A method for controlling the installation precision of a wind tunnel test model airfoil

Abstract

The present application relates to the technical field of aerodynamic model, provide a kind of wind tunnel test model airfoil installation precision control method, comprising the following steps: S1, the airfoil is connected assembly through the angle block of certain angle, the upper and lower profile three coordinates of airfoil under current angle are detected;S2, if three coordinate detection result has deviation, then airfoil is unqualified, use laser marking machine to mark out the convex of certain thickness on the target position of airfoil mounting surface and / or model main body mounting surface, airfoil and model main body are corrected;S3, if three coordinate detection is qualified, then airfoil and the angle block of this angle are qualified, the airfoil is connected assembly through the angle block of other angle, the feature point detection of airfoil under other angle, if detection result appears deviation, use laser marking machine to mark out the convex of certain thickness on the target position of angle block mounting surface, correct angle block.The present application improves efficiency while very good guarantee airfoil installation precision.

Description

Technical Field

[0001] This invention relates to the field of aerodynamic model technology, and more specifically, to a method for controlling the installation accuracy of the wing surface of a wind tunnel test model. Background Technology

[0002] In the development of various aircraft, wind tunnel testing using scaled-down models is an extremely important research method. The wings, canards, vertical stabilizers, horizontal stabilizers, ailerons, flaps, slats, leading flaps, spoilers, rudders, elevators, etc., on the model all belong to the airfoil surfaces of the wind tunnel test model. Generally, each airfoil is unique. By designing several angle blocks at different angles (e.g., 0° angle blocks, -20° angle blocks, -10° angle blocks, 10° angle blocks, 20° angle blocks, etc., where the corresponding angle refers to the angle formed between the airfoil and the model body), the airfoil is made to have different angle states to simulate the actual flight state of the aircraft. Each angled airfoil has its correct position. Due to the inherent machining errors of the airfoil and angle blocks, their correct installation position cannot be directly guaranteed after the machining process. Therefore, certain methods are needed during the assembly stage to control their installation accuracy.

[0003] Currently, the common method is to adjust the installation accuracy using shims to meet the required design standards. However, the airfoil requires frequent disassembly and assembly; each time an angle block is replaced, disassembly and assembly are necessary. Each time, shims need to be installed according to the airfoil installation deviation to adjust and control the installation accuracy. This often requires a significant amount of time to ensure the correct airfoil installation and repeatability, resulting in low efficiency and difficulty in effectively guaranteeing installation accuracy, thus affecting the delivery cycle and quality of wind tunnel test models. Therefore, how to provide a highly efficient method for controlling the airfoil installation accuracy of wind tunnel test models is a technical problem that urgently needs to be solved in this field. Summary of the Invention

[0004] The purpose of this invention is to provide a method for controlling the installation accuracy of the airfoil of a wind tunnel test model, thereby solving the technical problems of low efficiency and difficulty in effectively ensuring the installation accuracy of existing methods.

[0005] The embodiments of the present invention are achieved through the following technical solutions:

[0006] A method for controlling the installation accuracy of the airfoil of a wind tunnel test model includes the following steps:

[0007] S1. Connect the wing surface with an angle block at a certain angle, assemble it on the main body of the model, and perform three-coordinate detection on the upper and lower surfaces of the wing surface at the current angle.

[0008] S2. If the coordinate measuring machine result of step S1 is greater than or less than the theoretical deviation, it indicates that the wing surface processing is unqualified. Use a laser marking machine to mark a protrusion of a certain thickness on the target position on the wing surface mounting surface and / or the model body mounting surface, and perform coordinate measuring machine detection again until the wing surface is assembled in the correct position.

[0009] S3. If the three-coordinate measurement in step S1 is qualified, it means that the airfoil and the angle block at that angle are qualified. Then connect the airfoil with angle blocks at other angles and assemble it on the main body of the model. Check the feature points of the airfoil at other angles (the feature points are generally selected as the two sharp points on the trailing edge side). If the test result is greater than or less than the theoretical deviation, use a laser marking machine to mark a protrusion of a certain thickness on the target position of the angle block mounting surface and check again until the angle block and airfoil are assembled in the correct position.

[0010] Optionally, in step S2, if the coordinate measuring machine result of step S1 is greater than the theoretical deviation, a protrusion is marked on the mounting surface of the model body near the trailing edge and / or on the mounting surface of the wing near the leading edge using a laser marking machine; if the coordinate measuring machine result of step S1 is less than the theoretical deviation, a protrusion is marked on the mounting surface of the model body near the leading edge and / or on the mounting surface of the wing near the trailing edge using a laser marking machine.

