A wind tunnel test support device

Abstract

This utility model relates to the field of wind tunnel testing technology and discloses a wind tunnel testing support device, including a test chamber. A circular tube is fixedly connected to the lower surface of the test chamber, and the circular tube is connected to the interior of the test chamber. A rotating platform is installed on the circular tube, and a lifting mechanism is fixedly connected to the upper surface of the rotating platform. Adjustment mechanism one and adjustment mechanism two are installed on both sides of the lifting mechanism. The upper ends of the lifting mechanism, adjustment mechanism one, and adjustment mechanism two are connected to a support plate. This utility model can not only accurately control the vertical rise and fall height of the model, but also adjust spatial angle parameters such as pitch angle and yaw angle. It can simulate various relative positional relationships between the model and the airflow in real flight / driving scenarios, meet the testing needs under complex aerodynamic conditions such as different incoming flow angles of attack and sideslip angles, and effectively expand the coverage of wind tunnel testing. Compared with traditional fixed support structures, its dynamic adjustment characteristics significantly improve the information acquisition efficiency of a single test.

Description

Technical Field

[0001] This utility model relates to the field of wind tunnel testing technology, specifically a wind tunnel testing support device. Background Technology

[0002] Wind tunnel testing, as an important aerodynamic research method, plays an irreplaceable role in fields such as aerospace, automotive engineering, and architectural wind engineering. By simulating different airflow conditions in wind tunnels and testing various models, key aerodynamic parameters can be obtained, providing important basis for product design, optimization, and performance evaluation.

[0003] In wind tunnel testing, fixing aircraft and car models directly without adjusting their angles leads to several drawbacks: it fails to fully simulate the diverse flight attitudes of aircraft and the complex driving conditions of cars, making it difficult to accurately assess aircraft handling performance and optimize car aerodynamic design; test data is incomplete and its accuracy is affected, as only single-angle data can be obtained, failing to form a complete aerodynamic characteristic curve, and is prone to deviations due to ignoring angle changes; it fails to meet the diverse needs of interdisciplinary research and new technology development for flexible attitude adjustment, limiting technological innovation in related fields; at the same time, it prolongs the test cycle, and multiple tests increase the consumption of human and material resources, reduce wind tunnel utilization efficiency, and thus increase test costs. Utility Model Content

[0004] To address the shortcomings of existing technologies, this utility model provides a wind tunnel test support device that can change the tilt angle of the object being tested.

[0005] To achieve the above objectives, this utility model provides the following technical solution: a wind tunnel test support device, including a test chamber, a circular tube fixedly connected to the lower surface of the test chamber, the circular tube communicating with the interior of the test chamber, a rotating platform installed on the circular tube, a lifting mechanism fixedly connected to the upper surface of the rotating platform, an adjustment mechanism one and an adjustment mechanism two installed on both sides of the lifting mechanism, and a support plate connected to the upper ends of the lifting mechanism, the adjustment mechanism one and the adjustment mechanism two.

[0006] Furthermore, the lifting mechanism includes two electric telescopic rods fixedly connected to the rotating platform. The upper ends of the two electric telescopic rods are connected to a rotating shaft. Both ends of the rotating shaft are rotatably connected to rotating blocks. The two rotating blocks are fixedly connected to the lower surface of the support plate.

[0007] Furthermore, the adjustment mechanism includes two rotating blocks two fixedly connected to the rotating platform, a rotating shaft two rotatably connected between the two rotating blocks two, a multi-stage electric telescopic rod two fixedly connected to the rotating shaft two, a rotating shaft three fixedly connected to the upper end of the multi-stage electric telescopic rod two, rotating blocks three rotatably connected to both ends of the rotating shaft three, and the upper ends of the two rotating blocks three fixedly connected to the lower surface of the support plate.

[0008] Furthermore, the structure of the second adjustment mechanism is the same as that of the first adjustment mechanism.

[0009] Furthermore, the support plate is equipped with anti-slip pads or double-sided adhesive.

[0010] Furthermore, an internally threaded pipe is fixedly connected to the lower end of the circular tube, and an externally threaded pipe matching the internally threaded pipe is fixedly connected to the outer wall of the rotating platform.

[0011] Furthermore, a multi-stage electric telescopic rod three is fixedly connected to the support plate, the multi-stage electric telescopic rod three penetrates the upper surface of the support plate, and double-sided adhesive is pasted on the front end of the multi-stage electric telescopic rod three.

