A kind of vehicle model attitude adjusting structure and wake characteristic measurement method

Abstract

A kind of vehicle model posture adjusting structure and wake feature measurement method, including the attack angle adjusting component and drift angle adjusting component installed in the lower end of sword rod;Drift angle adjusting component includes the drift angle adjusting plate that can be detachably fixed with vehicle model, pivot is arranged in the middle of the lower surface of drift angle adjusting plate, first hinged part is arranged in the middle of the upper surface of drift angle adjusting plate;Attack angle adjusting component includes the attack angle adjusting plate that is fixed with the lower end of sword rod, the middle of attack angle adjusting plate is provided with the second hinged part that is hinged with first hinged part, attack angle adjusting plate is respectively provided with support at both ends along the length direction of vehicle model, support is used to adjust the included angle between the central axis of sword rod and the axis of vehicle model;Drift angle adjusting plate is rotated with pivot as center relative to vehicle model, for adjusting the included angle between the central longitudinal section of sword rod and the axis of vehicle model;The number of sword rod is one, reduce the influence of sword rod on test, facilitate vehicle model posture adjustment and carry out fine vehicle wake feature measurement.

Description

Technical Field

[0001] This invention relates to the field of aircraft model testing technology, and in particular to an attitude adjustment structure for an aircraft model and a method for measuring wake characteristics. Background Technology

[0002] In the field of shipbuilding, it is necessary to evaluate and test the performance of underwater vehicle models through underwater experiments.

[0003] For the wake characteristics of a vehicle, general experimental studies often use two spar rods to support the vehicle model along the front and rear directions. The angle of attack of the model is adjusted by adjusting the height of the two spar rods. The whole set of equipment is often quite complicated and inconvenient to adjust. Moreover, the influence of the two spar rods on the drag of the model and the wake is not negligible. In addition, the double spar rod installation method can only adjust the angle of attack, but cannot adjust the drift angle at the same time, which makes it impossible to complete the precise experimental research of the vehicle.

[0004] During underwater navigation, the angle of attack and drift angle of the vehicle are in a dynamic process. There is an urgent need for structural and refined experimental research on the vehicle model to facilitate attitude adjustment, so that more accurate data can be obtained during the experimental stage to guide the design of the vehicle. Summary of the Invention

[0005] To address the shortcomings of existing production technologies, the applicant provides a structure for adjusting the attitude of a flight vehicle model and a method for measuring wake characteristics, thereby reducing the impact of the rapier on the experiment, facilitating attitude adjustment of the flight vehicle model, and enabling precise measurement of the wake characteristics of the flight vehicle.

[0006] The technical solution adopted in this invention is as follows:

[0007] An attitude adjustment structure for a flight vehicle model includes an angle-of-attack adjustment component installed at the lower end of a sword shaft, the angle-of-attack adjustment component being located inside the flight vehicle model, and a drift angle adjustment component also being provided inside the flight vehicle model;

[0008] The drift angle adjustment assembly includes a drift angle adjustment plate that is detachably and fixedly connected to the aircraft model. A pivot is provided at the center of the lower surface of the drift angle adjustment plate, and a first hinge is provided at the center of the upper surface of the drift angle adjustment plate.

[0009] The angle of attack adjustment assembly includes an angle of attack adjustment plate fixedly connected to the lower end of the sword shaft. A second hinge portion is provided in the middle of the angle of attack adjustment plate. The second hinge portion is hinged to the first hinge portion. Support members are provided at both ends of the angle of attack adjustment plate along the length direction of the aircraft model. The lower part of the support member cooperates with the aircraft model to adjust the angle between the central axis of the sword shaft and the axis of the aircraft model.

[0010] The drift angle adjustment plate rotates relative to the vehicle model with the pivot as the center, and is used to adjust the angle between the mid-longitudinal section of the sword shaft and the axis of the vehicle model;

[0011] The number of sword shafts is one.

