Rapid installation device and method for tail support of airplane model for wind tunnel test

Abstract

The invention discloses a device and a method for quickly installing a tail support of an airplane model for a wind tunnel test. The device comprises a bent knife bracket, an outer tail sleeve seat, an inner tail sleeve seat, an installation execution servo motor, a torsion angle adjusting hollow servo motor, an installation execution force transmission shaft, a torsion angle adjusting force transmission hollow rod and a rod type balance, the rear end of the rod type balance is in coaxial insertion fit with the front end of the torsion angle adjusting force transmission hollow rod, the rear end of the rod type balance is in coaxial threaded connection fit with the front end of the installation execution force transmission shaft, and the front end of the rod type balance is used for being fixedly connected with an airplane model; laser distance measuring sensors are arranged under wingtips of the airplane model and are electrically connected with the wind tunnel main control computer; an airplane model torsion angle adjusting indicating lamp is arranged outside the wind tunnel. Semi-automatic installation is achieved, only manual assistance is achieved, the requirement for the skill level of installation personnel is lowered, the installation time is shortened, the installation efficiency is improved, the influence of human factors is reduced, installation precision error normalization is achieved, and the accuracy of measurement results and the reliability of test data are improved.

Description

Technical Field

[0001] The invention belongs to the technical field of wind tunnel testing, and in particular relates to a device and method for quickly installing a tail support of an aircraft model used in a wind tunnel test. Background Art

[0002] As a pipeline testing equipment, wind tunnel can artificially generate and control airflow to simulate the flow of gas around aircraft or objects. Through wind tunnel testing, the effect of airflow on aircraft or objects can be measured, and the corresponding physical phenomena can be observed during the wind tunnel test.

[0003] Currently, when conducting wind tunnel tests on aircraft models, the aircraft model is usually fixed to the test section of the wind tunnel via a tail support, which often uses a rod balance. The rod balance is used to measure the aerodynamic forces and moments acting on the aircraft model, and the installation accuracy of the rod balance can have a significant impact on the measurement results.

[0004] Since beam balances have a calibrated axis system when they leave the factory, which is called the body axis system in the industry, and the body axis will form an angle with the vertical axis when installed in the lift direction, the lift and lateral forces of the beam balance will have components. At the same time, due to the coupling interference between the various components of the beam balance, large measurement and iteration errors will be generated in this case. Therefore, in order to reduce the measurement error of the beam balance, it is key to ensure that its torsion angle is zero after the beam balance is installed.

[0005] Currently, the installation of beam balances and aircraft models is still a fully manual process, requiring a high level of skill from the installers. Due to the high precision requirements for beam balances, installers often need to make repeated adjustments to ensure the accuracy falls within the set range, which results in a significant time-consuming installation process. Furthermore, since the accuracy of beam balances and aircraft models is directly affected by the installer's skill level, achieving normalization of the accuracy error is difficult and is easily affected by human factors, which can lead to increased measurement errors.

[0006] Furthermore, when installing an aircraft model, it must be initially level, with no torsion and no sideslip. Since the beam balance is already in its initial level and sideslip state after installation, simply adjusting the torsion angle of the aircraft model to zero is sufficient. However, when using a traditional connection and positioning structure between the aircraft model and the beam balance, especially for aircraft with a large wingspan, errors in the torsion angle of the aircraft model can result in a height difference of 1mm to 2mm between the wingtips, ultimately affecting the accuracy of the measurement results and reducing the reliability of the test data. Summary of the Invention

[0007] In response to the problems existing in the prior art, the present invention provides a device and method for quickly installing a tail support of an aircraft model for wind tunnel testing, which realizes semi-automatic installation, with manual labor only serving as an auxiliary, greatly reducing the skill level requirements for installers, greatly shortening the installation time, significantly improving installation efficiency, reducing the influence of human factors, and achieving normalization of installation precision errors, effectively improving the accuracy of measurement results and the reliability of test data.