[0012] Compared with the prior art, the present invention has the following beneficial effects:

[0013] This type of wind tunnel test support device can not only precisely control the vertical rise and fall of the model, but also adjust spatial angular parameters such as pitch and yaw angles. Through this flexible attitude adjustment, the device can simulate various relative positional relationships between the model and the airflow in real flight / driving scenarios, meeting the testing requirements under complex aerodynamic conditions such as different incoming flow angles of attack and sideslip angles, effectively expanding the coverage of wind tunnel testing. Compared to traditional fixed support structures, its dynamic adjustment characteristics significantly improve the efficiency of information acquisition in a single test, providing more comprehensive test data support for engineering fields such as aircraft aerodynamic shape optimization and automotive aerodynamic drag reduction design. Attached Figure Description

[0014] Figure 1 This is a three-dimensional structural diagram of the entire utility model;

[0015] Figure 2 This is an exploded view of the entire utility model;

[0016] Figure 3 This is a three-dimensional structural diagram of the lifting mechanism, adjustment mechanism one, and adjustment mechanism two of this utility model.

[0017] In the diagram: 1. Test chamber; 2. Circular tube; 3. Rotating platform; 4. Support plate; 5. Electric telescopic rod one; 6. Rotating shaft one; 7. Rotating block one; 8. Rotating block two; 9. Rotating shaft two; 10. Multi-stage electric telescopic rod two; 11. Rotating shaft three; 12. Rotating block three; 13. Internally threaded tube; 14. Externally threaded tube; 15. Multi-stage electric telescopic rod three. Detailed Implementation

[0018] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present utility model. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments.

[0019] Please see Figures 1 to 3 A wind tunnel test support device includes a test chamber 1. A circular tube 2 is fixedly connected to the lower surface of the test chamber 1. The circular tube 2 is connected to the interior of the test chamber 1. A rotating platform 3 is installed on the circular tube 2. A lifting mechanism is fixedly connected to the upper surface of the rotating platform 3. An adjustment mechanism one and an adjustment mechanism two are installed on both sides of the lifting mechanism. The upper ends of the lifting mechanism, the adjustment mechanism one and the adjustment mechanism two are connected to a support plate 4.

[0020] like Figures 1 to 3 As shown, the wind tunnel test support device of this utility model allows for the placement of an aircraft model or a car model on the support plate 4 during use. The vertical height, pitch angle, yaw angle, and other spatial angle parameters of the aircraft model or car model can be adjusted through the rotating platform 3, the lifting mechanism, the first adjustment mechanism, and the second adjustment mechanism. This satisfies the test requirements under complex aerodynamic conditions such as different incoming flow angles of attack and sideslip angles, effectively expanding the coverage of wind tunnel tests and providing more comprehensive test data support. The rotating platform 3 is existing technology and will not be described in detail here.

[0021] like Figure 3 As shown, the lifting mechanism includes two electric telescopic rods 5 fixedly connected to the rotating platform 3. The upper ends of the two electric telescopic rods 5 are connected to a rotating shaft 6. Both ends of the rotating shaft 6 are rotatably connected to rotating blocks 7. The two rotating blocks 7 are fixedly connected to the lower surface of the support plate 4.

[0022] Specifically, the two electric telescopic rods 1 and 5 extend simultaneously, and at the same time, the adjustment mechanisms 1 and 2 also lengthen, thereby lifting the airplane model or car model vertically.

[0023] like Figure 3 As shown, the adjustment mechanism includes two rotating blocks 8 fixedly connected to the rotating platform 3. A rotating shaft 9 is rotatably connected between the two rotating blocks 8. A multi-stage electric telescopic rod 10 is fixedly connected to the rotating shaft 9. A rotating shaft 11 is fixedly connected to the upper end of the multi-stage electric telescopic rod 10. Rotating blocks 12 are rotatably connected to both ends of the rotating shaft 11. The upper ends of the two rotating blocks 12 are fixedly connected to the lower surface of the support plate 4.