[0011] Optionally, in step S3, if the detection result is greater than the theoretical deviation, a protrusion is marked on the main body of the angle block mounting surface near the trailing edge and / or on the wing surface near the leading edge using a laser marking machine; if the detection result is less than the theoretical deviation, a protrusion is marked on the main body of the angle block mounting surface near the leading edge and / or on the wing surface near the trailing edge using a laser marking machine.

[0012] Optionally, in step S1, the angle block is a 0° angle block.

[0013] Optionally, in step S2, the width of the protrusion is 1 / 10 to 3 / 10 of the width of the mounting surface at its location; in step S3, the width of the protrusion is 1 / 10 to 3 / 10 of the width of the angle block.

[0014] Optionally, in step S2, the width of the protrusion is 1 / 5 of the width of the mounting surface at its location; in step S3, the width of the protrusion is 1 / 5 of the width of the angle block.

[0015] Optionally, after the coordinate measuring machine (CMM) detection in step S1 is qualified, the angle block at the current angle is installed and feature point detection is performed. The fluctuation range of the detected feature point data is compared again with the fluctuation range of the airfoil profile data detected by the CMM, so as to ensure the repeatability of the airfoil's deflection angle.

[0016] Optionally, in step S2, after marking is completed, the wing surface is subjected to at least three assembly / disassembly operations and at least three feature point detections.

[0017] Optionally, in step S3, after the marking is completed, the angle block is assembled and disassembled at least three times and the feature point is detected at least three times.

[0018] The present invention has at least the following advantages and beneficial effects: In the present invention, the upper and lower surfaces of the wing surface at a certain angle are first subjected to coordinate measuring machine (CMM) testing. If the CMM test is unqualified, it indicates that the wing surface processing is unqualified. Then, the wing surface and the model body, which are common parts, are corrected. That is, a laser marking machine is used to mark a protrusion of a certain thickness at the target position on the wing surface mounting surface and / or the model body mounting surface. If the CMM test is qualified, the wing surface feature points at other angles are subjected to CMM testing. If the test result is greater than or less than the theoretical deviation, the angle block is corrected. That is, a laser marking machine is used to mark a protrusion of a certain thickness at the target position on the angle block mounting surface. In other words, the protrusion marked in the present invention acts as a substitute for the shim. The protrusion is always present, which is well adapted to repeated and frequent disassembly and assembly. Only the initial adjustment and correction are required during the initial installation. No correction is required in each subsequent disassembly and assembly process. This method improves efficiency while ensuring the wing surface installation accuracy. Attached Figure Description

[0019] To more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of the present invention and should not be regarded as a limitation on the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0020] Figure 1 A flowchart of a method for controlling the installation accuracy of a wind tunnel test model wing surface provided by the present invention;

[0021] Figure 2 This is a schematic diagram of the overall structure of the wind tunnel test model;

[0022] Figure 3 A schematic diagram showing the markings on the wing surface and the main body of the model;

[0023] Figure 4 This is a schematic diagram showing the protrusions marked on the angle block.

[0024] Figure 5 This is a schematic diagram of the shape of the protrusion;

[0025] Icons: 1-Model body, 101-Model body mounting surface near the trailing edge, 102-Model body mounting surface near the leading edge, 2-Wing, 201-Wing mounting surface near the leading edge, 202-Wing mounting surface near the trailing edge, 3-Angle block, 301-Angle block mounting surface in contact with the model body near the trailing edge, 302-Angle block mounting surface in contact with the model body near the leading edge, 303-Angle block mounting surface in contact with the wing near the trailing edge, 304-Angle block mounting surface in contact with the wing near the leading edge, 4-Protrusion. Detailed Implementation

[0026] First, the premise for the application of this invention is that (1) the wing surface 2 and its corresponding angle block 3 are not deformed (if deformation occurs, it will be exposed during the completion inspection of the early parts, and corresponding rectification will be made at that time, which is not within the scope of this invention); (2) the measured deflection angle data of each wing surface 2 is within ±6′, including 6′ (because according to the "Wind Tunnel Test Model Design Guidelines", the deflection angle data of each wing surface 2 should be within ±3′, so in practice, 90% of the deflection angle error of the processed wing surface 2 is within ±6′. If it exceeds ±6′, it needs to be solved by other means, which is not within the scope of this invention).