[0008] In order to achieve the above-mentioned purpose, the present invention adopts the following technical scheme: a rapid installation device for the tail support of an aircraft model for a wind tunnel test, comprising a scimitar bracket, an outer tail sleeve seat, an inner tail sleeve seat, an installation execution servo motor, a torsion angle adjustment hollow servo motor, an installation execution force transmission shaft, a torsion angle adjustment force transmission hollow rod and a rod-type balance; the scimitar bracket is fixedly installed in the test section of the wind tunnel; the outer tail sleeve seat is horizontally fixedly installed on the top of the scimitar bracket, the outer tail sleeve seat is coaxially sleeved on the outside of the inner tail sleeve seat, and the annular contact positioning surface between the outer tail sleeve seat and the inner tail sleeve seat is a conical surface; the rear end of the inner tail sleeve seat is threadedly connected with a tail sleeve seat fastening nut, and a fastening gasket is provided between the tail sleeve seat fastening nut and the outer tail sleeve seat; a positioning screw is fixedly installed between the front end of the outer tail sleeve seat and the front end of the inner tail sleeve seat; the installation execution servo motor is horizontally fixedly installed at the rear end of the outer tail sleeve seat, the installation execution servo motor and the outer tail sleeve seat are coaxially distributed, and the installation execution servo motor is fixedly installed at the rear end of the outer tail sleeve seat. The power output shaft is located in the outer tail sleeve seat; the torsion angle adjustment hollow servo motor is arranged horizontally, the outer stator of the torsion angle adjustment hollow servo motor is fixedly connected to the front end of the inner tail sleeve seat, and the torsion angle adjustment hollow servo motor and the inner tail sleeve seat are coaxially distributed; the rear end of the torsion angle adjustment force transmission hollow rod is fixedly connected to the inner rotor of the torsion angle adjustment hollow servo motor, and the torsion angle adjustment force transmission hollow rod and the torsion angle adjustment hollow servo motor are coaxially distributed; the installation execution force transmission shaft is coaxially installed on the inner side of the torsion angle adjustment force transmission hollow rod, the torsion angle adjustment hollow servo motor and the inner tail sleeve seat, and the rear end of the installation execution force transmission shaft is fixedly connected to the power output shaft of the installation execution servo motor through a coupling; the rod type balance is arranged horizontally, the rear end of the rod type balance is coaxially plug-fitted with the front end of the torsion angle adjustment force transmission hollow rod, the rear end of the rod type balance is coaxially threadedly connected with the front end of the installation execution force transmission shaft, and the front end of the rod type balance is used to fixedly connect the aircraft model.

[0009] A fairing is provided on the outside of the torsion angle adjustment hollow servo motor, the rear end of the fairing is coaxially fixedly connected to the front end of the inner tail sleeve seat, the front end of the fairing is coaxially sleeved on the torsion angle adjustment force transmission hollow rod, and the front end of the fairing is in sliding contact with the outer surface of the torsion angle adjustment force transmission hollow rod.

[0010] The rear end of the rod-type balance and the front end of the torsion angle adjustment force transmission hollow rod adopt a conical plug-in structure. A first plug-in positioning key is fixedly installed on the rear end plug-in surface of the rod-type balance, and a first plug-in positioning groove is provided on the front end plug-in surface of the torsion angle adjustment force transmission hollow rod. The first plug-in positioning key is plugged and positioned in cooperation with the first plug-in positioning groove.

[0011] A first transfer threaded hole is provided at the center of the rear end of the rod-type balance, and a transfer stud is processed at the front end of the installation execution force transmission shaft, and the transfer stud is threadedly connected and matched with the first transfer threaded hole.

[0012] A conical plug-in structure is adopted between the front end of the rod-type balance and the aircraft model. A second plug-in positioning key is fixedly installed on the front end plug-in surface of the rod-type balance, and a second plug-in positioning groove is provided on the plug-in surface of the aircraft model. The second plug-in positioning key is plugged and positioned with the second plug-in positioning groove.

[0013] A second transfer threaded hole is provided at the center of the front end of the rod-type balance, and a fastening screw is installed on the aircraft model, and the fastening screw is threadedly connected and matched with the second transfer threaded hole.

[0014] A first laser ranging sensor and a second laser ranging sensor are respectively installed directly below the wingtips on both sides of the aircraft model, and the first laser ranging sensor and the second laser ranging sensor are electrically connected to the wind tunnel main control computer; an aircraft model torsion angle adjustment indicator light is provided outside the wind tunnel, and the aircraft model torsion angle adjustment indicator light is electrically connected to the wind tunnel main control computer.

