A high-speed wind tunnel slice water-cooled hinge torque balance measuring system

Abstract

The application provides a high-hypersonic wind tunnel piece water-cooled hinge torque balance measurement system and belongs to the technical field of wind tunnel test measurement.The application aims to solve the problem that the rudder surface is difficult to be externally cooled due to thin structure and the hinge torque is difficult to be measured in the prior art.The aircraft fuselage is connected with the aircraft wing and the piece water-cooled hinge torque balance in the application.The top and bottom of the piece water-cooled hinge torque balance are respectively provided with a balance upper cover plate and a balance lower cover plate.The upper end surface of the balance lower cover plate is flush with the aircraft fuselage.The balance free end, the balance measurement element and the fuselage mounting base of the piece water-cooled hinge torque balance are sequentially connected.The balance free end is connected with the measured rudder surface through an angle ear.The balance measurement element is pasted with a strain gauge, and the balance measurement element is internally provided with a water-cooled groove circuit.The application solves the problem that the measurement precision is greatly reduced due to high temperature in the high-hypersonic wind tunnel test, and the rudder surface is difficult to be externally cooled due to thin structure and the hinge torque is difficult to be measured.

Description

Technical Field

[0001] This invention belongs to the field of wind tunnel testing and measurement technology, and in particular relates to a hypersonic wind tunnel plate-type water-cooled hinge torque balance measurement system. Background Technology

[0002] Wind tunnel force measurement is the most fundamental test item in aircraft development. In order to obtain the maneuverability of an aircraft, it is often necessary to measure the hinge torque of control surfaces such as elevators and rudders. The hinge torque balance is a direct measuring device for this aerodynamic load, and the aerodynamic performance of the aircraft can be optimized based on the measurement results.

[0003] In hypersonic wind tunnel tests, the incoming flow temperature can reach 600K-900K or even higher, depending on the test content and requirements. Due to the high incoming flow temperature, the test model and control surfaces are exposed to the high-temperature airflow, and the balance temperature rises due to the heat transfer from the airflow. The balance measurement results are affected by the thermal deformation of the materials and the change in the high-temperature resistance value of the strain gauge, resulting in a significant decrease in the accuracy of the test data. In the aileron and elevator areas, due to the thinness of the wing surface, it is difficult to install external cooling structures without interfering with the strain output of the balance.

[0004] In summary, there is an urgent need to design a hypersonic wind tunnel plate-type water-cooled hinge torque balance measurement system to solve the problems in existing hypersonic wind tunnel tests where high temperatures cause thermal deformation of the balance and changes in strain gauge resistance, resulting in a significant decrease in measurement accuracy. Furthermore, the thin structure of the wing control surfaces makes external cooling difficult, which also makes hinge torque measurement challenging. Summary of the Invention

[0005] A brief overview of the invention is given below to provide a basic understanding of certain aspects of it. It should be understood that this overview is not an exhaustive summary of the invention. It is not intended to identify key or essential parts of the invention, nor is it intended to limit the scope of the invention. Its purpose is merely to present certain concepts in a simplified form as a prelude to the more detailed description that follows.

[0006] In view of this, in order to solve the problems that high temperature in existing hypersonic wind tunnel tests can cause thermal deformation of the balance and changes in strain gauge resistance, resulting in a significant decrease in measurement accuracy, and that the thin structure of the wing control surface makes external cooling difficult, making hinge torque measurement challenging, this invention provides a hypersonic wind tunnel plate-type water-cooled hinge torque balance measurement system.

[0007] Solution: A hypersonic wind tunnel plate-type water-cooled hinge torque balance measurement system, including an aircraft fuselage, an aircraft wing, a plate-type water-cooled hinge torque balance, angle lugs, a control surface to be measured, an upper cover plate of the balance, a lower cover plate of the balance, and a semiconductor cooling water tank;

[0008] The aircraft fuselage is provided with wing mounting slots, balance mounting slots and water pipe outlets. The aircraft wings are mounted in the wing mounting slots. The balance mounting slots are stepped grooves with a plate-type water-cooled hinge torque balance installed at the bottom and a balance lower cover plate installed at the top. The water pipe outlets are located on the end face of the aircraft fuselage.

