Supporting device for increasing scaling ratio of missile wing transonic wind tunnel test model with high aspect ratio

Abstract

The invention belongs to the field of aerospace wind tunnel tests, and discloses a supporting device for increasing the scaling ratio of a transonic wind tunnel test model of a missile wing with a high aspect ratio. The supporting device comprises two supporting blades, an angle changing block, a connecting block and an attack angle adjusting pin. According to the supporting device for increasing the scaling ratio of the high-aspect-ratio missile wing transonic wind tunnel test model, the high-aspect-ratio wind tunnel test model is fixed through the connecting block and the inverted-V-shaped supporting device, and the size of the high-aspect-ratio wind tunnel test model can be increased in an existing wind tunnel; through an attack angle adjusting pin hole formed in the angle changing block, the attack angle changing of the high-aspect-ratio wind tunnel test model is realized. The supporting device for increasing the scale of the high-aspect-ratio missile wing transonic wind tunnel test model improves the accuracy of test data of a high-aspect-ratio wind tunnel test, and has engineering practical value.

Description

Technical Field

[0001] The invention belongs to the field of aerospace wind tunnel tests, and in particular relates to a supporting device for increasing the scale of a large aspect ratio wing transonic wind tunnel test model. Background Art

[0002] Wind tunnel testing is an important means to verify and evaluate the aerodynamic characteristics of aircraft. The accuracy of test data will affect the quality and progress of aircraft development.

[0003] When conducting wind tunnel tests, the wind tunnel test model generally needs to be scaled down due to the size limitation of the wind tunnel test section. When scaling down, the size of the wind tunnel test model should be increased as much as possible while meeting the test requirements. A large wind tunnel test model has obvious advantages: 1. The larger the size of the wind tunnel test model, the more realistically it can simulate the geometric details and small components on the aircraft. The higher the geometric similarity of the wind tunnel test model, the more conducive it is to accurately evaluate the aerodynamic characteristics of the aircraft, which is crucial to the reliability of wind tunnel test data; 2. The larger the wind tunnel test model, the closer the test conditions in the wind tunnel are to the actual flight conditions, which makes it easier to meet the flow similarity and provide more accurate wind tunnel test data; 3. For large aspect ratio wings, since the wing surface is very thin, for the sake of test safety and data validity, the larger the wind tunnel test model, the thicker the wing surface, which is easier to meet the strength requirements.

[0004] In a wind tunnel test, the cross section of the wind tunnel test section is usually square, and the wind tunnel test model is fixed in the wind tunnel test section by a support device. The support forms of the wind tunnel test model generally adopt tail support, abdomen support and back support. When the above support methods are adopted, the wind tunnel test model is generally horizontal to the ground. In order to ensure that the model area has good flow field quality and reduce the interference of the tunnel wall on the aerodynamic characteristics of the wind tunnel test model, it is generally required that the wind tunnel test model has a length of no more than 70% of the width of the wind tunnel test section, that is, the distance between one side of the model and the tunnel wall must be no less than 15% of the width of the test section. For large aspect ratio wind tunnel test models, due to their large length, they are severely restricted by the width or height of the wind tunnel test section, making it difficult to increase the size of large aspect ratio wind tunnel test models. In order to make the large aspect ratio wind tunnel test model as large as possible, it is usually necessary to conduct wind tunnel tests in a larger wind tunnel. However, the size of the wind tunnel is limited by many factors. The larger the wind tunnel size, the higher the construction cost and wind tunnel test cost. Therefore, it is necessary to increase the size of the large aspect ratio wind tunnel test model as much as possible in the existing wind tunnel.

[0005] Currently, there is an urgent need to develop a support device that can increase the scale of the transonic wind tunnel test model of a large aspect ratio wing. Summary of the invention

[0006] Currently, there is an urgent need to develop a support device that can increase the scale of a transonic wind tunnel test model of a large aspect ratio wing to overcome the defects of the prior art.

[0007] The supporting device for increasing the scale of a transonic wind tunnel test model of a high aspect ratio wing of the present invention comprises two supporting blades, an angle-changing block, a connecting block and an angle-of-attack adjustment pin; The vertices of the two supporting blades intersect to form a Λ shape; the foot of one supporting blade is fixed to the bottom wall of the wind tunnel test section by tightening screws, and the angle between the symmetry plane and the bottom wall of the wind tunnel test section is θ1, 75°≤θ1≤85°; the foot of the other supporting blade is fixed to the side wall of the wind tunnel test section by tightening screws, and the angle between the symmetry plane and the side wall of the wind tunnel test section is θ2, 75°≤θ2≤85°; The connecting block is located at the vertices of the two supporting blades and is used to connect the supporting blades and the variable angle block, and the mating surface between the connecting block and the variable angle block is an arc surface; the variable angle block is connected to the test model, and the mating surface between the variable angle block and the test model is a plane; The connecting block is provided with three connecting surfaces, the connecting surfaces on both sides are respectively fixed to two supporting blades, and the connecting surface on the top is connected to the variable angle block; the variable angle block is also provided with M angle of attack adjustment pin holes, and the center lines of each angle of attack adjustment pin hole are distributed in a fan shape and intersect at the angle of attack rotation center of the variable angle block; the connecting block is provided with N positioning pin holes matching the angle of attack adjustment pin holes, M>N; the angle of attack of the test model is adjusted and fixed between the connecting block and the variable angle block by an angle of attack adjustment pin that passes through the angle of attack adjustment pin hole and the positioning pin hole.

