Wind tunnel test model supporting device and test method
By designing a wind tunnel test model support device including balance cabin, model support rod and wind tunnel support rod, the problem of being unable to measure the aerodynamic data of the aircraft without obvious fuselage reduction ratio is solved, and various test models are realized. Aerodynamic measurement under different conditions has universal applicability and ease of use.
Patent Information
- Application Number
- CN202310943256.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2023-07-28
- Publication Date
- 2025-02-14
AI Technical Summary
The existing wind tunnel test support device cannot effectively measure the aerodynamic data of aircraft shrinkage models with no obvious fuselage or significant differences from traditional aircraft in wind tunnel tests, especially for wind tunnel tests of 8 meters. In terms of.
A wind tunnel test model support device was designed, including balance cabin, model support rod and wind tunnel support rod. The balance cabin adopts the shape of a fairing, and the balance is fixed in the balance cabin. The model support rod connects the balance cabin and the test model, and the wind tunnel is The support rod connects the balance compartment and the model attitude angle control mechanism to ensure that the balance axis is parallel to the test model axis.
The device can measure aerodynamic data of various test models under different attitude angles and test conditions. It has simple structure and easy to use, and has universal promotional significance.
Smart Images
Figure CN119437627A_ABST
Abstract
Description
Technical Field
[0001] The invention belongs to the field of experimental aerodynamics, and in particular relates to a wind tunnel test support device and a test method. Background Art
[0002] During the aircraft design phase, wind tunnel tests are generally conducted to obtain the aerodynamic forces that the aircraft is subject to when it moves relative to the airflow. Wind tunnel tests are based on the principle of similarity, using a scaled model of the aircraft fixed in the center of the wind tunnel for a wind-blown test. This can obtain the aerodynamic data of the scaled model, and then based on aerodynamic theory and experience, the data is corrected for Reynolds number, compressibility, static elasticity, dynamic influence, and balancing, so that the aerodynamic forces of the actual aircraft during flight can be predicted. In order to obtain aerodynamic forces during wind tunnel tests, a balance is needed to measure them. The configuration of a traditional aircraft generally includes wings, fuselage, tail, engine nacelle and landing gear, etc. If a rod-type or box-type balance is used to measure the aerodynamic force on the aircraft scale model, the balance is generally placed in the fuselage, the front end of the balance is connected to the fuselage through a flange or a connecting plane, and the rear end is connected to the wind tunnel strut through a flange. The wind tunnel strut is connected to the model attitude angle control mechanism of the wind tunnel to achieve the change of the angle of attack and sideslip angle of the aircraft during the wind tunnel test. At the same time, the wind tunnel strut and any part of the aircraft model cannot touch each other during the wind tunnel test. In this way, the aerodynamic force on the entire aircraft scale model is transmitted to the balance through the fuselage, so that the balance is used to measure the force, and finally the aerodynamic data of the aircraft scale model in a certain state is obtained. Through the above description, it can be seen that the current wind tunnel strut and balance system can only measure the aerodynamic force of the fuselage aircraft, and requires that the fuselage has enough space to accommodate the balance, as well as space for connecting the balance and the wind tunnel strut.
[0003] With the development of aviation technology, especially the development of UAV technology, there are now more and more aircraft without obvious fuselage, fuselage that is very different from traditional aircraft (especially slender or short and thick), fuselage that is not on the symmetry plane of the aircraft, such as flying wing, connecting wing, twin-fuselage aircraft, unmanned transport aircraft with special purposes, etc. Due to the limitations of the fuselage of these aircraft, there is not enough space to accommodate the above-mentioned existing balance and strut system to measure the aerodynamic force of the aircraft scale model. Especially for the 8-meter wind tunnel test, it can only be carried out with a built-in rod or box balance. Even if a new special balance is designed for the above-mentioned type of aircraft for wind tunnel testing, it is often impossible to achieve due to the limitations of the fuselage. Summary of the invention
[0004] In order to solve the above problems, an object of the present invention is to provide a simple and effective wind tunnel test model supporting device and a wind tunnel test method.
[0005] A wind tunnel test model support device, characterized in that the support device contains a balance cabin, a model support rod and a wind tunnel support rod, the balance cabin has a fairing shape, and the fairing is a streamlined swivel body, a balance for measuring aerodynamic force is fixed in the balance cabin, the lower end of the model support rod is fixed to the front joint at the front end of the balance cabin, the upper end of the model support rod is fixedly connected to the test model, the upper end of the wind tunnel support rod is connected and fixed to the rear end of the balance through a joint, the wind tunnel support rod is connected to the model attitude angle control mechanism of the wind tunnel, and the balance axis in the balance cabin is parallel to the axis of the test model.
[0006] The wind tunnel test model supporting device is characterized in that the left side of the front joint is connected and fixed to the front end of the balance, and the upper end of the front joint has a joint docking surface, which is used to dock with the lower end of the model support rod.
