A tool calibration structure and usage method for a dual-balance measurement system

Abstract

The present invention provides a tool calibration structure and method of use for a dual-balance measurement system, which relates to the technical field of aerodynamic characteristic measurement in wind tunnel tests, and includes a first-level tool and a second-level tool arranged in parallel, wherein the first-level tool is equipped with a first-level aircraft, and the second-level tool is equipped with a second-level aircraft, and the first-level tool and the second-level tool are rotatably connected on the same side by an adjustable connecting rod, and the relative roll angles of the first-level aircraft and the second-level aircraft are adjusted by the adjustable connecting rods on different sides. The present invention connects the first-level tool and the second-level tool in parallel with two left and right adjustable connecting rods, which can effectively reduce the relative roll angle error of the first-level and second-level aircraft of a backpack-type parallel structure layout aircraft. At the same time, compared with the existing technology, this tool structure can achieve synchronous adjustment of the roll angles of the two aircraft, simplifying the aircraft roll angle adjustment process. At the same time, the structure is easy to process and install, and is suitable for the test scenario of aerodynamic characteristic measurement of two aircraft in a wind tunnel test.

Description

Technical Field

[0001] The invention relates to the technical field of aerodynamic characteristic measurement of wind tunnel tests, and in particular to a tooling calibration structure of a double-balance measurement system. Background Art

[0002] Wind tunnel testing is a key method for simulating the aerodynamic characteristics of spacecraft on the ground, and a wind tunnel balance is the primary instrument for measuring the aerodynamic loads acting on the model during wind tunnel testing. A wind tunnel balance can directly measure the forces and moments acting on a spacecraft in the air, providing crucial data support for research on a wide range of aspects, including flight angles, streamlined design, and the effects of airflow on flight control.

[0003] In traditional testing methods, wind tunnel tests only use one balance to measure the aerodynamic data of a single component. However, with the continuous development of aerospace technology, new types of aircraft are being developed one after another, such as multi-boost stage rockets, two-stage orbital vehicles, etc., which require simultaneous aerodynamic measurement of multiple components of the aircraft. The traditional single balance measurement method can no longer meet the high-precision measurement requirements of certain models, so the dual balance measurement system came into being.

[0004] At present, piggyback parallel structure layout aircraft are a common new type of aircraft, in which the first and second stage aircraft are arranged up and down. In the corresponding wind tunnel test, the first and second stage aircraft are fixedly connected by two independent balance-strut structures. During the model installation process, the two aircraft are installed independently and both comply with the requirement that the model roll angle is less than ±3'. Since the two aircraft are independent of each other, there is no unified standard for their relative positions. Although the absolute roll angles of the two (relative to the quadrant) meet the requirement of less than ±3', the corresponding relative roll angles may bring an error of 6' (such as the roll angle of the first stage aircraft is -3' roll angle, and the roll angle of the second stage aircraft is +3' roll angle). Considering that the existing piggyback parallel structure aircraft have a large wingspan and a complex external structure, they are more sensitive to changes in the relative position between the first and second stage aircraft. Therefore, the relative roll angle error of 6' between the aircraft may cause a large change in aerodynamic characteristics, thereby affecting the test results. At the same time, in the current roll angle adjustment method, the initial roll angle of the model is first measured using a quadrant, and then a small weight impact load (such as a rubber hammer) is used to drive the model to rotate. Since the impact load is uncontrollable and mainly depends on the operating experience of the installer, it places higher requirements on the test personnel. Summary of the Invention

[0005] The purpose of the present invention is to provide a tooling calibration structure for a dual-balance measurement system that can effectively reduce the relative roll angle error of the first and second stage aircraft in a piggyback parallel structure layout, and can achieve synchronous adjustment of the roll angles of the two aircraft, thereby simplifying the aircraft roll angle adjustment process.

[0006] The present invention provides a tooling calibration structure for a dual-balance measurement system, comprising a first-level tooling and a second-level tooling arranged in parallel, wherein the first-level tooling is equipped with a first-level aircraft, and the second-level tooling is equipped with a second-level aircraft, and the first-level tooling and the second-level tooling are rotatably connected on the same side via an adjustable connecting rod, and the relative roll angle of the first-level aircraft and the second-level aircraft is adjusted via the adjustable connecting rods on different sides.

