Variable deflection tail pulse pressure measurement wind tunnel model

Abstract

A variable rudder angle tail rudder fluctuating pressure measurement wind tunnel model comprises an aircraft model, at least one tail rudder model, at least one pressure sensor, at least one angle piece and a support rod. The tail rudder model is installed at the rear mounting hole of the aircraft model through a bottom cylindrical rudder shaft; the middle of the rudder shaft is slotted rearward, and there is a rearward through hole corresponding to the position of the bottom of the aircraft model; the angle piece is inserted into the slot through the rearward through hole and fixes the angle of the tail rudder model, and the rudder angle adjustment is realized by replacing different angle pieces. The tail rudder model surface has an opening, and circular through holes are arranged on the tail rudder and the opening for installing the pressure sensor according to the test measurement requirements. The variable rudder angle tail rudder fluctuating pressure measurement wind tunnel model of the application realizes the installation of the pressure sensor on the tail rudder in the tail rudder buffet and load measurement wind tunnel test, and can realize quick rudder angle adjustment during the test process, obtain the fluctuating pressure under various rudder angles, avoid disassembling the model and connecting the signal line, and improve the test efficiency.

Description

Technical Field

[0001] This application belongs to the field of aerospace testing technology, and more specifically, relates to a wind tunnel model for measuring the pulsating pressure of a variable rudder deflection tail rudder. Background Technology

[0002] Pulsating pressure, as an excitation source for aircraft structural response and a root cause of aerodynamic noise, is a crucial aspect of aircraft aerodynamics research. The tail rudder, located at the rear of the aircraft, is highly susceptible to interference from incoming airflow, especially during high angle-of-attack flight. The tail rudder, situated on the leeward side, is prone to buffeting due to the influence of separated vortices, leading to structural damage. Therefore, wind tunnel testing with pulsating pressure is necessary to obtain unsteady aerodynamic loads acting on the tail rudder under various incoming flow conditions and rudder deflection angles for structural strength design. Currently, the commonly used pulsating pressure measurement technique involves testing a scaled-down model in a wind tunnel. The model must meet geometric similarity criteria. The testing element is a high-precision, wide-frequency-response, fast-response dynamic pressure sensor, installed with its head flush with the model surface. Since the pressure sensor needs to be connected to the acquisition system via a signal line, and the area below the tail rudder typically forms the mating section between the support rod and the model, interference with the signal line must be carefully considered during the installation of the support rod and model, and when the tail rudder deflection angle changes. In order to obtain test data under various rudder deflection angles, it was previously necessary to process tail rudder models with multiple angles. When changing the rudder deflection angle, the tail rudder model had to be removed and replaced, and the sensor signal lines had to be reconnected, which brought difficulties to the test measurement and resulted in low test efficiency. Utility Model Content

[0003] The technical problem solved by this application is to overcome the shortcomings of the prior art and provide a wind tunnel model for measuring the pulsating pressure of the tail rudder with a variable rudder deflection angle, so as to solve the problems of installing the pressure sensor and its signal line on the tail rudder model and realizing the change of rudder deflection angle.

[0004] The technical solution provided in this application is as follows:

[0005] A wind tunnel model for measuring tail rudder pulsation pressure with variable rudder deflection includes:

[0006] The aircraft model has at least one mounting hole on its outer wall for mounting a tail rudder model, and a rear through hole. One end of the rear through hole is connected to the mounting hole, and the other end extends through to the end face of the aircraft model.

[0007] The tail rudder model has a rudder shaft connected to one side, which is inserted into the mounting hole. The rudder shaft has a slot on the side facing the rear through hole.

[0008] Pressure sensor, connected to the tail rudder model;

[0009] Angle plates are inserted into slots through rearward through holes to fix the angle of the tail rudder model; the rudder deflection angle can be adjusted by replacing different angle plates.

[0010] Support rod, attached to the end of the aircraft model.

[0011] Furthermore, multiple mounting holes are provided, and these mounting holes are evenly distributed in the same circumferential position on the aircraft model.

[0012] Furthermore, the tail rudder model has an internal cavity, and its surface has a cover that covers the cavity without altering the original shape of the tail rudder model. The tail rudder and the cover have circular through holes, through which the head of the pressure sensor protrudes.

[0013] Furthermore, the rudder shaft has an opening on the side away from the slot, which communicates with the cavity. The aircraft model has a forward through hole, which is opposite to the opening, so that the signal line of the pressure sensor can be led out from the opening through the forward through hole in the cavity, and then enter the support rod to connect to the test acquisition equipment for test measurement.

[0014] Furthermore, the pressure sensor is a thin-film pulsating pressure sensor, and the depth of the cavity is not less than the thickness of the pressure sensor, and the width of the cavity is not less than the diameter of the pressure sensor.

[0015] Furthermore, the pressure-sensitive head of the pressure sensor does not extend beyond the outer edge of the circular through hole and is within 0.5 mm below the outer edge of the circular through hole.

[0016] Furthermore, the difference between the diameter of the circular through hole and the diameter of the pressure sensor head is no greater than 0.1 mm.