[0027] refer to Figure 1 A method for controlling the installation accuracy of the wing surface of a wind tunnel test model includes the following steps:

[0028] S1. Connect the wing surface 2 with an angle block 3 at a certain angle and assemble it onto the model body 1. Perform coordinate measuring machine (CMM) detection on the upper and lower surfaces of the wing surface 2 at the current angle. It is worth noting that this step can assemble the angle block 3 at any angle. However, since the final assembly and inspection of the wind tunnel test model needs to be determined based on the initial state of the wind tunnel test model, the 0° angle block 3 is usually selected as the common angle for this step. That is, in this embodiment, this step connects the wing surface 2 with the 0° angle block 3 and assembles it onto the model body 1. Perform coordinate measuring machine (CMM) detection on the upper and lower surfaces of the wing surface 2 at the 0° angle.

[0029] After the coordinate measuring machine (CMM) of the wing surface 2 at 0° passes the inspection, the wing surface 2 meets the prerequisite for component assembly inspection. At this time, the angle block 3 at 0° is installed and feature point detection is performed. The process of disassembly and reassembly is repeated three times, and the average value is taken. The fluctuation range of the detected feature point data (i.e., the average value) is compared with the fluctuation range of the wing surface 2 profile data detected by the CMM to ensure the repeatability of the wing surface 2's deflection angle and to eliminate other influencing factors in the feature point detection process (such as whether the detection platform is clean or whether there are measurement errors).

[0030] S2. If the coordinate measuring machine result of step S1 is greater than or less than the theoretical deviation, it means that the wing surface 2 is not qualified. Use a laser marking machine to mark a protrusion 4 of a certain thickness on the mounting surface of the wing surface 2 and / or the mounting surface of the model body 1 at the target position and perform coordinate measuring machine detection again until the wing surface 2 is assembled in the correct position.

[0031] Test Figure 2 It should be understood that the figure shows the state of the 0° angle block 3 being assembled. The upward-facing surface in the figure will face downward during the test, and the downward-facing surface in the figure will face upward during the test. That is, the upward-facing surface in the figure is the lower surface of the wing surface 2 and the model body 1, and the downward-facing surface in the figure is the upper surface of the wing surface 2 and the model body 1. In addition, the side pointed to by the arrow in the figure is the leading edge, and the side pointed to in the opposite direction is the trailing edge.

[0032] refer to Figure 3 If the three-coordinate detection result in step S1 is greater than the theoretical deviation, it means that the upper surface of the wing 2 is higher than the upper surface of the model body 1. Then, a protrusion 4 is marked on the mounting surface of the model body near the trailing edge region 101 using a laser marking machine, or a protrusion 4 is marked on the mounting surface of the wing near the leading edge region 201. If the deviation is too large, the protrusion 4 can also be marked on the mounting surface of the model body near the trailing edge region 101 and the mounting surface of the wing near the leading edge region 201 at the same time.

[0033] If the coordinate measuring machine result of step S1 is less than the theoretical deviation, it means that the upper surface of the wing 2 is lower than the upper surface of the model body 1. Then, a protrusion 4 is marked on the mounting surface of the model body near the leading edge region 102 using a laser marking machine, or a protrusion 4 is marked on the mounting surface of the wing near the trailing edge region 202. If the deviation is too large, the protrusion 4 can also be marked on the mounting surface of the model body near the leading edge region 102 and the mounting surface of the wing near the trailing edge region 202 at the same time.

[0034] S3. If the coordinate measuring machine (CMM) test in step S1 is qualified, it indicates that the wing surface 2 and the 0° angle block 3 are properly machined. Then, connect the wing surface 2 with the angle blocks 3 at other angles and assemble it onto the model body 1. Detect the feature points of the wing surface 2 at other angles. It is easy to understand that this step should involve detecting the wing surface 2 under each angle block 3 assembly. If the detection result is greater or less than the theoretical deviation, use a laser marking machine to mark a protrusion 4 of a certain thickness at the target position on the mounting surface of the angle block 3 and detect it again until the angle block 3 and the wing surface 2 are assembled in the correct position. It is worth noting that the feature point detection of the wing surface 2 in this step can be performed using a height gauge or a CMM. Preferably, this embodiment uses a height gauge for detection, which is simpler to operate.