[0007] Furthermore, the adjustable connecting rod includes tooling connection blocks at both ends and a top screw with an adjustable distance located between the two tooling connection blocks.

[0008] Furthermore, the circumferential surfaces at both ends of the top screw are respectively provided with threaded portions in opposite directions, and the tool connection block is provided with a threaded hole that cooperates with the top screw.

[0009] Furthermore, the top screw is provided with a cylindrical fitting section, and the tool connection block is provided with a circular hole that cooperates with the cylindrical fitting section. The cylindrical fitting section and the threaded portion form a stepped shaft, and the threaded hole and the circular hole form a stepped hole.

[0010] Furthermore, the middle portion of the top screw is a multi-faceted structure.

[0011] Furthermore, a first-level fitting hole is axially provided on the first-level tooling, and the first-level aircraft is connected to the first-level tooling through the first-level fitting hole. A second-level fitting hole is axially provided on the second-level tooling, and the second-level aircraft is connected to the second-level tooling through the second-level fitting hole.

[0012] Furthermore, grooves are respectively provided on both side walls of the first-level tooling and the second-level tooling, and the tooling connecting blocks are rotatably embedded in the grooves.

[0013] Furthermore, the end of the first-stage aircraft away from the first-stage tooling is connected to the first-stage support rod, and the end of the second-stage aircraft away from the second-stage tooling is connected to the second-stage support rod.

[0014] The present invention also provides a method for using a tooling calibration structure, comprising the following steps: S1, calibrating the initial roll angles of a first-stage aircraft and a second-stage aircraft; S2, assembling the first-stage aircraft and the first-stage tooling, leveling the roll angle of the first-stage aircraft model, and fixing it; S3, adjusting the length of a first adjustable connecting rod on one side to be roughly equal to the distance between the first-stage aircraft and the second-stage aircraft; S4, assembling the second-stage aircraft and the second-stage tooling, adjusting the length of the first adjustable connecting rod according to the distance between the first-stage aircraft and the second-stage aircraft, and installing it; S5, adjusting the length of the first adjustable connecting rod to adjust the roll angle of the second-stage aircraft; S6, after calibrating the roll angles of the first-stage aircraft and the second-stage aircraft, installing the length of the second adjustable connecting rod on the other side, and fixing the lengths of the two adjustable connecting rods so that the relative positions of the first-stage aircraft and the second-stage aircraft remain unchanged.

[0015] Furthermore, when the roll angle of the first-stage aircraft is known, the roll angle of the second-stage aircraft is adjusted using the following formula:

[0016]

[0017] Where γ is the roll angle of the secondary tooling, a is the distance between the secondary tooling structure shaft hole and the secondary matching hole, b is the distance between the primary matching hole and the secondary matching hole, c is the distance between the primary tooling structure shaft hole and the primary matching hole, d is the top screw thread pitch, l is the initial length of the left adjustable connecting rod, and Φ is the rotation angle of the middle section of the top screw.

[0018] The beneficial effect of the technical solution of this invention lies in that, by connecting the first and second stage fixtures in parallel with two left and right adjustable links, the relative roll angle error of the first and second stage aircraft in a piggyback parallel layout can be effectively reduced. Furthermore, compared to existing technologies, this fixture structure allows for synchronous adjustment of the roll angles of both aircraft, simplifying the aircraft roll angle adjustment process. Furthermore, this structure is easy to manufacture and install, making it suitable for measuring the aerodynamic characteristics of two aircraft in wind tunnel testing. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the specific embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0020] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0021] Figure 2 For the present invention Figure 1 Side view of

[0022] Figure 3 This is a schematic diagram of the connection between the first-level tooling and the second-level tooling of the present invention;

[0023] Figure 4 For the present invention Figure 3 Side view of

[0024] Figure 5 For the present invention Figure 3 AA cross-sectional view;

[0025] Figure 6 It is a schematic diagram of the secondary tooling structure of the present invention;

[0026] Figure 7 For the present invention Figure 6 Side view of

[0027] Figure 8 For the present invention Figure 6 AA cross-sectional view;