[0015] A method for quickly installing a tail support of an aircraft model for a wind tunnel test, using the aforementioned device for quickly installing a tail support of an aircraft model for a wind tunnel test, comprises the following steps:

[0016] Step 1: Select a beam balance according to the size of the aircraft model;

[0017] Step 2: Select the installation points of the first laser ranging sensor and the second laser ranging sensor according to the wing size of the aircraft model, and then complete the installation of the first laser ranging sensor and the second laser ranging sensor at the selected installation points so that the first laser ranging sensor and the second laser ranging sensor are respectively located directly below the wingtips on both sides of the aircraft model;

[0018] Step 3: Perform equal height adjustment on the installed first laser ranging sensor and the second laser ranging sensor. First, install a height gauge directly above the first laser ranging sensor and the second laser ranging sensor, adjust the two height gauges to the same height, and then use the first laser ranging sensor and the second laser ranging sensor to measure the distance of the two height gauges in the same height state. If the aircraft model torsion angle adjustment indicator light is on, it means that the first laser ranging sensor and the second laser ranging sensor have not reached the equal height setting requirement. It is necessary to fine-tune the height of the first laser ranging sensor and the second laser ranging sensor until the aircraft model torsion angle adjustment indicator light goes out, indicating that the first laser ranging sensor and the second laser ranging sensor have reached the equal height setting requirement.

[0019] Step 4: Set the thread tightening force of the servo motor in the wind tunnel main control computer;

[0020] Step 5: First, align and press the rear end of the rod balance with the front end of the torsion angle adjustment force transmission hollow rod, so that the first plug-in positioning key extends into the first plug-in positioning slot. At the same time, the opening of the first transfer threaded hole at the rear end of the rod balance and the column head of the transfer stud at the front end of the installation execution force transmission shaft are in abutment and docking state. Then, start the installation execution servo motor to drive the installation execution force transmission shaft to rotate, thereby screwing the transfer stud into the first transfer threaded hole and generating a backward pulling force on the rod balance along the axial direction until the thread tightening force of the installation execution servo motor reaches the set value. At this time, the fixed installation of the rod balance is completed;

[0021] Step 6: Zero the initial torsion angle of the beam balance. First, hang a weight at the front end of the beam balance as a counterweight to put the beam balance in a loaded state. At this time, the wind tunnel main control computer will automatically determine the initial torsion angle of the beam balance based on the measured value of the beam balance. If the initial torsion angle exceeds the error threshold, the torsion angle adjustment hollow servo motor will be started, and the inner rotor of the torsion angle adjustment hollow servo motor will sequentially drive the torsion angle adjustment force transmission hollow rod, the first plug-in positioning key and the beam balance to rotate until the initial torsion angle of the beam balance is within the error threshold. At this time, the initial torsion angle zeroing of the beam balance is completed.

[0022] Step 7: First, align the second plug-in positioning groove on the aircraft model with the second plug-in positioning key on the front end of the rod-type balance. Then, move the fuselage of the aircraft model axially so that the second plug-in positioning key is completely inserted into the second plug-in positioning groove. Then, screw the fastening screw into the second adapter threaded hole on the front end of the rod-type balance until the fastening screw is tightened. Then, assemble the nose and fuselage of the aircraft model together. At this time, the fixed installation of the aircraft model is completed.

[0023] Step 8: Zeroing the initial torsion angle of the aircraft model. First, start the first laser ranging sensor and the second laser ranging sensor. Then, the first laser ranging sensor and the second laser ranging sensor measure the height of the wingtips on both sides of the aircraft model. If the aircraft model torsion angle adjustment indicator light is on, it means that the height difference between the wingtips on both sides of the aircraft model exceeds the error threshold range. At this time, the initial torsion angle of the aircraft model is fine-tuned by tapping the wings until the aircraft model torsion angle adjustment indicator light goes out, indicating that the height difference between the wingtips on both sides of the aircraft model is within the error threshold range. At this time, the initial torsion angle of the aircraft model is zeroed.

