Symmetrical pressure measurement structure of thin-wall wind tunnel pressure measurement test model
By setting up a symmetrical pressure measurement structure on a thin-walled wind tunnel test model, and using pressure measurement units and pressure measurement tubes to achieve symmetrical pressure measurement, the difficulty of pressure measurement at thin-walled locations was solved, ensuring the accuracy of load data and meeting design requirements.
Patent Information
- Application Number
- CN202520187770.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-02-06
- Publication Date
- 2025-12-23
- Estimated Expiration
- 2035-02-06
AI Technical Summary
In the existing technology, wind tunnel test models at thin-walled locations cannot achieve bilateral symmetrical pressure measurement, resulting in the inability to accurately obtain load data at the top and bottom of the airfoil, which affects design judgment.
A symmetrical pressure measurement structure for a thin-walled wind tunnel pressure measurement test model is designed. By setting pressure measurement units on the main body of the airfoil, and using pressure measurement tubes to symmetrically extend the pressure measurement points to both sides of the airfoil, symmetrical pressure measurement is achieved through the symmetrical arrangement of pressure measurement blocks and pressure measurement tubes.
It enables accurate measurement of load data at the top and bottom of thin-walled airfoils, solves the difficulty of pressure measurement at thin-walled locations, and ensures that designers obtain accurate aerodynamic performance data.
Smart Images
Figure CN223711017U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of wind tunnel model technology, and more specifically, to a symmetrical pressure measurement structure for a thin-walled wind tunnel pressure measurement test model. Background Technology
[0002] In the process of aircraft development, an indispensable task is to conduct wind tunnel tests of various types (such as force measurement, pressure measurement, and heat measurement). The usual approach is to manufacture a scaled-down physical model of the aircraft and then use wind tunnel tests to verify the theoretical design data.
[0003] To improve the overall aerodynamic performance of an aircraft, the trailing edge (such as ailerons, flaps, and spoilers) is often designed to be relatively thin, and designers are very concerned about the aerodynamic characteristics and load conditions in these areas. Currently, in the design of such wind tunnel test models, pressure measurement is often impossible or only unilateral pressure measurement is possible at these thinner areas. This results in the inability to obtain accurate load data from both the upper and lower parts of the wing surface simultaneously, ultimately affecting the designer's judgment. Therefore, how to provide a structure that can achieve symmetrical pressure measurement on both sides for thinner areas is a problem that urgently needs to be solved in this field. Utility Model Content
[0004] The purpose of this invention is to provide a symmetrical pressure measurement structure for a thin-walled wind tunnel pressure measurement test model, so as to solve the above-mentioned defects of the prior art.
[0005] This utility model is achieved through the following technical solution:
[0006] A symmetrical pressure measurement structure for a thin-walled wind tunnel pressure measurement test model includes an airfoil body and a pressure measurement unit corresponding to the number of measurement points. The pressure measurement unit includes a pressure measurement block and two pressure measurement tubes. Pressure measurement holes are symmetrically arranged on both sides of the pressure measurement block. A connection hole is provided on one side of the pressure measurement block, perpendicular to the pressure measurement hole and communicating with it. The pressure measurement tubes are fixedly connected to the connection hole.
[0007] The main body of the wing has mounting slots that run through the upper and lower wing surfaces at various measuring points. The upper and lower wing surfaces are symmetrically equipped with wiring slots that correspond one-to-one with each mounting slot. The wiring slots on the same side converge on one side of the main body of the wing. The pressure measuring block is located in the mounting slot, and the pressure measuring tube is located in the wiring slot and extends out of the main body of the wing from the confluence point. The wiring slot is filled with a type of filler.
[0008] Optionally, the wing body has lead-out holes at the intersection of each wiring groove, and each of the pressure measuring tubes extends out of the wing body from the lead-out holes.
[0009] Optionally, the connecting hole is a stepped hole with a larger outer end and a smaller inner end, wherein the diameter of the larger end of the connecting hole is equal to the outer diameter of the pressure measuring tube, and the diameter of the smaller end of the connecting hole is equal to the inner diameter of the pressure measuring tube.
[0010] Optionally, the diameter of the pressure hole is equal to the inner diameter of the pressure tube.
[0011] Optionally, the pressure block is in interference fit with the mounting groove.
[0012] Optionally, the pressure block and the mounting groove are fixed by laser welding.
[0013] Optionally, the width and depth of the wiring groove are greater than the diameter of the pressure tube by 0.5-1mm.
[0014] Optionally, the pressure tube is connected with the connecting hole by bonding or soldering.
[0015] Optionally, the additional filler is metal putty or AB glue.
