the outside.

8. A high Reynolds number single propeller aerodynamic force measurement method obtained from the high Reynolds number single propeller aerodynamic force measurement test device according to claim 7, which increases the Reynolds number by increasing the pressure in the wind tunnel to increase the flow field density, and is characterized in that The specific steps of the method are as follows: Step 1: After the wind tunnel is pressurized to a predetermined test pressure, in a windless state, a dynamic data acquisition system collects initial readings of a rotating axis balance (2) of a propeller model (1) at the same angle as that of a wind tunnel blowing test; Step 2: Start the wind tunnel, and at the same time, control the supply of high-pressure gas to rotate the propeller model (1) to the initial rotational speed. Then continue to increase the wind tunnel airspeed to the predetermined test airspeed, and increase the supply of high-pressure gas to make the rotational speed of the propeller model (1) reach the predetermined test value. Step 3: After the wind tunnel flow field and the rotational speed of the propeller model (1) are feedback-stabilized, the dynamic data acquisition system collects the dynamic signals of the rotating shaft balance (2) and the torque sensor (5) and the rotational speed signal of the propeller model (1). Subtract the initial readings obtained in Step 1 from the data of the rotating shaft balance (2). After calculation and processing, the aerodynamic force data affected by the self-weight of the propeller model (1) is obtained. Then, after subtracting the self-weight of the propeller model (1), the aerodynamic force of the propeller model (1) under the high Reynolds number condition is obtained.

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