[0024] Beneficial effects of the present invention:

[0025] The device and method for quickly installing a tail support of an aircraft model for wind tunnel testing of the present invention realize semi-automatic installation, with manual labor only serving as an auxiliary, greatly reducing the skill level requirements for installers, greatly shortening the installation time, significantly improving installation efficiency, reducing the influence of human factors, achieving normalization of installation precision errors, and effectively improving the accuracy of measurement results and the reliability of test data. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 This is a front view of a quick installation device for a tail support of an aircraft model for wind tunnel testing according to the present invention;

[0027] Figure 2 A top view of a quick installation device for a tail support of an aircraft model for wind tunnel testing according to the present invention;

[0028] Figure 3 This is a front view of a quick installation device for a tail support of an aircraft model for wind tunnel testing according to the present invention (when the torsion angle of the rod-type balance is zeroed);

[0029] Figure 4 for Figure 1 Enlarged view of middle part I;

[0030] Figure 5 for Figure 1 Enlarged view of middle part II;

[0031] In the figure, 1 is a scimitar bracket, 2 is an outer tail sleeve seat, 3 is an inner tail sleeve seat, 4 is an installation and execution servo motor, 5 is a torsion angle adjustment hollow servo motor, 6 is an installation and execution force transmission shaft, 7 is a torsion angle adjustment force transmission hollow rod, 8 is a rod-type balance, 9 is a wind tunnel, 10 is a tail sleeve seat fastening nut, 11 is a fastening gasket, 12 is a coupling, 13 is an aircraft model, 14 is a positioning screw, 15 is a fairing, 16 is a first plug-in positioning key, 17 is a first plug-in positioning groove, 18 is a first transfer threaded hole, 19 is a transfer stud, 20 is a second plug-in positioning key, 21 is a second plug-in positioning groove, 22 is a second transfer threaded hole, 23 is a fastening screw, 24 is a weight. DETAILED DESCRIPTION

[0032] The present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0033] like Figures 1 to 5 As shown, a quick installation device for the tail support of an aircraft model for a wind tunnel test comprises a scimitar bracket 1, an outer tail sleeve seat 2, an inner tail sleeve seat 3, an installation execution servo motor 4, a torsion angle adjustment hollow servo motor 5, an installation execution force transmission shaft 6, a torsion angle adjustment force transmission hollow rod 7 and a rod-type balance 8; the scimitar bracket 1 is fixedly installed in the test section of the wind tunnel 9; the outer tail sleeve seat 2 is horizontally fixedly installed on the top of the scimitar bracket 1, the outer tail sleeve seat 2 is coaxially sleeved on the outside of the inner tail sleeve seat 3, and the outer tail sleeve seat 2 is coaxial with the inner tail sleeve seat 3. The annular contact positioning surface between the sleeves 3 is a conical surface; the rear end of the inner tail sleeve seat 3 is threadedly connected with a tail sleeve seat fastening nut 10, and a fastening gasket 11 is provided between the tail sleeve seat fastening nut 10 and the outer tail sleeve seat 2; a positioning screw 14 is fixedly installed between the front end of the outer tail sleeve seat 2 and the front end of the inner tail sleeve seat 3; the installation execution servo motor 4 is horizontally fixed on the rear end of the outer tail sleeve seat 2, the installation execution servo motor 4 is coaxially distributed with the outer tail sleeve seat 2, and the power output shaft of the installation execution servo motor 4 Located in the outer tail sleeve seat 2; the torsion angle adjustment hollow servo motor 5 is arranged horizontally, the outer stator of the torsion angle adjustment hollow servo motor 5 is fixedly connected to the front end of the inner tail sleeve seat 3, and the torsion angle adjustment hollow servo motor 5 and the inner tail sleeve seat 3 are coaxially distributed; the rear end of the torsion angle adjustment force transmission hollow rod 7 is fixedly connected to the inner rotor of the torsion angle adjustment hollow servo motor 5, and the torsion angle adjustment force transmission hollow rod 7 and the torsion angle adjustment hollow servo motor 5 are coaxially distributed; the installation execution force transmission shaft 6 is coaxially installed on the torsion The rear end of the force transmission shaft 6 is installed and fixedly connected to the power output shaft of the servo motor 4 through a coupling 12 on the inner side of the hollow rod 7 for adjusting the rotation angle, the hollow servo motor 5 for adjusting the torsion angle, and the inner side of the inner tail sleeve seat 3; the rod-type balance 8 is arranged horizontally, and the rear end of the rod-type balance 8 is coaxially plugged with the front end of the hollow rod 7 for adjusting the torsion angle, and the rear end of the rod-type balance 8 is coaxially threaded with the front end of the force transmission shaft 6, and the front end of the rod-type balance 8 is used for fixed connection with the aircraft model 13.