[0009] The plate-type water-cooled hinge torque balance is equipped with an upper cover plate and a lower cover plate at the top and bottom, respectively, with the upper end of the lower cover plate flush with the aircraft fuselage.

[0010] The plate-type water-cooled hinge torque balance includes a free end, a measuring element, a fuselage mounting base, a pagoda connector, and a water-cooling tank circuit. The free end, the measuring element, and the fuselage mounting base are connected sequentially. The fuselage mounting base is installed in the mounting slot of the balance. The side of the fuselage mounting base is threaded to the pagoda connector, which connects two water pipes to a semiconductor cooling water tank. The free end of the balance has a mounting slot that mates with an angle lug. The free end of the balance is connected to the measured rudder surface through the angle lug. Strain gauges are attached to the surface of the measuring element, and the inside of the measuring element has a water-cooling tank circuit. The strain gauges of the bridge are on the same water-cooling tank circuit.

[0011] Furthermore, the semiconductor cooling water tank is equipped with a high-lift water pump and cooling water. The side wall of the semiconductor cooling water tank is provided with an outlet pipe hole and an inlet pipe hole, and the high-lift water pump is equipped with a water pump interface.

[0012] Furthermore, the bottom of the semiconductor cooling water tank is a semiconductor cooling chip.

[0013] Furthermore, the connecting surface of the angle lug and the measured rudder surface is coated with a zirconium oxide coating with a thickness of more than 0.3 mm.

[0014] Furthermore, the balance measuring element is a beam-column structure combination with a rectangular cross-section.

[0015] Furthermore, the upper and lower covers of the balance are made of non-metallic materials with low thermal conductivity.

[0016] Furthermore, the plate-type water-cooled hinge torque balance is integrally formed using 3D printing technology and surface finishing.

[0017] Furthermore, sensors are provided inside the semiconductor cooling water tank and on the balance measuring element.

[0018] Furthermore, the temperature of the plate-type water-cooled hinge torque balance is maintained within a range of 3°C by adjusting the power of the high-lift water pump and the semiconductor cooling chip.

[0019] The present invention has the following advantages over the prior art:

[0020] 1. The present invention adopts an internal circulating water cooling structure, which is suitable for the installation space of thin wing structure. It does not damage the shape of the aircraft, nor does it interfere with the strain output, so as to restore the real aerodynamic environment to the greatest extent and effectively improve the authenticity and reliability of wind tunnel test data.

[0021] 2. This invention optimizes the structural dimensions of the balance measuring element and the water-cooling tank circuit through material mechanics calculations, and adopts a uniform wall thickness design to ensure uniform heat conduction around the balance measuring element, guarantee consistent cooling effect of each strain gauge, avoid the introduction of additional strain due to uneven temperature field, and improve measurement accuracy and adaptability to high-temperature environments.

[0022] 3. This invention uses 3D printing integrated molding and precision machining technology to integrate the cooling channel into the inside of the balance measuring element. The internal water cooling directly reduces the balance temperature, significantly reducing the thermal stress and thermal deformation caused by high temperature. It can achieve high-precision and stable measurement of the hinge torque of aileron and elevator in hypersonic wind tunnel.

[0023] 4. In this invention, a semiconductor cooling water tank is used to prepare low-temperature cooling water, which further enhances the overall cooling effect, continuously reduces the temperature of the balance body, and can adapt to hypersonic wind tunnel tests with higher heat flux density, expanding the working conditions and application scenarios of hinge torque measurement. Attached Figure Description

[0024] The accompanying drawings, which are included to provide a further understanding of the invention and form part of this invention, illustrate exemplary embodiments of the invention and are used to explain the invention, but do not constitute an undue limitation of the invention. In the drawings:

[0025] Figure 1 This is a schematic diagram of a high-performance wind tunnel plate-type water-cooled hinged torque balance measurement system.

[0026] Figure 2 This is an axonometric drawing of the lower cover plate of the balance.

[0027] Figure 3 This is a structural diagram of the aircraft fuselage;

[0028] Figure 4 This diagram shows the positional relationship between the plate-type water-cooled hinge torque balance and the measured rudder surface.

[0029] Figure 5 This is a cross-sectional view of a plate-type water-cooled hinge torque balance.

