CN118010304A - A frame structure and processing method of an all-metal pressure wind tunnel model - Google Patents

A frame structure and processing method of an all-metal pressure wind tunnel model Download PDF

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Publication number
CN118010304A
CN118010304A CN202410060628.4A CN202410060628A CN118010304A CN 118010304 A CN118010304 A CN 118010304A CN 202410060628 A CN202410060628 A CN 202410060628A CN 118010304 A CN118010304 A CN 118010304A
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China
Prior art keywords
main beam
model
wind tunnel
support rod
splicing
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CN202410060628.4A
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Inventor
何小明
任家昊
谭慧俊
王子运
王德鹏
李东坡
柯玉祥
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Avic Chengdu Uav System Co ltd
Nanjing University of Aeronautics and Astronautics
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Avic Chengdu Uav System Co ltd
Nanjing University of Aeronautics and Astronautics
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Application filed by Avic Chengdu Uav System Co ltd, Nanjing University of Aeronautics and Astronautics filed Critical Avic Chengdu Uav System Co ltd
Priority to CN202410060628.4A priority Critical patent/CN118010304A/en
Publication of CN118010304A publication Critical patent/CN118010304A/en
Pending legal-status Critical Current

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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
    • G01M9/08—Aerodynamic models
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
    • G01M9/06—Measuring arrangements specially adapted for aerodynamic testing

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • General Physics & Mathematics (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)

Abstract

The invention discloses a frame type structure of an all-metal pressure measurement wind tunnel model and a processing method, wherein the frame type structure comprises a machine body, a main beam positioned in the machine body and wings positioned at two sides of the machine body, the machine body and the wings are formed by splicing a plurality of spliced plates, the spliced plates are fixedly connected with the main beam, and adjacent spliced plates are fixedly connected; the wing is also connected with the main beam through a wing supporting rod positioned in the wing, the wing supporting rod penetrates through the main beam, and the central shaft of the wing supporting rod is perpendicular to the central shaft of the main beam. The frame type structure of the whole model is formed by splicing the spliced plates, so that the time for processing the model, required materials and cost are effectively reduced; meanwhile, by adopting the spliced structure, the spliced plate has small volume, and is convenient for transporting and installing the model; if the model is damaged, only the spliced plate of the part needs to be replaced, so that the maintenance and repair are easy; and can design a plurality of concatenation plates in a flexible way according to different experimental requirements, improve the adaptation degree of model.