[0008] Furthermore, the support blades, angle-changing blocks and connecting blocks are all made of high-strength alloy steel.

[0009] Furthermore, the cross-section of the supporting blade is a symmetrical airfoil with a relative thickness of 10% to 12%. The supporting blade is at the root at the wall of the wind tunnel, and the blade root chord length Cr is the longest. The supporting blade is at the tip close to the test model, and the blade tip chord length Ct is the shortest. The blade root chord length Cr to the blade tip chord length Ct changes linearly, and the root-tip ratio 1≤Cr / Ct≤2; the symmetry plane of the supporting blade is an isosceles trapezoid, and the base angle of the isosceles trapezoid is 180°-δ, and the range of δ is 90°~105°.

[0010] Furthermore, reinforcing ribs are provided on the foot of the support blade, and two reinforcing ribs are provided on each support blade to increase the rigidity and strength of the support blade. The thickness of the reinforcing ribs is h≤0.5b, where b is the maximum thickness of the support blade.

[0011] Furthermore, the variable angle block enables the test model's angle of attack adjustment range to be -20°~20°.

[0012] Furthermore, the angle of attack adjustment pin is a cylindrical pin with a diameter of 10 mm, and the length L of the angle of attack adjustment pin ranges from 30 mm to 100 mm.

[0013] The supporting device for increasing the scale of a transonic wind tunnel test model of a large aspect ratio missile wing of the present invention fixes the large aspect ratio wind tunnel test model through a connecting block and a Λ-shaped supporting device, and can increase the size of the large aspect ratio wind tunnel test model in an existing wind tunnel; and the angle of attack adjustment pin hole provided on the angle-changing block can realize the variable angle of attack of the large aspect ratio wind tunnel test model. The supporting device for increasing the scale of a transonic wind tunnel test model of a large aspect ratio missile wing of the present invention improves the accuracy of test data of a large aspect ratio wind tunnel test, and has engineering practical value. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a structural schematic diagram of a support device for increasing the scale of a transonic wind tunnel test model of a high aspect ratio wing according to the present invention; Figure 2 It is a schematic diagram of the connection between the supporting blade and the wall; Figure 3 It is a schematic diagram of the shape of the supporting blade; Figure 4 It is a schematic diagram of the reinforcement rib (partial enlarged view of A); Figure 5 A wind tunnel installation schematic diagram of a support device for increasing the scale of a transonic wind tunnel test model of a high aspect ratio wing according to the present invention; Figure 6 Schematic diagram of the angle of attack adjustment method of the variable angle block.

[0015] In the figure, 1. Test model; 2. Support blade; 3. Variable angle block; 4. Reinforcement rib; 5. Attack angle adjustment pin; 6. Bottom wall of wind tunnel test section; 7. Side wall of wind tunnel test section; 8. Attack angle rotation center; 9. Connection block; 201. Positioning pin hole Ⅰ; 202. Positioning pin hole Ⅱ; 301. Angle of attack adjustment pin hole I; 302. Angle of attack adjustment pin hole II; 303. Angle of attack adjustment pin hole III; 304. Angle of attack adjustment pin hole IV; 305. Angle of attack adjustment pin hole V. DETAILED DESCRIPTION

[0016] The present invention is described in detail below with reference to the accompanying drawings and embodiments.