[0012] Its further technical solution lies in:

[0013] The second hinge part is a plate-shaped structure. There are two second hinge parts, which are arranged in parallel and spaced apart on the angle of attack adjustment plate. The second hinge part is provided with a first through hole.

[0014] The first hinge portion is provided with a second through hole, which is concentrically arranged with the first through hole and connected by a hinge shaft.

[0015] The support is a screw, and the angle of attack adjustment plate is provided with a first threaded hole that mates with the support. The lower end of the support abuts against the model of the aircraft. Adjusting the distance between the lower end of the support and the angle of attack adjustment plate is used to adjust the angle between the central axis of the sword shaft and the axis of the model of the aircraft.

[0016] The number of the first threaded holes is four, and they are symmetrical about the mid-longitudinal section of the rapier.

[0017] The drift angle adjustment plate is provided with drift angle adjustment holes at both ends along the axis of the vehicle model. The drift angle adjustment holes are arc-shaped waist holes. The center of the arc center line of the drift angle adjustment hole coincides with the rotating shaft. A first fastener is installed at the drift angle adjustment hole. The first fastener is used to detachably and fix the vehicle model and the drift angle adjustment plate.

[0018] It also includes a mounting base assembly, the structure of which includes a mounting base plate, the mounting base plate being fixedly installed inside the aircraft model by a second fastener;

[0019] The lower end of the rotating shaft is provided with an external thread. The lower end of the rotating shaft passes through the shaft hole in the middle of the mounting base plate and then engages with a nut to detachably and fix the drift angle adjustment plate to the mounting base plate.

[0020] The lower part of the aircraft model is provided with an operating hole that mates with the nut.

[0021] The lower end of the sword shaft is provided with a connecting plate, which is detachably connected to the angle of attack adjustment plate via a third fastener. The angle of attack adjustment plate is provided with a second threaded hole that mates with the third fastener.

[0022] The cross-section of the sword shaft is airfoil-shaped.

[0023] The model of the aircraft is provided with a cover plate that matches the streamlined shape of the exterior of the model. The cover plate is detachably installed on the model of the aircraft to cover the angle of attack adjustment component and the drift angle adjustment component. The cover plate is provided with a through hole for the spar to cooperate with the spar.

[0024] A method for measuring the wake characteristics of a vehicle model includes the following steps:

[0025] S1. Determine the measurement conditions: The conditions include the drift angle and angle of attack of the aircraft model;

[0026] S2. Adjust the angle of attack of the aircraft model: Release the support member from the aircraft model, swing the angle of attack adjustment plate around the axis of the hinge between the second hinge and the first hinge, and after the angle of attack of the aircraft model meets the measurement conditions, re-connect the support member to the aircraft model and keep the angle of attack of the aircraft model unchanged.

[0027] S3. Adjust the drift angle of the model: Disconnect the drift angle adjustment component from the model and rotate the drift angle adjustment plate relative to the model around the pivot. After the drift angle of the model meets the measurement conditions, reconnect the drift angle adjustment component to the model in a detachable and fixed manner.

[0028] S4. Wake Measurement: A moving device connected to the rapier is used to move the submerged water-based model along a set route and collect wake characteristics.

[0029] Repeat steps S1-S4 to collect wake characteristics under multiple sets of different drift angle and angle of attack combinations.

[0030] The beneficial effects of this invention are as follows:

[0031] This invention features a compact and rational structure, and is easy to operate. It uses a single spar to fix the model of the vehicle, reducing the impact of the spar structure on the underwater navigation performance test of the model. At the end of the spar, it is connected to the inside of the model through drift angle adjustment components and angle of attack adjustment components, which can simultaneously adjust the angle of attack and drift angle of the model during navigation. By setting different combinations of angle of attack and drift angle parameters during the wake characteristic measurement of the model, more accurate wake characteristic data can be obtained during the test phase, which can be used to guide the design and research of the vehicle.