Description

Frame type structure of all-metal pressure measurement wind tunnel model and processing method
Technical Field
The invention relates to the technical field of experimental model design, in particular to a frame structure of an all-metal pressure measurement wind tunnel model and a processing method.
Background
In the field of wind tunnel experiments, the current model manufacturing technology has reached a very high level, and as the building scale of wind tunnels is larger and larger, for example, a low-speed supercharging wind tunnel FL-9, a continuous transonic wind tunnel FL-62 and a closed-loop reflux low-speed wind tunnel FL-10, the size of an experimental model is larger and larger. In the state army standard, metal materials such as aluminum metal or steel are required to be selected for the model processing materials, so that the design and processing mode of the model and the use amount of the materials directly influence the experiment cost. In the field of traditional large-scale model processing, a mode of numerical control processing is generally adopted for a whole metal material. This way of processing has some non-negligible problems to some extent. First, finding a monolithic metallic material of sufficiently large size can be challenging, limiting the flexibility of the process. Secondly, the use of integral materials for the hollowing out process not only increases the difficulty of the process, but also results in a waste of a large amount of materials, and excessive machining allowance, which constitutes a serious challenge for resource utilization and cost effectiveness.
Disclosure of Invention
The invention aims to: aiming at the defects of large processing difficulty, much material waste and high cost of the whole metal material, the invention provides a frame type structure of an all-metal pressure measuring wind tunnel model and a processing method thereof.
The technical scheme is as follows: in order to solve the problems, the invention adopts a frame type structure of an all-metal pressure measurement wind tunnel model, which comprises a fuselage, a main beam positioned in the fuselage and wings positioned at two sides of the fuselage, wherein the fuselage and the wings are formed by splicing a plurality of spliced plates, the spliced plates are fixedly connected with the main beam, and adjacent spliced plates are fixedly connected; the wing is also connected with the main beam through a wing supporting rod positioned in the wing, the wing supporting rod penetrates through the main beam, and the central shaft of the wing supporting rod is perpendicular to the central shaft of the main beam.
Further, a plurality of first connecting plates are arranged on the main beam, a second connecting plate is arranged on the spliced plate, screw holes corresponding to the positions are formed in the first connecting plates and the second connecting plates, and bolts and nuts are arranged in the screw holes to fixedly connect the main beam with the spliced plate.
Further, four first connecting plates located on the same plane are arranged at the same axial position of the main beam, and the plane where the first connecting plates are located is perpendicular to the central axis of the main beam.
Further, a third connecting plate is further arranged on the spliced plate, a screw hole is formed in the third connecting plate, and bolts and nuts are arranged in the screw hole to fixedly connect the adjacent spliced plates.
Further, an opening for reducing the weight of the main beam is formed in the main beam.
Further, the wind tunnel main support comprises a main support rod connected with the main beam, and the main support rod is fixed in the wind tunnel.
Further, the device also comprises a diagonal brace, one end of the diagonal brace is hinged with the main girder, the other end of the diagonal brace is hinged with the main brace, and the main brace and the diagonal brace are matched to change the attack angle and sideslip angle of the model.
Further, the diagonal bracing bar includes one end and girder articulated first linkage segment and one end and main tributary vaulting pole articulated second linkage segment, first linkage segment, second linkage segment are connected through adjusting screw, the adjusting screw both ends are equipped with opposite direction's screw thread, are equipped with the screw that matches with adjusting screw on first linkage segment, the second linkage segment, change the distance between first linkage segment, the second linkage segment through rotatory adjusting screw.
Furthermore, the fuselage and the wing are made of metal materials.
The invention also provides a processing method of the frame structure of the all-metal pressure measurement wind tunnel model, which comprises the following steps:
Step 1, dividing the overall shape of a model by adopting a gridding dividing method, and dividing a machine body into a plurality of spliced plates;
step 2, performing technological processing to obtain spliced plates, splicing the spliced plates in sequence from front to back and from bottom to top, and fixedly connecting the spliced plates with the main beam;
step 3, fixedly connecting adjacent spliced plates;
Step 4, fixedly connecting the wing with the main beam to finish model splicing;
and 5, carrying out surface treatment on the model to enable all the spliced plates to be connected smoothly.
The beneficial effects are that: compared with the prior art, the invention has the remarkable advantages that the frame structure of the whole model is formed by splicing the spliced plates, so that the time for processing the model, required materials and cost are effectively reduced; meanwhile, by adopting the spliced structure, the spliced plate is small in size, easy to process and convenient for transportation and installation of the model, and deformation caused by release of internal stress can be avoided due to the common material size in the market; the outer side profile of the spliced integral model subjected to surface treatment is as smooth as that of the prior method, so that the experimental requirement is met; if the model is damaged, only the spliced plate of the part needs to be replaced, so that the maintenance and repair are easy; and can design a plurality of concatenation plates in a flexible way according to different experimental requirements, improve the adaptation degree of model.
Drawings
FIG. 1 is a schematic view of the overall structure of a frame structure of the present invention;
FIG. 2 is a top view of a frame structure of the present invention;