[0007] The wind tunnel test model supporting device is characterized in that there is a gap between the fairing and the wind tunnel support rod.
[0008] The wind tunnel test model support device is characterized in that the upper end of the model support rod is provided with an upper docking surface that is horizontally docked with the test model, and the lower end of the model support rod is provided with a lower docking surface that matches the joint docking surface of the front joint, and the upper docking surface and the lower docking surface are parallel to each other and parallel to the axis of the balance.
[0009] The wind tunnel test model supporting device is characterized in that the fairing includes a front fairing, a middle fairing and a rear fairing, the front fairing is connected to the front end of the front joint, the middle fairing is connected to the rear outer side of the front joint, and the rear fairing is connected to the middle fairing.
[0010] A wind tunnel test method, characterized in that it includes the following contents: 1) using the above-mentioned wind tunnel test model support device; 2) fixing the test model on the upper end of the model support rod of the support device so that the axis of the test model is parallel to the axis of the balance in the balance cabin of the support device; 3) placing the test model and the balance cabin of the support device in the wind tunnel through the wind tunnel support rod, and the lower end of the wind tunnel support rod is connected to the model attitude angle control mechanism; 4) the model attitude angle control mechanism controls the axis angle of the test model through the wind tunnel support rod to realize the change of the model attitude angle during the wind tunnel test, so that the aerodynamic force exerted on the test model under different attitude angles and test conditions can be measured.
[0011] The beneficial effects of the present application are: 1) the present application places a balance for measuring aerodynamic force in an independent balance cabin, connects the balance cabin to the test model through a model support rod, and the balance cabin and the test model are connected into an integrated structure supported at the front end of the wind tunnel support rod, which can realize wind tunnel tests of various test models; 2) the wind tunnel test support device of the present application has a simple structure, is easy to use, and has universal promotion significance. BRIEF DESCRIPTION OF THE DRAWINGS
[0012] Figure 1 This is a schematic diagram of the installation relationship between the wind tunnel test model support device and the test model in the wind tunnel test.
[0013] Figure 2 This is a schematic diagram of the structure of the wind tunnel test model support device.
[0014] Figure 3 This is a schematic diagram of the balance cabin structure.
[0015] Figure 4 Schematic diagram of the model support rod structure.
[0016] Figure 5 This is a schematic diagram of the front joint structure.
[0017] Explanation of numbers in the figure: 1 wind tunnel, 2 test model, 3 balance cabin, 4 model support rod, 5 wind tunnel support rod, 6 front fairing, 7 middle fairing, 8 rear fairing, 9 balance, 10 front joint, 11 upper docking surface, 12 lower docking surface, 13 joint docking surface. DETAILED DESCRIPTION
[0018] Referring to the accompanying drawings, the wind tunnel test model support device of the present application comprises a balance cabin 3, a model support rod 4 and a wind tunnel support rod 5. The balance cabin 3 has a fairing in shape, and the fairing is a streamlined swivel body. A balance 9 for measuring aerodynamic force is fixed in the balance cabin 3. The lower end of the model support rod 4 is fixed to a front joint 10 at the front end of the balance cabin, and the upper end of the model support rod 4 is fixedly connected to the test model 2. The upper end of the wind tunnel support rod 5 is connected and fixed to the rear end of the balance 9 through a joint. The wind tunnel support rod 5 is connected to the model attitude angle control mechanism of the wind tunnel, and the balance axis in the balance cabin 3 is parallel to the axis of the test model 2.
[0019] The front joint 10 is located in the balance cabin 3. The front joint 10 is a rotating body. The left side of the front joint 10 is connected and fixed to the front end of the balance 9 by screws. The upper end of the front joint 10 has a horizontal joint interface 13, which is used to connect with the lower end of the model support rod 2. The front joint 10 is the main load-bearing component. The aerodynamic force on the test model 2 is basically concentrated on this component, so it is processed by metal materials, generally high-strength alloy steel.
[0020] There is a gap of about 5 mm between the fairing of the balance cabin 3 and the wind tunnel support rod 5. This gap ensures that during the wind tunnel test, the wind tunnel support rod 5 will not interfere with the fairing of the balance cabin when adjusting the attitude of the model attitude angle control mechanism of the wind tunnel, and ensures that no large airflow cross-flow will occur.