[0034] A fairing 15 is provided on the outside of the torsion angle adjustment hollow servo motor 5. The rear end of the fairing 15 is coaxially fixedly connected to the front end of the inner tail sleeve seat 3. The front end of the fairing 15 is coaxially sleeved on the torsion angle adjustment force transmission hollow rod 7. The front end of the fairing 15 is in sliding contact with the outer surface of the torsion angle adjustment force transmission hollow rod 7.

[0035] The rear end of the rod-type balance 8 and the front end of the torsion angle adjustment force transmission hollow rod 7 adopt a conical cone plug-in structure. A first plug-in positioning key 16 is fixedly installed on the rear end plug-in surface of the rod-type balance 8, and a first plug-in positioning groove 17 is provided on the front end plug-in surface of the torsion angle adjustment force transmission hollow rod 7. The first plug-in positioning key 16 is plugged and positioned with the first plug-in positioning groove 17.

[0036] A first transfer threaded hole 18 is provided at the rear center of the rod-type balance 8 , and a transfer stud 19 is processed at the front end of the installation execution force transmission shaft 6 , and the transfer stud 19 is threadedly connected to the first transfer threaded hole 18 .

[0037] A conical plug-in structure is adopted between the front end of the rod-type balance 8 and the aircraft model 13. A second plug-in positioning key 20 is fixedly installed on the front end plug-in surface of the rod-type balance 8, and a second plug-in positioning groove 21 is provided on the plug-in surface of the aircraft model 13. The second plug-in positioning key 20 is plugged and positioned with the second plug-in positioning groove 21.

[0038] A second transfer threaded hole 22 is provided at the front center of the rod-type balance 8 , and a fastening screw 23 is installed on the aircraft model 13 , and the fastening screw 23 is threadedly connected and matched with the second transfer threaded hole 22 .

[0039] A first laser ranging sensor and a second laser ranging sensor are respectively installed directly below the wingtips on both sides of the aircraft model 13, and the first laser ranging sensor and the second laser ranging sensor are electrically connected to the wind tunnel main control computer; an aircraft model torsion angle adjustment indicator light is provided outside the wind tunnel 9, and the aircraft model torsion angle adjustment indicator light is electrically connected to the wind tunnel main control computer.

[0040] A method for quickly installing a tail support of an aircraft model for a wind tunnel test, using the aforementioned device for quickly installing a tail support of an aircraft model for a wind tunnel test, comprises the following steps:

[0041] Step 1: Select a beam balance 8 according to the size of the aircraft model 13. In this embodiment, the beam balance 8 is a φ24 six-component beam balance. The first adapter threaded hole 18 at the rear end and the second adapter threaded hole 22 at the front end of the beam balance 8 are both M8 threaded holes with a pitch of 1 mm.

[0042] Step 2: Select the installation points of the first laser ranging sensor and the second laser ranging sensor according to the wing size of the aircraft model 13, and then complete the installation of the first laser ranging sensor and the second laser ranging sensor at the selected installation points so that the first laser ranging sensor and the second laser ranging sensor are respectively located directly below the wingtips on both sides of the aircraft model 13;

[0043] Step 3: Perform equal height adjustment on the installed first laser ranging sensor and second laser ranging sensor. First, install a height gauge directly above each of the first laser ranging sensor and the second laser ranging sensor, and adjust the two height gauges to the same height. Then, the first laser ranging sensor and the second laser ranging sensor measure the distance of the two height gauges in the same height state. If the aircraft model torsion angle adjustment indicator light is on, it means that the first laser ranging sensor and the second laser ranging sensor have not met the equal height setting requirement. It is necessary to fine-tune the heights of the first laser ranging sensor and the second laser ranging sensor until the aircraft model torsion angle adjustment indicator light goes out, indicating that the first laser ranging sensor and the second laser ranging sensor have met the equal height setting requirement. In this embodiment, the equal height setting requirement for the first laser ranging sensor and the second laser ranging sensor is that the threshold value of the height difference between the two is not greater than 0.2 mm, and the threshold value of the height difference can be set in the wind tunnel main control computer.