[0017] like Figure 1~Figure 4 As shown, the supporting device for increasing the scale of the transonic wind tunnel test model of a large aspect ratio wing of the present invention comprises two supporting blades 2, an angle-changing block 3, a connecting block 9 and an angle-of-attack adjustment pin; The vertices of the two support blades 2 intersect to form a Λ shape; the foot of one support blade 2 is fixed to the bottom wall 6 of the wind tunnel test section by tightening screws, and the angle between the symmetry plane and the bottom wall 6 of the wind tunnel test section is θ1, 75°≤θ1≤85°; the foot of the other support blade 2 is fixed to the side wall 7 of the wind tunnel test section by tightening screws, and the angle between the symmetry plane and the side wall 7 of the wind tunnel test section is θ2, 75°≤θ2≤85°; The connecting block 9 is located at the vertices of the two supporting blades 2, and is used to connect the supporting blades 2 and the angle-changing block 3. The mating surface between the connecting block 9 and the angle-changing block 3 is an arc surface. The angle-changing block 3 is connected to the test model 1, and the mating surface between the angle-changing block 3 and the test model 1 is a plane. The connecting block 9 is provided with three connecting surfaces, the connecting surfaces on both sides are respectively fixed to the two supporting blades 2, and the connecting surface on the top is connected to the variable angle block 3; the variable angle block 3 is also provided with M angle of attack adjustment pin holes, and the center lines of each angle of attack adjustment pin hole are distributed in a fan shape and intersect at the angle of attack rotation center 8 of the variable angle block 3; the connecting block 9 is provided with N positioning pin holes matching the angle of attack adjustment pin holes, M>N; the angle of attack of the test model 1 is adjusted and fixed between the connecting block 9 and the variable angle block 3 by an angle of attack adjustment pin 5 that passes through the angle of attack adjustment pin hole and the positioning pin hole.

[0018] Furthermore, the support blades 2, the angle-changing blocks 3 and the connecting blocks 9 are all made of high-strength alloy steel.

[0019] Furthermore, the cross-section of the support blade 2 is a symmetrical airfoil with a relative thickness of 10% to 12%. The support blade 2 is at the root at the wall of the wind tunnel, and the blade root chord length Cr is the longest. The support blade 2 is at the tip near the test model 1, and the blade tip chord length Ct is the shortest. The blade root chord length Cr to the blade tip chord length Ct changes linearly, and the root-tip ratio 1≤Cr / Ct≤2; the symmetry plane of the support blade 2 is an isosceles trapezoid, and the base angle of the isosceles trapezoid is 180°-δ, and the range of δ is 90°~105°.

[0020] Furthermore, reinforcing ribs 4 are provided on the foot of the support blade 2 , and two reinforcing ribs 4 are provided on each support blade 2 to increase the rigidity and strength of the support blade 2 . The thickness of the reinforcing ribs 4 is h≤0.5b, where b is the maximum thickness of the support blade 2 .

[0021] Furthermore, the angle-variable block 3 enables the test model 1 to adjust the angle of attack in the range of -20° to 20°.

[0022] Furthermore, the angle of attack adjustment pin is a cylindrical pin with a diameter of 10 mm, and the length L of the angle of attack adjustment pin ranges from 30 mm to 100 mm.

[0023] Example 1: Figure 5As shown in the figure, along the heading, the test model 1 is at an angle of 45° with the horizontal line of the wind tunnel, so that the maximum length of the test model 1 is located at the diagonal section of the wind tunnel test section. According to the Pythagorean theorem, the diagonal length of the wind tunnel is equal to the width. times (i.e., about 1.414 times), the length of the test model 1 can reach 1.414 times that of the traditional horizontal method, thereby increasing the size of the test model 1; the test model 1 is connected to the variable angle block 3 by tightening screws, the variable angle block 3 is connected to the connecting block 9, and the connecting block 9 is modified along the flow direction to reduce support interference; the connecting block 9 is fixed to the wind tunnel test section by two Λ-shaped support blades 2, one support blade 2 is fixed to the bottom wall 6 of the test section by tightening screws, and the angle between the symmetry plane and the bottom wall 6 of the test section is 75°≤θ≤85°, and the other support blade 2 is fixed to the side wall 7 of the wind tunnel test section by tightening screws, and the angle between the symmetry plane and the side wall 7 of the wind tunnel test section is 75° ≤θ≤85°; the cross section of the support blade 2 is a symmetrical airfoil with a relative thickness of 10%~12%; the support blade 2 is the blade root at the wall of the wind tunnel, and the blade root chord length Cr is the longest; the support blade 2 is the blade tip near the test model 1, and the blade tip chord length Ct is the shortest; the blade root chord length Cr to the blade tip chord length Ct changes linearly, and the root tip ratio 1≤Cr / Ct≤2; the symmetry plane of the support blade 2 is an isosceles trapezoid, and the base angle of the isosceles trapezoid is 180°-δ, and the range of δ is 90°~105°; reinforcing ribs 4 are arranged on the foot of the support blade 2, and two reinforcing ribs 4 are arranged on each support blade 2 to increase the rigidity and strength of the support blade 2, and the thickness of the reinforcing rib 4 is h≤0.5b, where b is the maximum thickness of the support blade 2.