[0024] Specifically, when it is necessary to change the spatial angle parameters such as pitch angle and yaw angle of the aircraft model or car model, the multi-stage electric telescopic rod 10 is activated. During the lengthening process of the multi-stage electric telescopic rod 10, its tilt angle is adjusted through the rotating shaft 9 and the rotating shaft 11, thereby changing the tilt angle of the support plate 4. During this process, the rotating block 7 rotates with the rotating shaft 6 at the upper end of the electric telescopic rod 5. After the rotating platform 3 is activated, the orientation of the tilting support plate 4 can be adjusted again after rotation, thereby adjusting the spatial angle parameters such as pitch angle and yaw angle of the aircraft model or car model to increase the coverage area of ​​the test.

[0025] like Figure 3 As shown, the structure of the second adjustment mechanism is the same as that of the first adjustment mechanism.

[0026] Specifically, during the elongation of adjustment mechanism one, adjustment mechanism two contracts.

[0027] like Figure 3 As shown, the support plate 4 is equipped with an anti-slip pad or double-sided adhesive.

[0028] Specifically, the anti-slip mat is more convenient for adjusting only the vertical distance of the airplane model, and the double-sided tape is sticky and can prevent the model from moving.

[0029] like Figure 2 As shown, the lower end of the circular tube 2 is fixedly connected to an internally threaded tube 13, and the outer wall of the rotating platform 3 is fixedly connected to an externally threaded tube 14 that matches the internally threaded tube 13.

[0030] Specifically, the internally threaded pipe 13 and the externally threaded pipe 14 are connected by threads, which facilitates the installation and disassembly of this support device.

[0031] like Figure 3 As shown, a multi-stage electric telescopic rod 15 is fixedly connected to the support plate 4. The multi-stage electric telescopic rod 15 penetrates the upper surface of the support plate 4, and double-sided tape is attached to the front end of the multi-stage electric telescopic rod 15.

[0032] Specifically, airplane models usually have a chassis and support rods, while car models do not. By attaching the car model to the double-sided tape at the front end of the multi-stage electric telescopic rod 315, it is convenient to conduct wind tunnel tests on the car model from multiple angles.

[0033] Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A wind tunnel test support device, comprising a test chamber (1), characterized in that: A circular tube (2) is fixedly connected to the lower surface of the test chamber (1). The circular tube (2) is connected to the interior of the test chamber (1). A rotating platform (3) is installed on the circular tube (2). A lifting mechanism is fixedly connected to the upper surface of the rotating platform (3). An adjustment mechanism one and an adjustment mechanism two are installed on both sides of the lifting mechanism. A support plate (4) is connected to the upper ends of the lifting mechanism, the adjustment mechanism one and the adjustment mechanism two.

2. The wind tunnel test support device according to claim 1, characterized in that: The lifting mechanism includes two electric telescopic rods (5) fixedly connected to the rotating platform (3). The upper ends of the two electric telescopic rods (5) are connected to a rotating shaft (6). Both ends of the rotating shaft (6) are rotatably connected to rotating blocks (7). The two rotating blocks (7) are fixedly connected to the lower surface of the support plate (4).

3. The wind tunnel test support device according to claim 1, characterized in that: The adjustment mechanism includes two rotating blocks (8) fixedly connected to the rotating platform (3). A rotating shaft (9) is rotatably connected between the two rotating blocks (8). A multi-stage electric telescopic rod (10) is fixedly connected to the rotating shaft (9). A rotating shaft (11) is fixedly connected to the upper end of the multi-stage electric telescopic rod (10). A rotating block (12) is rotatably connected to both ends of the rotating shaft (11). The upper ends of the two rotating blocks (12) are fixedly connected to the lower surface of the support plate (4).

4. A wind tunnel test support device according to claim 3, characterized in that: The structure of the second adjustment mechanism is the same as that of the first adjustment mechanism.

5. A wind tunnel test support device according to claim 1, characterized in that: The support plate (4) is equipped with anti-slip pads or double-sided tape.

6. A wind tunnel test support device according to claim 1, characterized in that: The lower end of the round tube (2) is fixedly connected to an internally threaded tube (13), and the outer wall of the rotating platform (3) is fixedly connected to an externally threaded tube (14) that matches the internally threaded tube (13).

7. A wind tunnel test support device according to claim 1, characterized in that: The support plate (4) is fixedly connected to a multi-stage electric telescopic rod three (15), which penetrates the upper surface of the support plate (4) and has double-sided adhesive glued to its front end.

Images