[0016] The technical scheme of the utility model has at least the following advantages and beneficial effects: in the utility model, the pressure measuring unit is arranged on the wing surface main body, the pressure measuring point is extended to one side by the pressure tube, and the two pressure holes and the two pressure tubes in each pressure measuring unit are symmetrically arranged on the two sides of the upper and lower wing surfaces, the difficulty of symmetric pressure measurement of the pressure measuring point on the wing surface main body with thin wall thickness is solved, and the load data of the upper and lower wing surfaces with thin wall thickness can be accurately obtained. BRIEF DESCRIPTION OF DRAWINGS
[0017] Figure 1 It is a front structure schematic view of the symmetric pressure measurement structure of the thin-wall wind tunnel pressure test model provided by the utility model;
[0018] Figure 2 It is a back structure schematic view of the symmetric pressure measurement structure of the thin-wall wind tunnel pressure test model provided by the utility model;
[0019] Figure 3 It is a front structure schematic view of the symmetric pressure measurement structure of the thin-wall wind tunnel pressure test model provided by the utility model (before filling the additional filler);
[0020] Figure 4 It is a back structure schematic view of the symmetric pressure measurement structure of the thin-wall wind tunnel pressure test model provided by the utility model (before filling the additional filler);
[0021] Figure 5 It is a front structure schematic view of the wing surface main body;
[0022] Figure 6 It is a back structure schematic view of the wing surface main body;
[0023] Figure 7 It is a structure schematic view of the pressure measuring unit;
[0024] Figure 8 It is a sectional view of the pressure measuring unit;
[0025] Reference numerals: 1 - airfoil body, 101 - mounting groove, 102 - wiring groove, 103 - lead-out hole, 2 - pressure measuring block, 201 - pressure measuring hole, 202 - connecting hole, 3 - pressure measuring tube, 4 - profile filler. DETAILED DESCRIPTION
[0026] Reference Figure 1 A symmetrical pressure measuring structure of a thin-walled wind tunnel test model includes an airfoil body and pressure measuring units, the number of the pressure measuring units being the same as the number of measuring points on the airfoil body. For example, in actual application, five pressure measuring points are selected on the airfoil body, and there are also five pressure measuring units.
[0027] The pressure measuring unit includes a pressure measuring block and two pressure measuring tubes. Symmetrically arranged on both sides of the pressure measuring block are pressure measuring holes. It is easy to understand that the axes of the two pressure measuring holes are located on a straight line, but they are not connected to each other and are symmetric about the middle part in the thickness direction of the pressure measuring block. One side of the pressure measuring block is provided with a connecting hole perpendicular to the pressure measuring hole and connected thereto. As an option, the connecting hole is a stepped hole with a large outer end and a small inner end. The large end diameter of the connecting hole is equal to the outer diameter of the pressure measuring tube, and the small end diameter of the connecting hole is equal to the inner diameter of the pressure measuring tube. Further, the diameter of the pressure measuring hole is also equal to the inner diameter of the pressure measuring tube, so that the entire path size from the pressure measuring hole into the pressure measuring tube is consistent, avoiding the influence of cross-section change on the test results.
[0028] In actual application, for example, there are three specifications of pressure measuring tubes, the first one has an outer diameter of 0.6 mm and an inner diameter of 0.3 mm, the second one has an outer diameter of 0.8 mm and an inner diameter of 0.5 mm, and the third one has an outer diameter of 1 mm and an inner diameter of 0.6 mm. Corresponding to the first pressure measuring tube, the large end diameter of the connecting hole is 0.6 mm, and the small end diameter of the connecting hole and the diameter of the pressure measuring hole are 0.3 mm. Corresponding to the second pressure measuring tube, the large end diameter of the connecting hole is 0.8 mm, and the small end diameter of the connecting hole and the diameter of the pressure measuring hole are 0.5 mm. Corresponding to the third pressure measuring tube, the large end diameter of the connecting hole is 1 mm, and the small end diameter of the connecting hole and the diameter of the pressure measuring hole are 0.6 mm.
[0029] The pressure measuring tube is fixedly connected with the connecting hole, so that the pressure measuring tube and the pressure measuring block form an integral whole. As an option, the pressure measuring tube can be adhesively fixed with the connecting hole, or the pressure measuring tube can be fixed with the connecting hole by soldering.
[0030] The airfoil body is provided with a mounting groove penetrating the upper and lower airfoils at each measuring point position, and the upper and lower airfoils are symmetrically provided with wiring grooves corresponding to each mounting groove. The wiring grooves on the same side converge at one side of the airfoil body. The pressure measuring block is arranged in the mounting groove, and the pressure measuring tube is arranged in the wiring groove and extends out of the airfoil body from the convergence position. In actual application, the pressure measuring tube extending out of the airfoil body is connected with a pressure scanning valve used for testing.