[0024] Embodiment 2: Based on embodiment 1, Figure 6 As shown, taking M=5, the sequence of the angle of attack adjustment pin holes is angle of attack adjustment pin hole I301, angle of attack adjustment pin hole II302, angle of attack adjustment pin hole III303, angle of attack adjustment pin hole IV304 and angle of attack adjustment pin hole V305, and the angle between adjacent angle of attack adjustment pin holes is 10°; N=2, the sequence of the positioning pin holes is positioning pin hole I201 and positioning pin hole II202, and similarly, the angle between the positioning pin holes is 10°; When the positioning pin hole II 202 cooperates with the angle of attack adjustment pin hole III 303, the angle of attack of the test model 1 is 0°; when the positioning pin hole II 202 cooperates with the angle of attack adjustment pin hole 302 II, the model angle of attack is 10°, and so on. The angle of attack of the test model 1 can be changed, and the angle of attack change range is -20°~20°, so as to carry out wind tunnel tests at different angles of attack.

[0025] Although the embodiments of the present invention have been disclosed as above, they are not limited to the applications listed in the specification and implementation modes. For those familiar with the art, all features disclosed in the present invention, or steps in all methods or processes disclosed, except for mutually exclusive features and / or steps, can be combined in any way without departing from the principles of the present invention. The present invention is not limited to the specific details and illustrations shown and described herein.

Claims

1. A support device for increasing the scale of a transonic wind tunnel test model of a high aspect ratio wing, characterized in that: The supporting device comprises two supporting blades (2), an angle-changing block (3), a connecting block (9) and an angle-of-attack adjustment pin; The vertices of the two support blades (2) intersect to form a Λ shape; the foot of one support blade (2) is fixed to the bottom wall surface (6) of the wind tunnel test section by means of tightening screws, and the angle between the symmetry plane and the bottom wall surface (6) of the wind tunnel test section is θ1, 75°≤θ1≤85°; the foot of the other support blade (2) is fixed to the side wall surface (7) of the wind tunnel test section by means of tightening screws, and the angle between the symmetry plane and the side wall surface (7) of the wind tunnel test section is θ2, 75°≤θ2≤85°; The connecting block (9) is located at the vertices of the two supporting blades (2) and is used to connect the supporting blades (2) and the angle-changing block (3); the mating surfaces of the connecting block (9) and the angle-changing block (3) are arc surfaces; the angle-changing block (3) is connected to the test model (1); the mating surfaces of the angle-changing block (3) and the test model (1) are plane surfaces; The connection block (9) is provided with three connection surfaces, the connection surfaces on both sides are respectively fixed to the two supporting blades (2), and the connection surface on the top is connected to the variable angle block (3); the variable angle block (3) is also provided with M angle-of-attack adjustment pin holes, the center lines of the angle-of-attack adjustment pin holes are distributed in a fan shape and intersect at the angle-of-attack rotation center (8) of the variable angle block (3); the connection block (9) is provided with N positioning pin holes matching the angle-of-attack adjustment pin holes, M>N; the angle of attack of the test model (1) is adjusted and fixed between the connection block (9) and the variable angle block (3) by an angle-of-attack adjustment pin (5) penetrating the angle-of-attack adjustment pin hole and the positioning pin hole.

2. The supporting device for increasing the scale of a transonic wind tunnel test model of a high aspect ratio wing according to claim 1 is characterized in that: The support blades (2), the angle-changing blocks (3) and the connecting blocks (9) are all made of high-strength alloy steel.

3. The supporting device for increasing the scale of a transonic wind tunnel test model of a high aspect ratio wing according to claim 1 is characterized in that: The cross-section of the support blade (2) is a symmetrical airfoil with a relative thickness of 10% to 12%. The support blade (2) is at the wind tunnel wall surface as a blade root, and the blade root chord length Cr is the longest. The support blade (2) is at the tip close to the test model (1), and the blade tip chord length Ct is the shortest. The blade root chord length Cr to the blade tip chord length Ct varies linearly, and the root-tip ratio 1≤Cr / Ct≤2. The symmetry plane of the support blade (2) is an isosceles trapezoid, and the base angle of the isosceles trapezoid is 180°-δ, and the range of δ is 90° to 105°.

4. The supporting device for increasing the scale of a transonic wind tunnel test model of a high aspect ratio wing according to claim 1 is characterized in that: A reinforcing rib (4) is provided on the foot of the support blade (2), and two reinforcing ribs (4) are provided on each support blade (2) to increase the rigidity and strength of the support blade (2), and the thickness of the reinforcing rib (4) is h≤0.5b, where b is the maximum thickness of the support blade (2).

5. The supporting device for increasing the scale of a transonic wind tunnel test model of a high aspect ratio wing according to claim 1 is characterized in that: The variable angle block (3) enables the test model (1) to have an angle of attack adjustment range of -20° to 20°.

6. The supporting device for increasing the scale of a transonic wind tunnel test model of a high aspect ratio wing according to claim 1 is characterized in that: The angle-of-attack adjustment pin is a column pin with a diameter of 10 mm, and the length L of the angle-of-attack adjustment pin ranges from 30 mm to 100 mm.

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