[0030] Figure 6 This is a schematic diagram of the angled ear piece structure;

[0031] Figure 7 This is a schematic diagram of the structure of a semiconductor cooling water tank;

[0032] Figure 8 Paste the front view of the strain gauge location;

[0033] Figure 9 Rear view showing the location where the strain gauges are pasted;

[0034] Figure 10 Strain gauge bridge layout diagram.

[0035] In the diagram: 1-Aircraft fuselage, 11-Wing mounting slot, 12-Balance mounting slot, 14-Water pipe outlet, 2-Aircraft wing, 3-Plate-type water-cooled hinge torque balance, 31-Balance free end, 32-Balance measuring element, 33-Fuselage mounting base, 34-Pagoda connector, 35-Water-cooled tank circuit, 4-Angle lug, 5-Measured control surface, 6-Balance upper cover plate, 7-Balance lower cover plate, 8-Semiconductor cooling water tank, 81-High-lift water pump, 82-Semiconductor cooling chip, 83-Water outlet pipe hole, 84-Water inlet pipe hole, 85-Water pump interface. Detailed Implementation

[0036] To make the technical solutions and advantages of the embodiments of the present invention clearer, the exemplary embodiments of the present invention will be further described in detail below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not an exhaustive list of all embodiments. It should be noted that, unless otherwise specified, the embodiments and features in the embodiments of the present invention can be combined with each other.

[0037] Examples, References Figures 1-7 This embodiment describes a hypersonic wind tunnel plate-type water-cooled hinge torque balance measurement system, which includes an aircraft fuselage 1, an aircraft wing 2, a plate-type water-cooled hinge torque balance 3, an angle lug 4, a control surface to be measured 5, an upper cover plate 6, a lower cover plate 7, and a semiconductor cooling water tank 8.

[0038] The aircraft fuselage 1 is provided with a wing mounting slot 11, a balance mounting slot 12 and a water pipe outlet 14. The aircraft wing 2 is installed in the wing mounting slot 11. The balance mounting slot 12 is a stepped groove. A plate-type water-cooled hinge torque balance 3 is installed at the bottom and a balance lower cover plate 7 is installed at the top. The water pipe outlet 14 is located on the end face of the aircraft fuselage 1.

[0039] The plate-type water-cooled hinge torque balance 3 is equipped with an upper balance cover plate 6 and a lower balance cover plate 7 at its top and bottom, respectively. The upper surface of the lower balance cover plate 7 is flush with the aircraft fuselage 1.

[0040] The plate-type water-cooled hinge torque balance 3 includes a free end 31, a measuring element 32, a mounting base 33, a pagoda connector 34, and a water-cooling circuit 35. The free end 31, the measuring element 32, and the mounting base 33 are connected sequentially. The mounting base 33 is installed in the mounting slot 12. The side of the mounting base 33 is threaded to the pagoda connector 34, which connects two water pipes to the semiconductor cooling water tank 8. The free end 31 has a mounting slot that mates with the angle lug 4. The free end 31 is connected to the measured rudder surface 5 through the angle lug 4. Strain gauges are attached to the surface of the measuring element 32. The measuring element 32 has a water-cooling circuit 35 inside. The strain gauges of the bridge are on the same water-cooling circuit 35 to reduce the temperature influence inside the bridge circuit. At the same time, the appropriate size of the measuring element 32 can be matched according to the load characteristics. Water is required during calibration and testing to achieve the ideal measurement effect.

[0041] Furthermore, the ninth strain gauge R9 and the eleventh strain gauge R11 are attached to the upper surface of the outer circuit of the balance measuring element 32, and the tenth strain gauge R10 and the twelfth strain gauge R12 are attached to the lower surface of the outer circuit; the fifth strain gauge R5 and the seventh strain gauge R7 are attached to the upper surface of the inner circuit of the balance measuring element 32 near the mounting base 33 of the body, and the sixth strain gauge R6 and the eighth strain gauge R8 are attached to the lower surface; the first strain gauge R1 and the third strain gauge R3 are attached to the upper surface of the inner circuit of the balance measuring element 32 near the free end 31 of the balance, and the second strain gauge R2 and the fourth strain gauge R4 are attached to the lower surface.