[0035] refer to Figure 4 It should be noted that, Figure 3For ease of viewing, the areas of each marked protrusion 4 are shown on the opposite side of the mounting surface of the angle block 3. It should be understood that the protrusion 4 should actually be marked on the opposite side of the surface shown in the figure (i.e., the mounting surface). In step S3, if the three-coordinate measurement result is greater than the theoretical deviation, it means that the upper surface of the wing 2 is higher than the upper surface of the model body 1. In this case, the protrusion 4 is marked on the area 301 near the trailing edge of the part of the angle block mounting surface that contacts the model body using a laser marking machine, or the protrusion 4 is marked on the area 304 near the leading edge of the part of the angle block mounting surface that contacts the wing surface. If the deviation is too large, the protrusion 4 can also be marked on both the area 301 near the trailing edge of the part of the angle block mounting surface that contacts the model body and the area 304 near the leading edge of the part of the angle block mounting surface that contacts the wing surface.

[0036] If the coordinate measuring machine (CMM) test result is less than the theoretical deviation, it means that the upper surface of the wing surface 2 is lower than the upper surface of the model body 1. In this case, a protrusion 4 is marked on the part of the angle block mounting surface that contacts the model body near the leading edge region 302 using a laser marking machine, or a protrusion 4 is marked on the part of the angle block mounting surface that contacts the wing surface near the trailing edge region 303. If the deviation is too large, a protrusion 4 can also be marked on both the part of the angle block mounting surface that contacts the model body near the leading edge region 302 and the part of the angle block mounting surface that contacts the wing surface near the trailing edge region 303.

[0037] In step S2, after marking is completed, the wing surface 2 undergoes at least three assembly / disassembly cycles and at least three feature point checks to ensure the repeatability of the wing surface 2's installation angle. In step S3, after marking is completed, the angle block 3 undergoes at least three assembly / disassembly cycles and at least three feature point checks, similarly to ensure the repeatability of the wing surface 2's installation angle.

[0038] As can be seen from the above, the present invention first performs coordinate measuring machine (CMM) testing on the upper and lower surfaces of the wing surface 2 at a certain angle. If the CMM test fails, it indicates that the wing surface 2 is not properly processed. Therefore, the wing surface 2 and the model body 1, which are shared components, are corrected by using a laser marking machine to mark a protrusion 4 of a certain thickness at the target position on the mounting surface of the wing surface 2 and / or the mounting surface of the model body 1. If the CMM test fails, the feature points of the wing surface 2 at other angles are tested using CMM. If the test result is greater than or less than the theoretical deviation, the angle block 3 is corrected by using a laser marking machine to mark a protrusion 4 of a certain thickness at the target position on the mounting surface of the angle block 3. This invention... In this invention, the etched protrusions 4 serve as a substitute for gaskets. The protrusions 4 are always present, which is well adapted to repeated and frequent disassembly and assembly. Once the initial adjustment is corrected, there is no need to make corrections in each subsequent disassembly and assembly process. This method improves efficiency while ensuring the installation accuracy of the wing surface 2. Moreover, the protrusions 4 etched by the laser marking machine have high wear resistance. Under the premise that no one intentionally damages them by using oilstones, files or other grinding tools, the wear during multiple disassembly and assembly processes is negligible and will not affect the reproducibility of the wing surface 2 component assembly, thus ensuring the accuracy of repeated assembly.

[0039] In step S2, the width of the protrusion 4 is 1 / 10 to 3 / 10 of the width of the mounting surface at its location. Preferably, the width of the protrusion 4 is 1 / 5 of the width of the mounting surface at its location. That is to say, for example, if the protrusion 4 is marked on the mounting surface of the wing surface 2, then the width of the protrusion 4 is 1 / 5 of the width of the mounting surface of the wing surface 2. In step S3, the width of the protrusion 4 is 1 / 10 to 3 / 10 of the width of the angle block 3. Preferably, the width of the protrusion 4 is 1 / 5 of the width of the mounting surface of the angle block 3.

[0040] It is worth noting that after marking, the overall shape of the raised part 4 is similar to that of the barcode (e.g., Figure 5 As shown in the figure, the protrusion 4 is marked on the angle block 3, and the same applies to the protrusion 4 on the mounting surface of the wing surface 2 and the mounting surface of the model body 1.