[0031] As an alternative, the pressure block is in interference fit with the mounting groove, further, a bevel can be used to slope the mounting groove at the upper and lower wing surfaces, and then the pressure block is fixed by laser welding, so as to ensure the reliability of the connection between the pressure block and the wing surface body. As an alternative, the wing surface body is provided with a lead-out hole at the intersection of each wiring groove, and each pressure tube extends out of the wing surface body from the lead-out hole. The lead-out hole can be used to preliminarily fix the pressure tube when arranging the pressure tube.
[0032] The width and depth of the wiring groove are greater than the diameter of the pressure tube by 0.5-1mm, and then the pressure tube is filled with a supplementary filler after being assembled. It is easy to understand that the surface of the wing surface body needs to be shaped and polished according to the local surface after the wiring groove is filled. As an alternative, the supplementary filler can be a metal putty, an AB glue or other fillers.
[0033] As can be seen from the above, the utility model discloses a pressure measuring unit arranged on the wing surface body, and the pressure measuring point is extended to one side by the pressure tube, and the two pressure holes and the two pressure tubes in each pressure measuring unit are symmetrically arranged on the two sides of the upper and lower wing surfaces, so that the difficulty of symmetrically measuring the pressure of the pressure measuring point on the wing surface body with thin wall thickness is solved, and the load data of the upper and lower wing surfaces with thin wall thickness can be accurately obtained.
[0034] The above is only the preferred embodiment of the utility model, and is not used to limit the utility model. For those skilled in the art, the utility model can have various changes and changes. Any modification, equivalent replacement, improvement, etc. within the spirit and principles of the utility model should be included in the protection scope of the utility model.
Claims
1. A symmetrical pressure measurement structure for a thin-walled wind tunnel pressure measurement test model, comprising a main airfoil, characterized in that, It also includes a pressure measuring unit corresponding to the number of measuring points. The pressure measuring unit includes a pressure measuring block and two pressure measuring tubes. The pressure measuring block has pressure measuring holes symmetrically arranged on both sides. One side of the pressure measuring block has a connection hole perpendicular to the pressure measuring hole and communicating with it. The pressure measuring tubes are fixedly connected to the connection hole. The main body of the wing has mounting slots that run through the upper and lower wing surfaces at various measuring points. The upper and lower wing surfaces are symmetrically equipped with wiring slots that correspond one-to-one with each mounting slot. The wiring slots on the same side converge on one side of the main body of the wing. The pressure measuring block is located in the mounting slot, and the pressure measuring tube is located in the wiring slot and extends out of the main body of the wing from the confluence point. The wiring slot is filled with a type of filler.
2. The symmetrical pressure measurement structure of the thin-walled wind tunnel pressure measurement test model according to claim 1, characterized in that, The wing body has lead-out holes at the intersection of each wiring groove, and each of the pressure measuring tubes extends out of the wing body from the lead-out holes.
3. The symmetrical pressure measurement structure of the thin-walled wind tunnel pressure measurement test model according to claim 1, characterized in that, The connecting hole is a stepped hole with a larger outer end and a smaller inner end. The diameter of the larger end of the connecting hole is equal to the outer diameter of the pressure measuring tube, and the diameter of the smaller end of the connecting hole is equal to the inner diameter of the pressure measuring tube.
4. The symmetrical pressure measurement structure of the thin-walled wind tunnel pressure measurement test model according to claim 3, characterized in that, The diameter of the pressure measuring hole is also equal to the inner diameter of the pressure measuring tube.
5. The symmetrical pressure measurement structure of the thin-walled wind tunnel pressure measurement test model according to any one of claims 1-4, characterized in that, The pressure testing block is interference-fitted with the mounting groove.
6. The symmetrical pressure measurement structure of the thin-walled wind tunnel pressure measurement test model according to claim 5, characterized in that, The pressure measuring block is fixed to the mounting groove by laser welding.
7. The symmetrical pressure measurement structure of the thin-walled wind tunnel pressure measurement test model according to any one of claims 1-4, characterized in that, The width and depth of the wiring groove are both 0.5-1 mm greater than the diameter of the pressure measuring tube.
8. The symmetrical pressure measurement structure of the thin-walled wind tunnel pressure measurement test model according to any one of claims 1-4, characterized in that, The pressure measuring tube is bonded or soldered to the connecting hole.
9. The symmetrical pressure measurement structure of the thin-walled wind tunnel pressure measurement test model according to any one of claims 1-4, characterized in that, The filler material is either metallic putty or AB glue.