[0042] The first strain gauge R1, the second strain gauge R2, the third strain gauge R3 and the fourth strain gauge R4 form a U1 bridge, the fifth strain gauge R5, the sixth strain gauge R6, the seventh strain gauge R7 and the eighth strain gauge R8 form a U2 bridge, and the ninth strain gauge R9, the tenth strain gauge R10, the eleventh strain gauge R11 and the twelfth strain gauge R12 form a U3 bridge.

[0043] Furthermore, the semiconductor cooling water tank 8 is equipped with a high-lift water pump 81 and cooling water. The side wall of the semiconductor cooling water tank 8 is provided with a water outlet 83 and a water inlet 84. The high-lift water pump 81 is equipped with a water pump interface 85.

[0044] Furthermore, the bottom of the semiconductor cooling water tank 8 is a semiconductor cooling chip 82, which can further cool the water temperature.

[0045] Furthermore, the connecting surface of the angle lug 4 and the test rudder surface 5 is coated with a zirconium oxide coating with a thickness of more than 0.3 mm to reduce the heat transfer of the test rudder surface 5.

[0046] Furthermore, the balance measuring element 32 is a beam-column structure combination with a rectangular cross-section. The cross-section is matched to the dimensions through material mechanics calculations. It adopts a design with equal wall thickness so that the thermal conductivity is the same on all four sides, resulting in a consistent cooling effect on the surface strain gauge.

[0047] Furthermore, the upper cover plate 6 and the lower cover plate 7 of the balance are made of non-metallic materials with low thermal conductivity such as PEEK, which can work for a long time in an environment above 260°C and maintain mechanical properties, thereby reducing heat transfer.

[0048] Furthermore, the plate-type water-cooled hinge torque balance 3 is integrally formed using 3D printing technology and surface finishing.

[0049] Furthermore, sensors are installed inside the semiconductor cooling water tank 8 and on the balance measuring element 32 to monitor their temperatures in real time.

[0050] Furthermore, the temperature of the plate-type water-cooled hinge torque balance 3 is maintained within a range of 3°C by adjusting the power of the high-lift water pump 81 and the semiconductor cooling chip 82.

[0051] Furthermore, Teflon tape is wrapped between the pagoda connector 34 and the mounting base 33 to prevent water leakage.

[0052] Furthermore, the semiconductor cooling water tank 8 is installed inside the wind tunnel support curved structure.

[0053] The working principle of water cooling in this invention is as follows:

[0054] When the high-lift water pump 81 is turned on, the cooling water in the semiconductor cooling water tank 8 enters the water pipe through the water pump interface 85, and then enters the plate-type water-cooled hinge torque balance 3 through the water inlet pipe hole 84, the water pipe outlet 14 and the pagoda connector 34 in sequence. It flows through the internal water-cooling tank circuit 35 to cool the balance measuring element 32, and then flows through the outlet pipe hole 83 from another pagoda connector 34 back into the semiconductor cooling water tank 8, thus completing the entire cooling circuit.

[0055] This invention employs an internal circulating water-cooling structure, adapted to the installation space of thin-wing structures. It neither damages the aircraft's shape nor interferes with strain output, maximizing the reproduction of the real aerodynamic environment and effectively improving the authenticity and reliability of wind tunnel test data. At the same time, it optimizes the structural dimensions of the measuring elements of the balance and the water-cooling tank circuit through material mechanics calculations, and adopts a uniform wall thickness design to ensure uniform circumferential heat conduction of the balance measuring elements, ensuring consistent cooling effect for each strain gauge, avoiding the introduction of additional strain due to uneven temperature field, and improving measurement accuracy and adaptability to high-temperature environments.

[0056] This invention employs 3D printing and precision machining processes to integrate cooling channels into the internal components of the balance. Internal water cooling directly reduces the balance temperature, significantly minimizing thermal stress and deformation caused by high temperatures. This enables high-precision and stable measurement of aileron and elevator hinge moments in hypersonic wind tunnels. Simultaneously, a semiconductor-cooled water tank is used to prepare low-temperature cooling water, further enhancing the overall cooling effect and continuously reducing the balance body temperature. This allows the balance to adapt to hypersonic wind tunnel tests with higher heat flux densities, expanding the operating conditions and application scenarios for hinge moment measurement.