[0041] Figure 3 neutralization Figure 4 The area between the two dashed lines represents the marking area of ​​protrusion 4, and the width between the two dashed lines is the width of protrusion 4. Furthermore, the thickness of protrusion 4 (i.e., the height of the protrusion) can be controlled by the number of marking cycles. It should be understood that marking the entire area using a laser marking machine counts as one cycle, then marking the already marked area again counts as another cycle, and so on. Each marking cycle increases the thickness of protrusion 4 by approximately 0.01 mm, and 10 marking cycles will result in an increase of 0.1 mm. It is easy to understand that the actual required marking thickness is determined by the absolute value of the actual deviation in the test results.

[0042] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A method for controlling the installation accuracy of the airfoil of a wind tunnel test model, characterized in that, Includes the following steps: S1. Connect the wing surface with an angle block at a certain angle, assemble it on the main body of the model, and perform three-coordinate detection on the upper and lower surfaces of the wing surface at the current angle. S2. If the coordinate measuring machine result of step S1 is greater than or less than the theoretical deviation, it indicates that the wing surface processing is unqualified. Use a laser marking machine to mark a protrusion of a certain thickness on the target position on the wing surface mounting surface and / or the model body mounting surface, and perform coordinate measuring machine detection again until the wing surface is assembled in the correct position. S3. If the three-coordinate detection in step S1 is qualified, it means that the wing surface and the angle block at that angle are qualified. Then connect the wing surface with angle blocks at other angles and assemble it on the main body of the model. Detect the feature points of the wing surface at other angles. If the detection result is greater than or less than the theoretical deviation, use a laser marking machine to mark a protrusion of a certain thickness at the target position on the angle block mounting surface and detect it again until the angle block and wing surface are assembled in the correct position.

2. The method for controlling the installation accuracy of the wing surface of the wind tunnel test model according to claim 1, characterized in that, In step S2, if the coordinate measuring machine result of step S1 is greater than the theoretical deviation, a protrusion is marked on the mounting surface of the model body near the trailing edge and / or on the mounting surface of the wing near the leading edge using a laser marking machine; if the coordinate measuring machine result of step S1 is less than the theoretical deviation, a protrusion is marked on the mounting surface of the model body near the leading edge and / or on the mounting surface of the wing near the trailing edge using a laser marking machine.

3. The method for controlling the installation accuracy of the wing surface of the wind tunnel test model according to claim 1, characterized in that, In step S3, if the detection result is greater than the theoretical deviation, a protrusion is marked on the main body of the angle block mounting surface near the trailing edge and / or on the wing surface near the leading edge using a laser marking machine; if the detection result is less than the theoretical deviation, a protrusion is marked on the main body of the angle block mounting surface near the leading edge and / or on the wing surface near the trailing edge using a laser marking machine.

4. The method for controlling the installation accuracy of the wing surface of a wind tunnel test model according to any one of claims 1-3, characterized in that, In step S1, the angle block is a 0° angle block.

5. The method for controlling the installation accuracy of the wing surface of a wind tunnel test model according to any one of claims 1-3, characterized in that, In step S2, the width of the protrusion is 1 / 10 to 3 / 10 of the width of the mounting surface at its location; in step S3, the width of the protrusion is 1 / 10 to 3 / 10 of the width of the angle block.

6. The method for controlling the installation accuracy of the wing surface of the wind tunnel test model according to claim 5, characterized in that, In step S2, the width of the protrusion is 1 / 5 of the width of the mounting surface at its location; in step S3, the width of the protrusion is 1 / 5 of the width of the angle block.

7. The method for controlling the installation accuracy of the wing surface of a wind tunnel test model according to any one of claims 1-3, characterized in that, After the coordinate measuring machine (CMM) detection in step S1 is qualified, the angle block at the current angle is installed and the feature points of the wing surface are detected. The fluctuation range of the detected feature point data is compared with the fluctuation range of the wing surface profile data detected by the CMM to ensure the repeatability of the wing surface deflection angle.

8. The method for controlling the installation accuracy of the wing surface of a wind tunnel test model according to any one of claims 1-3, characterized in that, In step S2, after marking is completed, the wing surface is subjected to at least three assembly / disassembly operations and at least three feature point detections.

9. The method for controlling the installation accuracy of the wing surface of a wind tunnel test model according to any one of claims 1-3, characterized in that, In step S3, after the marking is completed, the angle block is assembled and disassembled at least three times and the feature point is detected at least three times.

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