[0032] Furthermore, the present invention also has the following advantages:

[0033] (1) The screw structure support can be screwed in and out inside the first threaded hole to adjust the distance between the lower end of the support and the angle of attack adjustment plate, thereby controlling the specific value of the angle between the central axis of the scissor and the axis of the ship model. This structure is simple and easy to adjust manually.

[0034] (2) The drift angle adjustment plate rotates relative to the model of the aircraft with the pivot as the center, and the drift angle of the model of the aircraft is adjusted through a pair of arc-shaped waist hole structure drift angle adjustment holes and the first fastener. The structure is simple and easy to adjust manually.

[0035] (3) A nut is set at the lower part of the shaft. The nut is used to fix the drift angle adjustment plate to the mounting base plate from the middle position of the drift angle adjustment plate. The drift angle adjustment plate is fixed from both ends of the drift angle adjustment plate with the first fastener. This not only makes the drift angle adjustment operation convenient, but also increases the stability of the drift angle adjustment structure. Attached Figure Description

[0036] Figure 1 This is a schematic diagram of the structure of the present invention.

[0037] Figure 2 for Figure 1 Enlarged view of point A in the middle.

[0038] Figure 3 This is a schematic diagram of the drift angle adjustment state of the present invention. Figure 1 .

[0039] Figure 4 This is a schematic diagram of the drift angle adjustment state of the present invention. Figure 2 .

[0040] Figure 5 This is a schematic diagram of the angle of attack adjustment state of the present invention.

[0041] Figure 6 This is a front view of the angle of attack adjustment component of the present invention.

[0042] Figure 7 This is a bottom view of the angle of attack adjustment component of the present invention.

[0043] Figure 8 This is a front view of the drift angle adjustment component of the present invention.

[0044] Figure 9 This is a top view of the drift angle adjustment component of the present invention.

[0045] Figure 10 This is a top view of the mounting plate of the present invention.

[0046] Figure 11 This is a cross-sectional view of the sword shaft of the present invention.

[0047] Figure 12 This is a top view of the cover plate of the present invention.

[0048] in:

[0049] 1. Sword shaft; 11. Connecting plate;

[0050] 2. Model of the aircraft body; 21. Cover plate; 211. First plate; 212. Mounting hole; 213. Through hole for the spar; 22. Operating hole;

[0051] 3. Angle of attack adjustment assembly; 31. Angle of attack adjustment plate; 311. First threaded hole; 312. Second threaded hole; 32. Second hinge part; 321. First through hole; 33. Support member;

[0052] 4. Drift angle adjustment assembly; 41. Drift angle adjustment plate; 411. Drift angle adjustment hole; 42. Nut; 43. Rotating shaft; 44. First fastener; 45. First hinge; 451. Second through hole;

[0053] 5. Mounting base assembly; 51. Mounting base plate; 511. Second plate; 512. Connecting hole; 513. Angle fixing hole; 514. Shaft hole; 52. Second fastener;

[0054] 6. Hinge shaft. Detailed Implementation

[0055] The specific embodiments of the present invention will now be described with reference to the accompanying drawings.

[0056] Example 1:

[0057] like Figures 1-5 As shown, the attitude adjustment structure of the aircraft model in this embodiment includes an angle-of-attack adjustment component 3 installed at the lower end of the spar 1. The angle-of-attack adjustment component 3 is located inside the aircraft model 2. The aircraft model 2 also has a drift angle adjustment component 4. The drift angle adjustment component 4 includes a drift angle adjustment plate 41 that is detachably and fixedly connected to the aircraft model 2. A pivot 43 is provided in the middle of the lower surface of the drift angle adjustment plate 41, and a first hinge portion 45 is provided in the middle of the upper surface of the drift angle adjustment plate 41. The angle-of-attack adjustment component 3 includes an angle-of-attack adjustment plate 41 that is fixedly connected to the lower end of the spar 1. Plate 31, the angle of attack adjustment plate 31 is provided with a second hinge part 32 in the middle, the second hinge part 32 is hinged with the first hinge part 45, the angle of attack adjustment plate 31 is provided with support members 33 at both ends along the length direction of the aircraft model 2, the lower part of the support member 33 cooperates with the aircraft model 2, and is used to adjust the angle between the central axis of the sword 1 and the axis of the aircraft model 2; the drift angle adjustment plate 41 rotates relative to the aircraft model 2 with the pivot 43 as the center, and is used to adjust the angle between the mid-longitudinal section of the sword 1 and the axis of the aircraft model 2; the number of swords 1 is one.