[0057] Although the invention has been described with reference to a limited number of embodiments, those skilled in the art will understand from the foregoing description that other embodiments are conceivable within the scope of the invention described herein. Furthermore, it should be noted that the language used in this specification has been chosen primarily for readability and instructional purposes, and not for the purpose of interpreting or limiting the subject matter of the invention. Therefore, many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the appended claims. The disclosure of the invention is illustrative and not restrictive, and the scope of the invention is defined by the appended claims.

Claims

1. A high-performance wind tunnel plate-type water-cooled hinge torque balance measurement system, characterized in that, Includes aircraft fuselage (1), aircraft wings (2), plate water-cooled hinge torque balance (3), angle lugs (4), control surface to be measured (5), balance upper cover plate (6), balance lower cover plate (7) and semiconductor cooling water tank (8); The aircraft fuselage (1) is provided with a wing mounting slot (11), a balance mounting slot (12) and a water pipe outlet (14). The aircraft wing (2) is installed in the wing mounting slot (11). The balance mounting slot (12) is a stepped groove. A plate-type water-cooled hinge torque balance (3) is installed at the bottom and a balance lower cover plate (7) is installed at the top. The water pipe outlet (14) is located on the end face of the aircraft fuselage (1). The top and bottom of the plate-type water-cooled hinge torque balance (3) are respectively equipped with an upper cover plate (6) and a lower cover plate (7), and the upper end face of the lower cover plate (7) is flush with the fuselage (1) of the aircraft. The plate-type water-cooled hinge torque balance (3) includes a balance free end (31), a balance measuring element (32), a fuselage mounting base (33), a pagoda connector (34), and a water-cooling tank circuit (35). The balance free end (31), the balance measuring element (32), and the fuselage mounting base (33) are connected in sequence. The fuselage mounting base (33) is installed in the balance mounting slot (12). The side of the fuselage mounting base (33) is threaded to the pagoda connector (34). The pagoda connector (34) connects two water pipes to the semiconductor cooling water tank (8). The balance free end (31) is provided with a mounting slot that mates with the angle lug (4). The balance free end (31) is connected to the measured rudder surface (5) through the angle lug (4). The surface of the balance measuring element (32) is covered with a strain gauge. The interior of the balance measuring element (32) is provided with a water-cooling tank circuit (35). The strain gauges of the bridge are set on the same water-cooling tank circuit (35).

2. The hypersonic wind tunnel plate-type water-cooled hinge torque balance measurement system according to claim 1, characterized in that, The semiconductor cooling water tank (8) is equipped with a high-lift water pump (81) and cooling water. The side wall of the semiconductor cooling water tank (8) is provided with an outlet pipe hole (83) and an inlet pipe hole (84). The high-lift water pump (81) is equipped with a water pump interface (85).

3. The hypersonic wind tunnel plate-type water-cooled hinge torque balance measurement system according to claim 2, characterized in that, The bottom of the semiconductor cooling water tank (8) is a semiconductor cooling chip (82).

4. The hypersonic wind tunnel plate-type water-cooled hinge torque balance measurement system according to claim 1, characterized in that, The angle lug (4) and the connecting side surface of the rudder surface (5) are coated with a zirconium oxide coating with a thickness of more than 0.3 mm.

5. The hypersonic wind tunnel plate-type water-cooled hinge torque balance measurement system according to claim 1, characterized in that, The balance measuring element (32) is a beam-column structure with a rectangular cross-section.

6. The hypersonic wind tunnel plate-type water-cooled hinge torque balance measurement system according to claim 1, characterized in that, The upper cover plate (6) and lower cover plate (7) of the balance are made of non-metallic materials with low thermal conductivity.

7. The hypersonic wind tunnel plate-type water-cooled hinge torque balance measurement system according to claim 1, characterized in that, The plate-type water-cooled hinge torque balance (3) is integrally formed using 3D printing technology and surface finishing.

8. The hypersonic wind tunnel plate-type water-cooled hinge torque balance measurement system according to claim 2, characterized in that, Sensors are provided inside the semiconductor cooling water tank (8) and on the balance measuring element (32).

9. The hypersonic wind tunnel plate-type water-cooled hinge torque balance measurement system according to claim 8, characterized in that, The temperature of the plate-type water-cooled hinge torque balance (3) is maintained within a range of 3°C by adjusting the power of the high-lift water pump (81) and the semiconductor cooling chip (82).

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