[0017] Furthermore, the angle plate is a quadrilateral sheet with a set thickness. Two sides of the angle plate are parallel to each other, the third side is perpendicular to the two parallel sides, and the fourth side is the side that is in close contact with the bottom of the slot. The rudder deflection angle can be adjusted by the different included angles between the fourth side and the two parallel sides. The distance between the two parallel sides is the same as the width of the rear through hole, and the thickness of the angle plate is the same as the height of the rear through hole.

[0018] In summary, this application includes at least the following beneficial technical effects:

[0019] In wind tunnel tests for tail rudder flutter and load measurement, pressure sensors can be installed on the tail rudder, and rapid adjustment of the rudder deflection angle can be achieved during the test to obtain pulsating pressure at various rudder deflection angles, avoiding disassembly of the model and connection of signal lines, thus improving test efficiency. Attached Figure Description

[0020] Figure 1A schematic diagram of the structure of a wind tunnel model for measuring the pulsating pressure of a tail rudder with variable rudder deflection angle, an exemplary embodiment of the present invention, is shown.

[0021] Figure 2 An internal schematic diagram of a wind tunnel model for measuring the pulsating pressure of a tail rudder with variable rudder deflection angle, an exemplary embodiment of the present invention, is shown.

[0022] Figure 3 This is a rearward schematic diagram of a wind tunnel model for measuring the pulsating pressure of a variable rudder deflection tail rudder, which is an exemplary embodiment of the present invention, without support rods.

[0023] Figure 4 A schematic diagram of an aircraft model of an exemplary embodiment of the present invention is shown.

[0024] Figure 5 and Figure 6 A schematic diagram of the tail rudder and angle plate in cooperation with an exemplary embodiment of the present invention is shown.

[0025] Figure 7 A schematic diagram of a tail rudder model of an exemplary embodiment of the present invention is shown.

[0026] Figure 8 The figure shows a three-view angle sheet of an exemplary embodiment of the present invention.

[0027] Explanation of reference numerals in the attached figures:

[0028] 1. Aircraft model; 2. Tail rudder model; 3. Pressure sensor; 4. Angle plate; 5. Support rod; 6. Rudder shaft; 7. Mounting hole; 8. Slot; 9. Rear through hole; 10. Cavity; 11. Opening; 12. Circular through hole; 13. Opening; 14. Forward through hole. Detailed Implementation

[0029] To make the objectives, technical solutions, and advantages of this application clearer, the embodiments disclosed in this application will be described in further detail below with reference to the accompanying drawings.

[0030] This application discloses a wind tunnel model for measuring the pulsating pressure of a variable rudder deflection tail rudder, such as... Figure 1 , Figure 4 and Figure 5 As shown, the system includes an aircraft model 1, at least one tail rudder model 2, at least one pressure sensor 3, at least one angle plate 4, and a support rod 5. The support rod 5 is connected to the tail of the aircraft model 1. The aircraft model 1 has multiple mounting holes 7 arranged circumferentially, each mounting hole 7 for mounting the tail rudder model 2. The pressure sensor 3 is mounted on the tail rudder model 2. The angle plate 4 connects the aircraft model 1 and the tail rudder model 2. Installing angle plates 4 at different angles can be used to adjust the rudder deflection angle.

[0031] like Figure 3 , Figure 5 and Figure 7 As shown, the tail rudder model 2 is mounted on the aircraft model 1 at the mounting hole 7 via a bottom cylindrical rudder shaft 6. The rudder shaft 6 has a slot 8 in the middle facing rearward, corresponding to a rearward through hole 9 at the bottom of the aircraft model 1. The angle plate 4 is inserted into the slot 8 through the rearward through hole 9 to fix the angle of the tail rudder model 2. The rudder deflection angle is adjusted by replacing different angle plates 4. In actual operation, the angle plate 4 has a threaded hole at the rear, which can be used to insert and remove it using a pin puller. The angle plate 4 can be securely installed using a clamping screw.

[0032] like Figure 2 and Figure 7 As shown, the tail rudder model 2 has a cavity 10 inside. For easy installation, the tail rudder model has a cover 11 on its surface. The cover 11 does not change the original shape of the tail rudder. According to the test measurement requirements, there are circular through holes 12 on the tail rudder 2 and the cover 11. The head of each pressure sensor 3 is exposed in the circular through hole 12. There is an opening 13 in front of the rudder shaft 6, which is connected to the cavity 10. The part of the aircraft model 1 corresponding to the opening 13 has a forward through hole 14. The signal line of the pressure sensor 3 is led out from the opening 13 in the cavity 10 through the forward through hole 14, and enters the support rod 5 to connect to the test acquisition equipment for test measurement.

[0033] The pressure sensor 3 is a thin-film pulsating pressure sensor. The depth of the cavity 10 is not less than the thickness of the pressure sensor 3, and the width of the cavity 10 is not less than the diameter of the pressure sensor.

[0034] The pressure-sensitive head of the pressure sensor 3 shall not extend beyond the outer edge of the circular through-hole 12, and shall be within 0.5mm below the outer edge of the circular through-hole 12. The difference between the diameter of the circular through-hole 12 of the tail rudder model 2 and the cover 11 and the diameter of the head of the pressure sensor 3 shall not exceed 0.1mm.