[0058] Specifically, one end of the spar 1 is fitted with the model 2 of the aircraft, and the other end of the spar 1 is connected to the power device that drives the model 2 to move. The spar 1 serves to fix the model 2. When the angle between the central axis of the spar 1 and the axis of the model 2 is adjusted, the angle of attack of the model 2 is adjusted accordingly. When the angle between the longitudinal section of the spar 1 and the axis of the model 2 is adjusted, the drift angle of the model 2 is adjusted accordingly.

[0059] A single spar 1 is used to fix the model 2, reducing the impact of the spar 1 structure on the underwater navigation performance test of the model 2. The end of the spar 1 is connected to the inside of the model 2 through the drift angle adjustment component 4 and the angle of attack adjustment component 3, and the angle of attack and drift angle of the model 2 can be adjusted simultaneously during navigation.

[0060] In this embodiment, the attitude adjustment structure of the aircraft model is compactly built into the aircraft model 2.

[0061] Furthermore, such as Figures 5-7 As shown, the second hinge part 32 is a plate-shaped structure. There are two second hinge parts 32, which are arranged in parallel and spaced apart on the angle of attack adjustment plate 31. The second hinge part 32 is provided with a first through hole 321.

[0062] The first hinge part 45 is provided with a second through hole 451, which is concentrically arranged with the first through hole 321 and connected by the hinge shaft 6.

[0063] The support member 33 is a screw, and the angle of attack adjustment plate 31 is provided with a first threaded hole 311 that mates with the support member 33. The lower end of the support member 33 abuts against the aircraft model 2. Adjusting the distance between the lower end of the support member 33 and the angle of attack adjustment plate 31 is used to adjust the angle between the central axis of the sword shank 1 and the axis of the aircraft model 2.

[0064] The number of first threaded holes 311 is four and they are symmetrical about the mid-longitudinal section of the rapier 1.

[0065] Specifically, when the lower end of the support member 33 is disconnected from the aircraft model 2, the angle of attack adjustment plate 31 can swing around the hinge axis 6 to change the drift angle of the aircraft model 2; the screw-structured support member 33 can be adjusted by screwing in and out of the first threaded hole 311 to adjust the distance between the lower end of the support member 33 and the angle of attack adjustment plate 31, thereby controlling the specific value of the angle between the central axis of the scissor 1 and the axis of the aircraft model 2. This structure is simple and easy to adjust manually; four first threaded holes 311 are symmetrically arranged about the longitudinal section of the scissor 1, and four support members 33 are installed accordingly to stabilize and fix the drift angle.

[0066] Furthermore, the width of the first hinge portion 45 is the same as the distance between the two second hinge portions 32. A fastening structure is provided on the hinge shaft 6. The fastening structure includes a stop block located at one end of the hinge shaft 6 and a locking nut threadedly connected to the other end of the hinge shaft 6. After the drift angle adjustment is completed, the locking nut on the hinge shaft 6 is tightened so that the stop block and the locking nut clamp the first hinge portion 45 and the second hinge portion 32, restricting the relative rotation tendency of the first hinge portion 45 and the second hinge portion 32, and increasing the stability of the angle of attack adjustment structure.