FIG. 3 is a schematic view of the main beam structure of the present invention;
FIG. 4 is a schematic view of a main beam and splice plate splice according to the present invention;
FIG. 5 is a schematic view of the structure of a spliced plate A of the invention;
FIG. 6 is a schematic view of a spliced plate B according to the present invention;
FIG. 7 is a schematic view of the structure of a spliced plate C of the invention;
FIG. 8 is a schematic view of a spliced plate D according to the present invention;
FIG. 9 is a schematic view of a diagonal brace according to the present invention;
FIG. 10 is a diagram illustrating meshing of a model in accordance with the present invention.
Detailed Description
As shown in fig. 1 and 2, the frame structure of the all-metal pressure measurement wind tunnel model in this embodiment includes a fuselage 1, a main beam 2 located in the fuselage 1, and wings 5 located at two sides of the fuselage 1, where the fuselage 1 and the wings 5 are formed by splicing a plurality of spliced plates 7. As shown in fig. 3, twenty first connection plates 9 are provided on the main beam 2, and four first connection plates 9 respectively located on the upper, lower, left, and right end surfaces and on the same plane are provided on the same axial position. As shown in fig. 4 to 8, the splicing plate 7 is provided with a second connecting plate 10, and the first connecting plate 9 and the second connecting plate 10 are provided with screw holes corresponding to each other, and bolts and nuts are installed in the screw holes to fixedly connect the main beam 2 with the splicing plate 7. The spliced plate 7 is also provided with a third connecting plate 11, the third connecting plate 11 is provided with a screw hole, and bolts and nuts are arranged in the screw hole to fixedly connect the adjacent spliced plates 7. Besides the splicing mode, other modes such as flanges, tenon rabbets and the like can be adopted to splice the spliced plates with the main beam and the spliced plates. The connecting structure of each part only plays a role in fixing, does not bear external stress, and ensures the integral strength of the machine body.
Two wing support rods 6 are further arranged in the wing 5, two mounting holes are formed in the middle of the main beam 2, the wing support rods 6 are mounted in the mounting holes, and the central shaft of each wing support rod 6 is perpendicular to the central shaft of the main beam 2. The wing 5 is supported by the wing support rods 6, and meanwhile, the connection strength of the wing 5 and the main beam 2 is further enhanced. Under the condition of ensuring the bearing strength, the girder 2 is provided with a plurality of holes 21, and the holes 21 can lighten the girder weight, save manufacturing materials and save manufacturing cost.
The main girder 2 is also hinged with a main supporting rod 3 and two inclined supporting rods 4, and the main supporting rod 3 is hinged at the middle part of the main girder 2 to support and fix the model in the wind tunnel. As shown in fig. 9, the diagonal brace 4 includes a first connection section with one end hinged to the main girder 2 and a second connection section with one end hinged to the main brace 3, and the first connection section and the second connection section are connected through an adjusting screw 8. Screw threads with opposite directions are arranged at two ends of the adjusting screw rod 8, screw holes matched with the adjusting screw rod 8 are arranged on the first connecting section and the second connecting section, and the distance between the first connecting section and the second connecting section can be changed by rotating the adjusting screw rod 8. The hinge points of the two diagonal support rods 4 and the main beam 2 are respectively positioned at the front side and the rear side of the main beam. The main supporting rod 3 and the diagonal supporting rod 4 cooperate to support the model and change the attack angle and sideslip angle of the model.
The implementation also provides a processing method of the frame structure of the all-metal pressure measurement wind tunnel model, which comprises the following steps:
step 1, as shown in fig. 10, a gridding dividing method is adopted to divide the overall shape of the model, the model is firstly cut through a vertical plane, then the cut segments are divided into four spliced plates, namely an upper block, a lower block, a left block and a right block, the model is finely divided, and the machine body 1 is divided into a plurality of spliced plates 7.
And 2, carrying out technological processing to obtain spliced plates 7, wherein the thickness of each spliced plate 7 is not less than 200mm. The splicing plates 7 are spliced in sequence from front to back and from bottom to top and are fixedly connected with the main beam 2.
And 3, fixedly connecting the adjacent spliced plates 7.
And 4, fixedly connecting the wing 5 with the main beam 2 to finish model splicing.
And 5, carrying out surface treatment on the model to enable each spliced plate 7 to be connected smoothly, and coating or coating the surface according to experimental requirements to improve the surface quality.
Before the model is used for experiments, functional tests of the model are firstly carried out, whether the model is firmly spliced or not is checked, and whether all functional indexes meet experimental requirements or not is checked. The total weight of the model in the embodiment is about 500kg, and the model is made of aluminum metal materials, so that the initial material of the model is reduced by 1/2 compared with the prior whole metal processing, the overall cost of the model processing is about 1/2 of that of the prior method, and the time, required material and cost of the model processing are effectively reduced. Meanwhile, by adopting the spliced structure, the spliced plate is small in size, easy to process and convenient for transportation and installation of the model, and deformation caused by release of internal stress can be avoided due to the common material size in the market; the outer side profile of the spliced integral model subjected to surface treatment is as smooth as that of the prior method, so that the experimental requirement is met; if the model is damaged, only the spliced plate of the part needs to be replaced, so that the maintenance and repair are easy; and can design a plurality of concatenation plates in a flexible way according to different experimental requirements, improve the adaptation degree of model.