[0021] In the implementation, the upper end of the model support rod 4 is provided with an upper docking surface 11 that is horizontally docked with the test model 2, and the lower end of the model support rod 4 is provided with a lower docking surface 12 that matches the joint docking surface 13 of the front joint 10, and the upper docking surface 11 and the lower docking surface 12 are parallel to each other and parallel to the axis of the balance 9. In the implementation, the upper docking surface 11 and the lower docking surface 12 can be square, rectangular, circular, elliptical or other shapes determined according to the connection needs. The upper docking surface 11 is connected to the aircraft scaled test model 2 by screws, the model support rod 4 can be circular, multi-prism or wing-shaped, and the lower docking surface 12 of the model support rod 4 is connected to the front end joint of the balance cabin through a flange. A hole or groove is set in the middle part of the model support rod for the pressure measuring tube, motor wire, motor control line, cooling water (oil) pipe, balance signal line, etc. to pass through. The length of the model support rod 4 is comprehensively considered according to the specific conditions of the test wind tunnel 1 and the test model 2, mainly to reduce the influence of the wake generated by the balance cabin on the aerodynamic force of the test model 2, and to prevent the test model 2 from deviating too far from the center of the wind tunnel 1.
[0022] In practice, the main function of the balance cabin fairing is to isolate the balance 9 and the balance rear joint from the external airflow and provide fairing to reduce resistance. To ensure good processability, the fairing includes a front fairing 6, a middle fairing 7 and a rear fairing 8, the front fairing 6 is connected to the front end of the front joint 10, the middle fairing 7 is connected to the rear outer side of the front joint 10, and the rear fairing 8 is connected to the middle fairing 7.
[0023] For the convenience of processing, the front joint 10 and the middle fairing 7 can be combined into one component and processed as a whole, provided that the weight and strength meet the requirements.
[0024] In the balance cabin 3, the front end of the balance 9 is positioned with the front joint 10 by pins and connected with screws. The rear part of the balance 9 is connected with the upper part of the wind tunnel support rod 5 by screws through a joint. The lower part of the wind tunnel support rod 5 is connected with the model attitude angle control mechanism of the wind tunnel. The change of the model attitude angle during the wind tunnel test is realized by the control of the model attitude angle control mechanism, so that the aerodynamic force exerted on the test model 2 under different attitude angles and test conditions can be measured.
[0025] When the wind tunnel test model support device is used to perform a wind tunnel test, the test model 2 is fixed to the upper end of the model support rod 4 of the support device so that the axis of the test model 2 is parallel to the axis of the balance 9 in the balance cabin of the support device; the test model 2 and the balance cabin 3 of the support device are placed in the wind tunnel 1 through the wind tunnel support rod 5, and the lower end of the wind tunnel support rod 5 is connected to the model attitude angle control mechanism; the model attitude angle control mechanism controls the axis angle of the test model 2 through the wind tunnel support rod 5 to realize the change of the model attitude angle during the wind tunnel test, so that the aerodynamic force exerted on the test model 2 under different attitude angles and test conditions can be measured.
Claims
1. A wind tunnel test model support device, characterized in that: The supporting device comprises a balance cabin, a model support rod and a wind tunnel support rod. The balance cabin has a fairing shape, and the fairing is a streamlined rotating body. A balance for measuring aerodynamic force is fixed in the balance cabin. The lower end of the model support rod is fixed on a front joint at the front end of the balance cabin. The upper end of the model support rod is fixedly connected to a test model. The upper end of the wind tunnel support rod is connected and fixed to the rear end of the balance through a joint. The wind tunnel support rod is connected to a model attitude angle control mechanism of the wind tunnel. The axis of the balance in the balance cabin is parallel to the axis of the test model.
2. The wind tunnel test model support device according to claim 1, characterized in that: The left side of the front joint is connected and fixed to the front end of the balance, and the upper end of the front joint is provided with a joint docking surface, which is used for docking with the lower end of the model support rod.
3. The wind tunnel test model support device according to claim 1, characterized in that: There is a gap between the fairing and the wind tunnel support rod.
4. The wind tunnel test model support device according to claim 1, characterized in that: The upper end of the model support rod is provided with an upper docking surface horizontally docked with the test model, and the lower end of the model support rod is provided with a lower docking surface matching the joint docking surface of the front joint. The upper docking surface and the lower docking surface are parallel to each other and to the axis of the balance.
5. The wind tunnel test model support device according to claim 1, characterized in that: The fairing comprises a front fairing, a middle fairing and a rear fairing, wherein the front fairing is connected to the front end of the front joint, the middle fairing is connected to the rear outer side of the front joint, and the rear fairing is connected to the middle fairing.
6. A wind tunnel test method, characterized in that The invention comprises the following contents: 1) using any one of the wind tunnel test model support devices as described in claims 1 to 5; 2) fixing the test model on the upper end of the model support rod of the support device so that the axis of the test model is parallel to the axis of the balance in the balance cabin of the support device; 3) placing the test model and the balance cabin of the support device in the wind tunnel through the wind tunnel support rod, and the lower end of the wind tunnel support rod is connected to the model attitude angle control mechanism; 4) the model attitude angle control mechanism controls the axis angle of the test model through the wind tunnel support rod to realize the change of the model attitude angle during the wind tunnel test, so as to measure the aerodynamic force exerted on the test model under different attitude angles and test conditions.