[0067] Furthermore, such as Figures 3-4 , Figures 8-9 As shown, the drift angle adjustment plate 41 is provided with drift angle adjustment holes 411 at both ends along the axis of the navigating body model 2. The drift angle adjustment hole 411 is an arc-shaped waist hole. The center of the arc center line of the drift angle adjustment hole 411 coincides with the rotating shaft 43. The first fastener 44 is installed at the drift angle adjustment hole 411. The first fastener 44 is used to detachably and fix the navigating body model 2 and the drift angle adjustment plate 41.

[0068] Specifically, the first fastener 44 is a bolt. One end of the first fastener 44 is threadedly connected to the model 2. After the first fastener 44 passes through the drift angle adjustment hole 411, the bolt head at the other end of the first fastener 44 engages with the upper surface of the drift angle adjustment plate 41. The drift angle adjustment plate 41 and the model 2 are detachably and fixedly connected by tightening the first fastener 44. Half of the arc range of the arc-shaped waist hole is the drift angle adjustment range.

[0069] The drift angle adjustment plate 41 rotates relative to the model 2 with the pivot 43 as the center, and the drift angle of the model 2 is adjusted through a pair of arc-shaped waist hole structure drift angle adjustment holes 411 and the first fastener 44. The structure is simple and easy to adjust manually.

[0070] Furthermore, such as Figure 2 , Figure 10 As shown, it also includes a mounting base assembly 5. The structure of the mounting base assembly 5 is as follows: it includes a mounting base plate 51, which is fixedly installed inside the aircraft model 2 by a second fastener 52. The lower end of the rotating shaft 43 is provided with an external thread. The lower end of the rotating shaft 43 passes through the shaft hole 514 in the middle of the mounting base plate 51 and then cooperates with the nut 42 to detachably and fix the drift angle adjustment plate 41 to the mounting base plate 51. The lower part of the aircraft model 2 is provided with an operating hole 22 that cooperates with the nut 42.

[0071] Specifically, the mounting base assembly 5 is built into the aircraft model 2. The structure of the mounting base plate 51 includes a second plate 511, a shaft hole 514 in the middle of the second plate 511, and a connecting hole 512 on the outer periphery of the second plate 511. The second fastener 52 passes through the connecting hole 512 to fix the mounting base plate 51 inside the aircraft model 2. The mounting base assembly 5 provides a base for mounting the attitude adjustment structure of the aircraft model 2. The second plate 511 is also provided with a drift angle fixing hole 513 for fixing the first fastener 44, so that the first fastener 44 is indirectly connected to the aircraft model 2. The drift angle fixing hole 513 is a threaded hole that mates with the first fastener 44, which facilitates operation from the top of the first fastener 44. The drift angle adjustment plate 41 can be fixed and unfixed in one operation. When installing the drift angle adjustment plate 41, the rotating shaft 43 is passed through the shaft hole 514 and extends out of the lower surface of the mounting plate 51. The nut 42 is installed and kept loose. The drift angle adjustment plate 41 is rotated so that the first hinge part 45 on the drift angle adjustment plate 41 rotates together with the drift angle adjustment plate 41 to a suitable position. The nut 42 is then rotated so that the lower surface of the drift angle adjustment plate 41 and the upper end surface of the nut 42 are simultaneously pressed against the mounting plate 51. The drift angle adjustment plate 41 is then fixedly connected to the mounting plate 51 and remains relatively stationary relative to the model 2. When tightening the nut 42, it can be operated through the operating hole 22 at the bottom of the model 2.

[0072] Furthermore, a nut 42 is provided at the lower part of the rotating shaft 43. The nut 42 fixes the drift angle adjustment plate 41 to the mounting base plate 51 from the middle position of the drift angle adjustment plate 41. The drift angle adjustment plate 41 is fixed from both ends by the first fastener 44. This not only makes the operation of adjusting the drift angle convenient, but also increases the stability of the drift angle adjustment structure.