Claims (10)

1.一种全金属测压风洞模型的框架式结构，包括机身(1)、位于机身(1)内的主梁(2)、位于机身(1)两侧的机翼(5)，其特征在于，所述机身(1)和机翼(5)均由若干拼接板块(7)拼接而成，所述拼接板块(7)与主梁(2)固定连接，相邻拼接板块(7)之间固定连接；所述机翼(5)还通过位于机翼(5)内的机翼支撑杆(6)与主梁(2)连接，所述机翼支撑杆(6)穿过主梁且机翼支撑杆(6)中心轴与主梁(2)中心轴垂直。1. A frame structure of an all-metal pressure wind tunnel model, comprising a fuselage (1), a main beam (2) located in the fuselage (1), and wings (5) located on both sides of the fuselage (1), characterized in that the fuselage (1) and the wings (5) are both spliced together by a plurality of splicing plates (7), the splicing plates (7) are fixedly connected to the main beam (2), and adjacent splicing plates (7) are fixedly connected to each other; the wings (5) are also connected to the main beam (2) through a wing support rod (6) located in the wing (5), the wing support rod (6) passes through the main beam and the central axis of the wing support rod (6) is perpendicular to the central axis of the main beam (2). 2.如权利要求1所述的全金属测压风洞模型的框架式结构，其特征在于，所述主梁(2)上设有若干第一连接板(9)，所述拼接板块(7)上设有第二连接板(10)，所述第一连接板(9)和第二连接板(10)上开有位置对应的螺孔，螺栓和螺母安装于螺孔内使主梁(2)与拼接板块(7)固定连接。2. The frame structure of the all-metal pressure wind tunnel model as described in claim 1 is characterized in that a plurality of first connecting plates (9) are provided on the main beam (2), and a second connecting plate (10) is provided on the splicing plate (7), and corresponding screw holes are opened on the first connecting plate (9) and the second connecting plate (10), and bolts and nuts are installed in the screw holes to fix the main beam (2) and the splicing plate (7). 3.如权利要求2所述的全金属测压风洞模型的框架式结构，其特征在于，所述主梁(2)的同一轴向位置上设有四块位于同一平面上的第一连接板(9)，所述第一连接板(9)所在平面与主梁(2)中心轴垂直。3. The frame structure of the all-metal pressure wind tunnel model as described in claim 2 is characterized in that four first connecting plates (9) located on the same plane are provided at the same axial position of the main beam (2), and the plane where the first connecting plates (9) are located is perpendicular to the central axis of the main beam (2). 4.如权利要求3所述的全金属测压风洞模型的框架式结构，其特征在于，所述拼接板块(7)上还设有第三连接板(11)，所述第三连接板(11)上设有螺孔，螺栓和螺母安装于螺孔内使相邻拼接板块(7)固定连接。4. The frame structure of the all-metal pressure wind tunnel model as described in claim 3 is characterized in that a third connecting plate (11) is also provided on the splicing plate (7), and screw holes are provided on the third connecting plate (11), and bolts and nuts are installed in the screw holes to fix the adjacent splicing plates (7) in connection. 5.如权利要求1所述的全金属测压风洞模型的框架式结构，其特征在于，所述主梁(2)上开有用于减轻主梁重量的开孔(21)。5. The frame structure of the all-metal pressure wind tunnel model according to claim 1 is characterized in that the main beam (2) is provided with an opening (21) for reducing the weight of the main beam. 6.如权利要求1所述的全金属测压风洞模型的框架式结构，其特征在于，还包括与主梁(2)连接的主支撑杆(3)，所述主支撑杆(3)固定于风洞内。6. The frame structure of the all-metal pressure wind tunnel model according to claim 1 is characterized in that it also includes a main support rod (3) connected to the main beam (2), and the main support rod (3) is fixed in the wind tunnel. 7.如权利要求6所述的全金属测压风洞模型的框架式结构，其特征在于，还包括斜支撑杆(4)，所述斜支撑杆(4)一端与主梁(2)铰接，斜支撑杆(4)另一端与主支撑杆(3)铰接，所述主支撑杆(3)和斜支撑杆(4)配合以改变模型的迎角和侧滑角。