[0035] like Figure 6 and Figure 8 As shown, the angle plate 4 is a quadrilateral sheet with a certain thickness, wherein two sides of the quadrilateral are parallel to each other, the third side is perpendicular to the two parallel sides, and the fourth side is the side into which the rudder shaft slot 8 is inserted. The rudder deflection angle is adjusted by the different included angles between the fourth side and the two parallel sides. The distance between the two parallel sides is equal to the width of the rear through hole 9, and the thickness of the angle plate 4 is equal to the height of the rear through hole 9. The fit tolerances are performed in accordance with relevant machining standards.

[0036] The test model provided by this utility model can realize the installation of pressure sensors on the tail rudder in wind tunnel tests for tail rudder flutter and load measurement, and can realize rapid adjustment of rudder deflection angle during the test to obtain pulsating pressure under various rudder deflection angles, avoiding disassembly of the model and connection of signal lines, thus improving test efficiency.

[0037] The contents not described in detail in this application specification are common knowledge to those skilled in the art.

[0038] The present application has been described in detail above with reference to specific embodiments and exemplary examples; however, these descriptions should not be construed as limiting the present application. Those skilled in the art will understand that various equivalent substitutions, modifications, or improvements can be made to the technical solutions and implementation methods of the present application without departing from the spirit and scope of the present application, and all such modifications and improvements fall within the scope of the present application. The scope of protection of the present application is determined by the appended claims.

Claims

1. A wind tunnel model for measuring the pulsating pressure of a variable rudder deflection tail rudder, characterized in that, include: The aircraft model (1) has at least one mounting hole (7) on its outer wall for mounting a tail rudder model (2), and a rear through hole (9). One end of the rear through hole (9) is connected to the mounting hole (7), and the other end extends through to the end face of the aircraft model (1). The tail rudder model (2) is connected to the rudder shaft (6) on one side. The rudder shaft (6) is inserted into the mounting hole (7). The rudder shaft (6) has a slot (8) on the side facing the rear through hole (9). Pressure sensor (3) is connected to tail rudder model (2); Angle plate (4) is inserted into slot (8) through rear through hole (9) to fix the angle of tail rudder model (2); the rudder deflection angle can be adjusted by replacing different angle plates (4); Support rod (5) is connected to the end of aircraft model (1).

2. The wind tunnel model for measuring the pulsating pressure of a variable rudder deflection tail rudder according to claim 1, characterized in that: Multiple mounting holes (7) are provided, and the multiple mounting holes (7) are evenly distributed in the same circumferential position on the aircraft model (1).

3. The wind tunnel model for measuring the pulsating pressure of a variable rudder deflection tail rudder according to claim 1, characterized in that: The tail rudder model (2) has a cavity (10) inside and a cover (11) on its surface. The cover (11) covers the cavity (10) and does not change the original shape of the tail rudder model (2). The tail rudder model (2) and the cover (11) are provided with a circular through hole (12) and the head of the pressure sensor (3) is exposed through the circular through hole (12).

4. The wind tunnel model for measuring the pulsating pressure of a variable rudder deflection tail rudder according to claim 3, characterized in that: The rudder shaft (6) has an opening (13) on the side away from the slot (8), and the opening (13) is connected to the cavity (10). The aircraft model (1) has a forward through hole (14), which is opposite to the opening (13) so that the signal line of the pressure sensor (3) can be led out from the opening (13) through the forward through hole (14) in the cavity (10), and enter the support rod (5) to connect to the test acquisition equipment for test measurement.

5. A wind tunnel model for measuring the pulsating pressure of a variable rudder deflection tail rudder according to claim 3, characterized in that: The pressure sensor (3) is a thin-film pulsating pressure sensor. The depth of the cavity (10) is not less than the thickness of the pressure sensor (3), and the width of the cavity (10) is not less than the diameter of the pressure sensor.

6. The wind tunnel model for measuring the pulsating pressure of a variable rudder deflection tail rudder according to claim 1, characterized in that: The pressure-sensitive head of the pressure sensor (3) does not extend beyond the outer edge of the circular through hole (12) and is within 0.5 mm below the outer edge of the circular through hole (12).

7. A wind tunnel model for measuring the pulsating pressure of a variable rudder deflection tail rudder according to claim 3, characterized in that: The difference between the diameter of the circular through hole (12) and the diameter of the head of the pressure sensor (3) is no greater than 0.1 mm.

8. The wind tunnel model for measuring the pulsating pressure of a variable rudder deflection tail rudder according to claim 1, characterized in that: The angle plate (4) is a quadrilateral thin plate with a set thickness. The two sides of the angle plate (4) are parallel to each other, the third side is perpendicular to the two parallel sides, and the fourth side is the side that is close to the bottom of the slot (8). The rudder deflection angle is adjusted by the different included angles between the fourth side and the two parallel sides. The distance between the two parallel sides is the same as the width of the rear through hole (9), and the thickness of the angle plate (4) is the same as the height of the rear through hole (9).

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