[0073] Furthermore, such as Figure 2 , Figure 11 As shown, a connecting plate 11 is provided at the lower end of the sword shaft 1. The connecting plate 11 is detachably connected to the angle of attack adjustment plate 31 via a third fastener. The angle of attack adjustment plate 31 is provided with a second threaded hole 312 that mates with the third fastener. The connecting plate 11 is used to increase the contact area between the lower end of the sword shaft 1 and the angle of attack adjustment plate 31, making the fixing structure of the aircraft model 2 more stable.

[0074] Furthermore, such as Figure 11 As shown, the cross-section of the rapier 1 is airfoil-shaped. This further reduces the impact of the rapier 1 structure on the underwater navigation performance test of the vehicle model 2.

[0075] Furthermore, such as Figure 2 , Figure 12As shown, the model 2 of the aircraft is provided with a cover plate 21 that is consistent with the external streamline shape of the model 2 of the aircraft. The cover plate 21 is detachably installed on the model 2 of the aircraft to cover the angle of attack adjustment component 3 and the drift angle adjustment component 4. The cover plate 21 is provided with a spar through hole 213 that cooperates with the spar 1.

[0076] Specifically, the cover plate 21 can be integrally molded or a split structure, covering the angle of attack adjustment component 3 and drift angle adjustment component 4 while cooperating with the scimitar 1. The outer periphery of the first plate 211 of the cover plate 21 is provided with multiple mounting holes 212, and the first plate 211 can be detachably connected to the model 2 of the aircraft using fasteners. When the drift angle or angle of attack is adjusted, the cover plate 21 adapted to the scimitar 1 can be replaced.

[0077] Example 2:

[0078] The method for measuring the wake characteristics of a flight model using the attitude adjustment structure of the flight model in Example 1 includes the following steps:

[0079] S1. Determine the measurement conditions: The conditions include the drift angle and angle of attack of the aircraft model 2;

[0080] S2. Adjust the angle of attack of the aircraft model 2: Release the cooperation between the support member 33 and the aircraft model 2, swing the angle of attack adjustment plate 31 around the axis of the hinge between the second hinge part 32 and the first hinge part 45, and after the angle of attack of the aircraft model 2 meets the measurement conditions, re-cooperate the support member 33 with the aircraft model 2 to keep the angle of attack of the aircraft model 2 unchanged.

[0081] S3. Adjust the drift angle of the navigation body model 2: Disconnect the drift angle adjustment component 4 from the navigation body model 2, rotate the drift angle adjustment plate 41 relative to the navigation body model 2 with the pivot 43 as the center, and after the drift angle of the navigation body model 2 meets the measurement conditions, reconnect the drift angle adjustment component 4 to the navigation body model 2 in a detachable fixed connection.

[0082] S4. Wake measurement: A moving device connected to the rapier 1 is used to move the submerged water-based model 2 along a set route and collect wake characteristics.

[0083] Repeat steps S1-S4 to collect wake characteristics under multiple sets of different drift angle and angle of attack combinations.

[0084] By setting different combinations of angle of attack and drift angle parameters during the wake characteristic measurement of the aircraft model, more accurate wake characteristic data can be obtained during the test phase, which can be used to guide the design and research of the aircraft.

[0085] Example 3:

[0086] Method for measuring wake characteristics of a flight model using the attitude adjustment structure of the flight model in Example 1:

[0087] During the wake characteristic measurement of the vehicle model, the vehicle model 2 travels along a predetermined route in the test pool. The upper end of the scimitar 1 connected to the vehicle model 2 is fixed on a movable trailer. The trailer travels along the bank of the pool, thereby driving the vehicle model 2 to travel in the water.

[0088] Determine the measurement conditions: These include the drift angle and angle of attack of the aircraft model 2, which can have various combinations. Adjust the drift angle and angle of attack after removing the cover plate 21 from the aircraft model 2.