[0028] Figure 9 Schematic diagram of the adjustable connecting rod structure of the present invention;

[0029] Figure 10 For the present invention Figure 9 AA cross-sectional view;

[0030] Figure 11 This is a schematic diagram of the structure of the tooling connection block of the present invention;

[0031] Figure 12 For the present invention Figure 11 AA cross-sectional view;

[0032] Figure 13 Schematic diagram of the top wire structure of the present invention;

[0033] Figure 14 For the present invention Figure 13 AA cross-sectional view;

[0034] Figure 15 For the present invention Figure 13 Side view of

[0035] Figure 16 A schematic diagram of calculating the roll angle adjustment of the secondary tooling according to the present invention;

[0036] Description of reference numerals:

[0037] 1-First-level tooling, 101-First-level matching hole, 2-Second-level tooling, 201-Second-level matching hole, 3-First-level aircraft, 4-Second-level aircraft, 5-Adjustable connecting rod, 6-Tooling connection block, 601-Threaded hole, 602-Circular hole, 7-Top screw, 701-Threaded portion, 702-Cylindrical matching section, 703-Polygonal structure, 8-Groove, 9-First-level support rod, 10-Second-level support rod, 11-Horseshaft hole, 12-Horseshaft, 13-Pin hole; DETAILED DESCRIPTION

[0038] The following will clearly and completely describe the technical solutions of the present invention in conjunction with the embodiments. Obviously, the embodiments described are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0039] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like to indicate directions or positional relationships based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operate in a specific direction, and therefore should not be understood as limiting the present invention.

[0040] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the said features. In the description of the present invention, "multiple" means two or more, unless otherwise clearly and specifically defined. In addition, the terms "installed", "connected", and "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be an indirect connection through an intermediate medium, or it can be a communication between the two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to the specific circumstances.

[0041] Example 1

[0042] like Figures 1-15As shown, the present invention provides a tool calibration structure for a dual balance measurement system, including a first-level tool 1 and a second-level tool 2 arranged in parallel, the first-level tool 1 is equipped with a first-level aircraft 3, and the second-level tool 2 is equipped with a second-level aircraft 4. The same side of the first-level tool 1 and the second-level tool 2 is rotatably connected by an adjustable connecting rod 5, and the relative roll angle of the first-level aircraft 3 and the second-level aircraft 4 is adjusted by the adjustable connecting rods 5 on different sides.

[0043] Specifically, the present invention is primarily based on the fixture calibration structure of a wind tunnel test dual-balance measurement system. Corresponding to the parallel structure of the first-stage aircraft 3 and the second-stage aircraft 4, the first-stage fixture 1 and the second-stage fixture 2 also adopt a parallel structure, and are connected on the left and right sides by an adjustable connecting rod 5. The adjustable connecting rod 5 has a telescopic function. When the lengths of the two adjustable connecting rods 5 are fixed, the relative roll angle error of the first-stage aircraft 3 and the second-stage aircraft 4 can be effectively reduced. When the length of one adjustable connecting rod 5 is adjusted, the length of the other adjustable connecting rod 5 can be changed synchronously according to the parallelogram principle (because the lengths of the first-stage fixture 1 and the second-stage fixture 2 are unchanged, when the distance between the first-stage fixture 1 and the second-stage fixture 2 on one side changes, the distance on the other side will also change accordingly). This achieves synchronous adjustment of the roll angles of the two aircraft and simplifies the aircraft roll angle adjustment process.

[0044] Example 2

[0045] This embodiment 2 describes the telescopic control method of the adjustable connecting rod 5.

[0046] like Figures 9-15 As shown, the adjustable connecting rod 5 includes tooling connection blocks 6 at both ends and a set screw 7 with adjustable distance located between the two tooling connection blocks 6. The circumference of the two ends of the set screw 7 is respectively provided with a threaded portion 701 in opposite directions, and the tooling connection block 6 is provided with a threaded hole 601 that cooperates with the set screw 7.

[0047] Specifically, the length of the connecting rod 5 is adjustable through a threaded connection between a jackscrew 7 and two tooling connection blocks 6 at its ends. However, the threads at both ends of the jackscrew 7 have opposite directions and equal pitches, so that when the jackscrew 7 is turned, the distance between the primary tooling 1 and the secondary tooling 2 can be precisely controlled to decrease or increase by a corresponding amount.