[0044] Step 4: Setting the thread tightening force of the servo motor 4 in the wind tunnel main control computer; in this embodiment, the thread tightening force of the servo motor 4 can be determined to an optimal value by experimental testing;

[0045] Step 5: First, dock the rear end of the rod balance 8 with the front end of the torsion angle adjustment force transmission hollow rod 7, so that the first plug-in positioning key 16 extends into the first plug-in positioning groove 17, and at the same time, make the hole of the first transfer threaded hole 18 at the rear end of the rod balance 8 and the column head of the transfer stud 19 at the front end of the installation execution force transmission shaft 6 in a pressing and docking state, then start the installation execution servo motor 4, drive the installation execution force transmission shaft 6 to rotate, and then make the transfer stud 19 screw into the first transfer threaded hole 18 and generate a backward pulling force on the rod balance 8 along the axial direction until the thread tightening force of the installation execution servo motor 4 reaches the set value. At this time, the fixed installation of the rod balance 8 is completed;

[0046] Step 6: Zeroing the initial torsion angle of the beam balance 8. First, a weight 24 is hung on the front end of the beam balance 8 as a counterweight to put the beam balance 8 in a loaded state. At this time, the wind tunnel main control computer automatically determines the initial torsion angle of the beam balance 8 according to the measured value of the beam balance 8. If the initial torsion angle exceeds the error threshold, the torsion angle adjustment hollow servo motor 5 is started, and the torsion angle adjustment force transmission hollow rod 7, the first plug-in positioning key 16 and the beam balance 8 are driven in sequence by the inner rotor of the torsion angle adjustment hollow servo motor 5 to rotate until the initial torsion angle of the beam balance 8 is within the error threshold. At this time, the initial torsion angle zeroing of the beam balance 8 is completed. In this embodiment, the single angle adjustment amplitude of the inner rotor of the torsion angle adjustment hollow servo motor 5 is 1′. Normally, zeroing can be achieved after two to three adjustments of a single angle.

[0047] Step 7: First, align the second plug-in positioning groove 21 on the aircraft model 13 with the second plug-in positioning key 20 at the front end of the rod-type balance 8. Then, move the fuselage of the aircraft model 13 axially so that the second plug-in positioning key 20 is completely inserted into the second plug-in positioning groove 21. Then, screw the fastening screw 23 into the second transfer threaded hole 22 at the front end of the rod-type balance 8 until the fastening screw 23 is tightened. Then, assemble the nose and fuselage of the aircraft model 13 together. At this time, the fixed installation of the aircraft model 13 is completed.

[0048] Step 8: Zeroing the initial torsion angle of the aircraft model 13. First, the first laser ranging sensor and the second laser ranging sensor are activated. Then, the first laser ranging sensor and the second laser ranging sensor measure the height of the wingtips on both sides of the aircraft model 13. If the aircraft model torsion angle adjustment indicator light is on, it means that the height difference between the wingtips on both sides of the aircraft model 13 exceeds the error threshold range. At this time, the initial torsion angle of the aircraft model 13 is fine-tuned by tapping the wings until the aircraft model torsion angle adjustment indicator light goes out, indicating that the height difference between the wingtips on both sides of the aircraft model 13 is within the error threshold range. At this time, the initial torsion angle of the aircraft model 13 is zeroed. In this embodiment, each tapping of the wing can achieve an adjustment amount of about 0.2 mm. Under normal circumstances, zeroing can be achieved after two to three tappings.

[0049] The solutions in the embodiments are not intended to limit the scope of protection of the present invention. All equivalent implementations or modifications that do not depart from the scope of protection of the present invention are included in the scope of protection of the present invention.