[0089] Adjusting the angle of attack of the aircraft model 2: Loosen the locking nut at the other end of the hinge shaft 6, release the fixed relationship between the first hinge part 45 and the second hinge part 32, adjust the distance between the lower end of the support member 33 and the angle of attack adjustment plate 31, release the cooperation relationship between the support member 33 and the aircraft model 2, and swing the angle of attack adjustment plate 31 around the axis of the hinge between the second hinge part 32 and the first hinge part 45. After the angle of attack of the aircraft model 2 meets the measurement conditions, re-coupling the support member 33 with the aircraft model 2 to keep the angle of attack of the aircraft model 2 unchanged, and confirm by measuring with an inclination meter. Then, retighten the locking nut to fix the relative positions of the first hinge part 45 and the second hinge part 32. Figure 5 As shown.

[0090] Adjusting the drift angle of the vehicle model 2: Loosen the nut 42 and the first fastener 44 at the lower part of the rotating shaft 43, detach the drift angle adjustment assembly 4 from the vehicle model 2, rotate the drift angle adjustment plate 41 relative to the vehicle model 2 with the rotating shaft 43 as the center, and after the drift angle of the vehicle model 2 meets the measurement conditions, re-tighten the nut 42 and the first fastener 44 at the lower part of the rotating shaft 43 to make the drift angle adjustment assembly 4 detachably and fixedly connected to the vehicle model 2. Figure 3 , Figure 4 As shown.

[0091] After adjusting the drift angle or angle of attack, replace the cover plate 21 with one that is compatible with the rapier shaft 1.

[0092] Wake measurement: After adjusting the angle of attack and drift angle, water is injected into the pool. The model 2 of the vehicle in the water moves along the set route and the wake characteristics are collected. The wake characteristics include the measurement of physical quantities such as the wake velocity of the vehicle. The collection of wake characteristics is a routine operation in this field. After one test, the angle of attack and drift angle of the model are readjusted.

[0093] Readjust the angle of attack and drift angle, and conduct tests with different combinations of angle of attack and drift angle. The order of adjusting the angle of attack and drift angle is not limited. By analyzing physical quantities such as the flow velocity of the wake, the wake characteristics of the vehicle under different combinations of drift angle and angle of attack are obtained.

[0094] The above description is an explanation of the present invention and not a limitation thereof. The scope of the present invention is defined by the claims. Within the scope of protection of the present invention, any form of modification may be made.

Claims

1. An attitude adjustment structure for a flight vehicle model, characterized in that: Includes an angle of attack adjustment component (3) installed at the lower end of the rapier (1), the angle of attack adjustment component (3) being located inside the navigator model (2), and a drift angle adjustment component (4) also being provided inside the navigator model (2). The drift angle adjustment assembly (4) includes a drift angle adjustment plate (41) that is detachably and fixedly connected to the aircraft model (2). A pivot (43) is provided in the middle of the lower surface of the drift angle adjustment plate (41), and a first hinge (45) is provided in the middle of the upper surface of the drift angle adjustment plate (41). The angle of attack adjustment assembly (3) includes an angle of attack adjustment plate (31) fixedly connected to the lower end of the sword (1). A second hinge part (32) is provided in the middle of the angle of attack adjustment plate (31). The second hinge part (32) is hinged to the first hinge part (45). Support members (33) are provided at both ends of the angle of attack adjustment plate (31) along the length direction of the aircraft model (2). The lower part of the support member (33) cooperates with the aircraft model (2) to adjust the angle between the central axis of the sword (1) and the axis of the aircraft model (2). The support member (33) is a screw, and the angle of attack adjustment plate (31) is provided with a first threaded hole (311) that mates with the support member (33). The lower end of the support member (33) abuts against the aircraft model (2). Adjusting the distance between the lower end of the support member (33) and the angle of attack adjustment plate (31) is used to adjust the angle between the central axis of the sword (1) and the axis of the aircraft model (2). The drift angle adjustment plate (41) rotates relative to the navigating body model (2) with the rotating shaft (43) as the center, and is used to adjust the angle between the mid-longitudinal section of the sword (1) and the axis of the navigating body model (2); The number of sword shafts (1) is one; The model (2) of the aircraft is provided with a cover plate (21) that is consistent with the external streamline of the model (2). The cover plate (21) is detachably installed on the model (2) to cover the angle of attack adjustment component (3) and the drift angle adjustment component (4). The cover plate (21) is provided with a spar through hole (213) that cooperates with the spar (1). The drift angle adjustment plate (41) is provided with drift angle adjustment holes (411) at both ends along the axis of the navigating body model (2). The drift angle adjustment holes (411) are arc-shaped waist holes. The center of the arc center line of the drift angle adjustment hole (411) coincides with the rotating shaft (43). A first fastener (44) is installed at the drift angle adjustment hole (411). The first fastener (44) is used to detachably and fix the navigating body model (2) and the drift angle adjustment plate (41). The cross section of the sword shaft (1) is airfoil-shaped.