[0048] Example 3

[0049] This embodiment 3 describes a further control method of the adjustable connecting rod 5.

[0050] The top screw 7 is further provided with a cylindrical mating section 702, and the tooling connection block 6 is further provided with a circular hole 602 that mates with the cylindrical mating section 702. The cylindrical mating section 702 and the threaded portion 701 form a stepped shaft, and the threaded hole 601 and the circular hole 602 form a stepped hole. The middle portion of the top screw 7 is a multi-faceted structure 703.

[0051] Specifically, the cylindrical fitting section 702 is located on the side of the threaded portion 701 away from the tooling connection block 6, and its diameter is larger than the diameter of the threaded portion 701, forming a stepped shaft structure; and correspondingly, the circular hole 602 is located on the side of the threaded hole 601 adjacent to the top screw 7, and its diameter is larger than the diameter of the threaded hole 601, forming a stepped hole structure. The advantages of this structure are that, on the one hand, the insertion of the cylindrical fitting section 702 and the circular hole 602 can maintain the coaxiality between the top screw 7 and the tooling connection block 6, ensuring the coaxiality and adjustment accuracy of the adjustable connecting rod 5; on the other hand, it facilitates the insertion of the threaded portion 701 of the guide top screw 7 into the threaded hole 601 of the tooling connection block 6. Of course, it should be noted that the cylindrical fitting section 702 can also be set on the side of the threaded portion 701 adjacent to the tooling connection block 6, and accordingly, the diameter of the cylindrical fitting section 702 needs to be smaller than the diameter of the threaded portion 701, also forming a stepped shaft structure, and the positional relationship between the circular hole 602 and the threaded hole 601 of the tooling connection block 6 is changed accordingly.

[0052] The middle section is designed as a polygonal structure, such as a quadrilateral square structure, to facilitate the control of the rotation of the top screw 7.

[0053] Example 4

[0054] This embodiment 4 specifically describes the connection between the adjustable connecting rod 5 and the first-level tooling 1 and the second-level tooling 2.

[0055] like Figure 3-Figure 8 As shown, the first-stage tooling 1 is provided with a first-stage matching hole 101 in the axial direction, and the first-stage aircraft 3 is connected to the first-stage tooling 1 through the first-stage matching hole 101. The second-stage tooling 2 is provided with a second-stage matching hole 201 in the axial direction, and the second-stage aircraft 4 is connected to the second-stage tooling 2 through the second-stage matching hole 201. Grooves 8 are provided on the side walls of the first-stage tooling 1 and the second-stage tooling 2, respectively, and the tooling connection block 6 is rotatably embedded in the groove 8. The end of the first-stage aircraft 3 away from the first-stage tooling 1 is connected to the first-stage support rod 9, and the end of the second-stage aircraft 4 away from the second-stage tooling 2 is connected to the second-stage support rod 10.

[0056] Specifically, matching holes are axially provided on the first-level tooling 1 and the second-level tooling 2, respectively. The first-level aircraft 3 and the second-level aircraft 4 are inserted into the first-level tooling 1 and the second-level tooling 2 through the axial holes and fixed by pins inserted into the pin holes 13. A groove 8 is also provided on the outer side surface of the outer side of the matching holes on the first-level tooling 1 and the second-level tooling 2, and a rotating shaft hole 11 is axially provided on the wall of the groove 8. A rotating shaft hole 11 is also axially provided on the tooling connection block 6. When the tooling connection block 6 is embedded in the groove 8, the rotating shaft 12 is inserted into the rotating shaft hole 11 to realize the rotatable connection between the adjustable connecting rod 5 and the first-level tooling 1 and the second-level tooling 2. The width and depth of the groove 8 of the first-level tooling 1 and the groove 8 of the second-level tooling 2 are consistent. The width of the adjustable connecting rod 5 is consistent with the width of the groove 8, and the height is less than the depth of the groove 8, providing sufficient space for the rotational movement of the adjustable connecting rod 5. The adjustable link 5 is rotationally connected to the primary fixture 1 via the primary fixture 1 connection block and rotational axis 12 at one end, and to the secondary fixture 2 via the secondary fixture 2 connection block and rotational axis 12 at the other end. This means that the adjustable link 5 has only one degree of freedom: rotation about rotational axis 12. The left and right adjustable links 5 work together to ensure unified movement of the primary and secondary fixtures 1 and 2, based on parallelogram theory. Within the fixture structure, the rotational axis hole 11 of the right adjustable link 5, the cylindrical mating section 702 of the aircraft, and the rotational axis hole 11 of the left adjustable link 5 must be aligned.