7. The frame structure of the all-metal pressure wind tunnel model as described in claim 6 is characterized in that it also includes an oblique support rod (4), one end of the oblique support rod (4) is hinged to the main beam (2), and the other end of the oblique support rod (4) is hinged to the main support rod (3), and the main support rod (3) and the oblique support rod (4) cooperate to change the angle of attack and sideslip angle of the model. 8.如权利要求7所述的全金属测压风洞模型的框架式结构，其特征在于，所述斜支撑杆(4)包括一端与主梁(2)铰接的第一连接段和一端与主支撑杆(3)铰接的第二连接段，所述第一连接段、第二连接段通过调节螺杆(8)连接，所述调节螺杆(8)两端设有方向相反的螺纹，第一连接段、第二连接段上设有与调节螺杆(8)匹配的螺孔，通过旋转调节螺杆(8)改变第一连接段、第二连接段之间的距离。8. The frame structure of the all-metal pressure wind tunnel model as described in claim 7 is characterized in that the inclined support rod (4) includes a first connecting section hinged to the main beam (2) at one end and a second connecting section hinged to the main support rod (3) at one end, the first connecting section and the second connecting section are connected by an adjusting screw (8), and the two ends of the adjusting screw (8) are provided with threads in opposite directions, and the first connecting section and the second connecting section are provided with screw holes matching the adjusting screw (8), and the distance between the first connecting section and the second connecting section is changed by rotating the adjusting screw (8). 9.如权利要求1所述的全金属测压风洞模型的框架式结构，其特征在于，所述机身(1)、机翼(5)采用金属材料制成。9. The frame structure of the all-metal pressure wind tunnel model according to claim 1, characterized in that the fuselage (1) and the wings (5) are made of metal materials. 10.一种权利要求1-9任一项所述全金属测压风洞模型的框架式结构的加工方法，其特征在于，包括以下步骤：10. A method for processing the frame structure of the all-metal pressure wind tunnel model according to any one of claims 1 to 9, characterized in that it comprises the following steps: 步骤1、采用网格化的划分方法将模型整体形状进行划分，将机身(1)划分为若干拼接板块(7)；Step 1: Using a gridding method to divide the overall shape of the model, the fuselage (1) is divided into a plurality of splicing panels (7); 步骤2、进行工艺加工得到拼接板块(7)，将拼接板块(7)按从前往后、从下至上的顺序拼接并与主梁(2)固定连接；Step 2, performing processing to obtain a splicing plate (7), splicing the splicing plate (7) in a sequence from front to back and from bottom to top and fixing the splicing plate (7) to the main beam (2); 步骤3、将相邻的拼接板块(7)固定连接；Step 3, fixing and connecting adjacent splicing panels (7); 步骤4、将机翼(5)与主梁(2)固定连接，完成模型拼接；Step 4: Fix the wing (5) and the main beam (2) to complete the model assembly; 步骤5、对模型进行表面处理，使各拼接板块(7)平滑连接。Step 5: Surface treatment is performed on the model to ensure smooth connection of each splicing plate (7).
CN202410060628.4A 2024-01-16 2024-01-16 A frame structure and processing method of an all-metal pressure wind tunnel model Pending CN118010304A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202410060628.4A CN118010304A (en) 2024-01-16 2024-01-16 A frame structure and processing method of an all-metal pressure wind tunnel model

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202410060628.4A CN118010304A (en) 2024-01-16 2024-01-16 A frame structure and processing method of an all-metal pressure wind tunnel model

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CN118010304A true CN118010304A (en) 2024-05-10

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