2. The attitude adjustment structure for a flight vehicle model as described in claim 1, characterized in that: The second hinge part (32) is a plate-shaped structure. There are two second hinge parts (32) arranged in parallel and spaced apart on the angle of attack adjustment plate (31). The second hinge part (32) is provided with a first through hole (321). The first hinge part (45) is provided with a second through hole (451), which is concentrically arranged with the first through hole (321) and connected by the hinge shaft (6).

3. The attitude adjustment structure for a flight vehicle model as described in claim 1, characterized in that: The number of the first threaded holes (311) is four and they are symmetrical about the mid-longitudinal section of the scissor (1).

4. The attitude adjustment structure for a flight vehicle model as described in claim 1, characterized in that: It also includes a mounting base assembly (5), the structure of which includes a mounting base plate (51), the mounting base plate (51) being fixedly installed inside the aircraft model (2) by a second fastener (52); The lower end of the rotating shaft (43) is provided with an external thread. The lower end of the rotating shaft (43) passes through the shaft hole (514) in the middle of the mounting base plate (51) and then cooperates with the nut (42) to detachably and fix the drift angle adjustment plate (41) to the mounting base plate (51). The lower part of the aircraft model (2) is provided with an operating hole (22) that cooperates with the nut (42).

5. The attitude adjustment structure for a flight vehicle model as described in claim 1, characterized in that: The lower end of the sword shank (1) is provided with a connecting plate (11), which is detachably connected to the angle of attack adjustment plate (31) via a third fastener. The angle of attack adjustment plate (31) is provided with a second threaded hole (312) that cooperates with the third fastener.

6. A method for measuring the wake characteristics of a flight vehicle model using the attitude adjustment structure of the flight vehicle model as described in claim 1, characterized in that: Includes the following steps: S1. Determine the measurement conditions: The conditions include the drift angle and angle of attack of the aircraft model (2); S2. Adjust the angle of attack of the aircraft model (2): Release the cooperation between the support (33) and the aircraft model (2), swing the angle of attack adjustment plate (31) around the axis of the hinge between the second hinge (32) and the first hinge (45), and after the angle of attack of the aircraft model (2) meets the measurement conditions, re-cooperate the support (33) with the aircraft model (2) and keep the angle of attack of the aircraft model (2) unchanged. S3. Adjust the drift angle of the navigation body model (2): Disconnect the drift angle adjustment component (4) from the navigation body model (2), rotate the drift angle adjustment plate (41) relative to the navigation body model (2) with the pivot (43) as the center, and after the drift angle of the navigation body model (2) meets the measurement conditions, reconnect the drift angle adjustment component (4) to the navigation body model (2) in a detachable fixed manner. S4. Wake measurement: A moving device connected to the rapier (1) is used to move the submerged water-based model (2) along a set route and collect wake characteristics. Repeat steps S1-S4 to collect wake characteristics under multiple sets of different drift angle and angle of attack combinations.

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