[0057] Example 5

[0058] like Figure 16 As shown, the present invention also provides a method for using the tooling calibration structure, comprising the following steps: S1, calibrating the initial roll angles of the first-stage aircraft 3 and the second-stage aircraft 4; S2, assembling the first-stage aircraft 3 and the first-stage tooling 1, leveling the roll angle of the first-stage aircraft 3 model, and fixing it; S3, adjusting the length of the first adjustable connecting rod on one side to be roughly equal to the distance between the first-stage aircraft 3 and the second-stage aircraft 4; S4, assembling the second-stage aircraft 4 and the second-stage tooling 5, adjusting the length of the first adjustable connecting rod according to the distance between the first-stage aircraft 3 and the second-stage aircraft 4, and installing it; S5, adjusting the length of the first adjustable connecting rod to adjust the roll angle of the second-stage aircraft 4; S6, after calibrating the roll angles of the first-stage aircraft 3 and the second-stage aircraft 4, installing the length of the second adjustable connecting rod on the other side, and fixing the lengths of the two adjustable connecting rods 5 to keep the relative positions of the first-stage aircraft 3 and the second-stage aircraft 4 unchanged.

[0059]

[0060] Where γ is the roll angle of the secondary tooling, a is the distance between the secondary tooling structure shaft hole and the secondary matching hole, b is the distance between the primary matching hole and the secondary matching hole, c is the distance between the primary tooling structure shaft hole and the primary matching hole, d is the top screw thread pitch, l is the initial length of the left adjustable connecting rod, and Φ is the rotation angle of the middle section of the top screw.

[0061] Specifically, during use, first calibrate the initial roll angles of the first-stage aircraft 3 and the second-stage aircraft 4. Assemble the first-stage aircraft 3 and the first-stage tooling 1, use the quadrant to level the roll angle of the first-stage aircraft 3, and tighten and secure the first-stage aircraft 3. Adjust the length of the first adjustable connecting rod 5 (i.e., the left adjustable connecting rod) so that its length is roughly equal to the 3 / 4 distance between the first-stage and second-stage aircraft. Assemble the second-stage aircraft 4 with the second-stage tooling 2, and then adjust the left adjustable connecting rod 5 according to the 1 / 2 distance between the first-stage and second-stage tooling, and install it. After the tooling calibration mechanism is assembled, adjust the length of the left adjustable connecting rod 5. When the roll angle of the first-stage aircraft 3 is known, the roll angle of the second-stage aircraft 4 can be adjusted based on the following formula:

[0062]

[0063]

[0064] n 2 =b 2 +c 2 (3)

[0065]

[0066] γ=β-α (5)

[0067] In summary,

[0068]

[0069] Where γ is the roll angle of the secondary tooling, a is the distance between the secondary tooling structure shaft hole and the secondary matching hole, b is the distance between the primary matching hole and the secondary matching hole, c is the distance between the primary tooling structure shaft hole and the primary matching hole, d is the top screw thread pitch, l is the initial length of the left adjustable connecting rod, and Φ is the rotation angle of the middle section of the top screw.

[0070] After calibrating the roll angles of the first and second stage vehicles, install the right adjustable link 5 and fix the lengths of the left and right adjustable links 5 to ensure that the relative positions of the vehicles remain unchanged. When the vehicle roll angles are changed, the roll angles of the first and second stage vehicles change in unison due to the parallelogram principle. Therefore, only one of the first and second stage vehicles needs to be adjusted to adjust the roll angles of both vehicles.

[0071] The usage of the present invention is described in Example 5 and will not be described in detail.

[0072] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the above embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the above embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A tool calibration structure for a dual balance measurement system, characterized in that: The first-stage tooling and the second-stage tooling are arranged in parallel, wherein the first-stage tooling is equipped with the first-stage aircraft, and the second-stage tooling is equipped with the second-stage aircraft. The left sides of the first-stage tooling and the second-stage tooling are rotatably connected by a first adjustable connecting rod, and the right sides are rotatably connected by a second adjustable connecting rod. The relative roll angles of the first-stage and second-stage aircraft are adjusted through adjustable links on different sides; When the lengths of the first adjustable link and the second adjustable link are fixed, the relative roll angle error between the first-stage aircraft and the second-stage aircraft is reduced, ensuring that the relative positions between the aircraft remain unchanged; When the length of the first adjustable link or the second adjustable link is adjusted, the length of the other adjustable link changes synchronously, and the roll angles of the first-stage aircraft and the second-stage aircraft change in unison, thereby achieving synchronous adjustment of the roll angles of the two aircraft.

2. The tooling calibration structure of the dual-balance measurement system according to claim 1, characterized in that: The adjustable connecting rod comprises tooling connection blocks at both ends and a top screw with adjustable distance located between the two tooling connection blocks.

3. The tooling calibration structure of the dual-balance measurement system according to claim 2, characterized in that: The circumferential surfaces at both ends of the top screw are respectively provided with threaded parts in opposite directions, and the tool connection block is provided with a threaded hole matched with the top screw.

4. The tooling calibration structure of the dual-balance measurement system according to claim 3, characterized in that: The top screw is also provided with a cylindrical matching section, and the tool connection block is also provided with a circular hole matching with the cylindrical matching section. The cylindrical matching section and the threaded portion form a stepped shaft, and the threaded hole and the circular hole form a stepped hole.

5. The tooling calibration structure of the dual-balance measurement system according to claim 4, characterized in that: The middle part of the top screw is a multi-ribbed structure.

6. The tooling calibration structure of the dual-balance measurement system according to claim 2, characterized in that: The first-level tooling is axially provided with a first-level matching hole, and the first-level aircraft is connected to the first-level tooling through the first-level matching hole. The second-level tooling is axially provided with a second-level matching hole, and the second-level aircraft is connected to the second-level tooling through the second-level matching hole.

7. The tooling calibration structure of the dual-balance measurement system according to claim 6, characterized in that: Grooves are respectively provided on both side walls of the first-level tooling and the second-level tooling, and the tooling connecting blocks are rotatably embedded in the grooves.

8. The tooling calibration structure of the dual-balance measurement system according to claim 1, characterized in that: The end of the first-stage aircraft away from the first-stage tooling is connected to the first-stage support rod, and the end of the second-stage aircraft away from the second-stage tooling is connected to the second-stage support rod.

9. A method for using the tool calibration structure according to any one of claims 1 to 8, characterized in that: The steps include: S1, calibrate the initial roll angles of the first-stage and second-stage aircraft; S2, assemble the first-level aircraft and the first-level tooling, level the roll angle of the first-level aircraft model, and fix it; S3, adjusting the length of the first adjustable link on one side to be approximately equal to the distance between the first-stage aircraft and the second-stage aircraft; S4, assembling the secondary aircraft and the secondary tooling, adjusting the length of the first adjustable connecting rod according to the distance between the primary aircraft and the secondary aircraft, and installing them; S5, adjusting the length of the first adjustable link to adjust the roll angle of the secondary aircraft; S6, after calibrating the roll angles of the first-stage aircraft and the second-stage aircraft, install the second adjustable link on the other side and fix the lengths of the two adjustable links so that the relative positions of the first-stage aircraft and the second-stage aircraft remain unchanged.

10. The method for using the tooling calibration structure according to claim 9, characterized in that: When the roll angle of the first-stage aircraft is known, the roll angle of the second-stage aircraft is adjusted using the following formula: ； Where, is the rolling angle of the secondary tooling, a is the distance between the secondary tooling structure shaft hole and the secondary matching hole, b is the distance between the primary matching hole and the secondary matching hole, c is the distance between the first-level tooling structure shaft hole and the first-level matching hole, d is the top screw thread pitch, l is the initial length of the first adjustable link, Φ The rotation angle of the middle section of the top screw.

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