Claims

1. A rapid installation device for a tail support of an aircraft model for wind tunnel testing, characterized by: The scimitar bracket comprises an outer tail sleeve seat, an inner tail sleeve seat, an installation execution servo motor, a torsion angle adjustment hollow servo motor, an installation execution force transmission shaft, a torsion angle adjustment force transmission hollow rod and a rod-type balance; the scimitar bracket is fixedly installed in the test section of the wind tunnel; the outer tail sleeve seat is horizontally fixedly installed on the top of the scimitar bracket, the outer tail sleeve seat is coaxially sleeved on the outside of the inner tail sleeve seat, and the annular contact positioning surface between the outer tail sleeve seat and the inner tail sleeve seat is a conical surface; the rear end of the inner tail sleeve seat is threadedly connected with a tail sleeve seat fastening nut, and a fastening gasket is provided between the tail sleeve seat fastening nut and the outer tail sleeve seat; a positioning screw is fixedly installed between the front end of the outer tail sleeve seat and the front end of the inner tail sleeve seat; the installation execution servo motor is horizontally fixedly installed at the rear end of the outer tail sleeve seat, the installation execution servo motor and the outer tail sleeve seat are coaxially distributed, and the power output shaft of the installation execution servo motor is located in the outer tail sleeve seat; the torsion angle adjustment The hollow servo motor is arranged horizontally, and the outer stator of the torsion angle adjustment hollow servo motor is fixedly connected to the front end of the inner tail sleeve seat, and the torsion angle adjustment hollow servo motor and the inner tail sleeve seat are coaxially distributed; the rear end of the torsion angle adjustment force transmission hollow rod is fixedly connected to the inner rotor of the torsion angle adjustment hollow servo motor, and the torsion angle adjustment force transmission hollow rod and the torsion angle adjustment hollow servo motor are coaxially distributed; the installation execution force transmission shaft is coaxially installed on the inner side of the torsion angle adjustment force transmission hollow rod, the torsion angle adjustment hollow servo motor and the inner tail sleeve seat, and the rear end of the installation execution force transmission shaft is fixedly connected to the power output shaft of the installation execution servo motor through a coupling; the rod type balance is arranged horizontally, and the rear end of the rod type balance is coaxially plug-fitted with the front end of the torsion angle adjustment force transmission hollow rod, and the rear end of the rod type balance is coaxially threadedly connected with the front end of the installation execution force transmission shaft, and the front end of the rod type balance is used to fixedly connect the aircraft model.

2. The rapid installation device for a tail support of an aircraft model for wind tunnel testing according to claim 1, characterized in that: A fairing is provided on the outside of the torsion angle adjustment hollow servo motor, the rear end of the fairing is coaxially fixedly connected to the front end of the inner tail sleeve seat, the front end of the fairing is coaxially sleeved on the torsion angle adjustment force transmission hollow rod, and the front end of the fairing is in sliding contact with the outer surface of the torsion angle adjustment force transmission hollow rod.

3. The rapid installation device for a tail support of an aircraft model for wind tunnel testing according to claim 1, characterized in that: The rear end of the rod-type balance and the front end of the torsion angle adjustment force transmission hollow rod adopt a conical plug-in structure. A first plug-in positioning key is fixedly installed on the rear end plug-in surface of the rod-type balance, and a first plug-in positioning groove is provided on the front end plug-in surface of the torsion angle adjustment force transmission hollow rod. The first plug-in positioning key is plugged and positioned in cooperation with the first plug-in positioning groove.

4. The rapid installation device for a tail support of an aircraft model for wind tunnel testing according to claim 1, characterized in that: A first transfer threaded hole is provided at the center of the rear end of the rod-type balance, and a transfer stud is processed at the front end of the installation execution force transmission shaft, and the transfer stud is threadedly connected and matched with the first transfer threaded hole.

5. The rapid installation device for a tail support of an aircraft model for wind tunnel testing according to claim 1, characterized in that: A conical plug-in structure is adopted between the front end of the rod-type balance and the aircraft model. A second plug-in positioning key is fixedly installed on the front end plug-in surface of the rod-type balance, and a second plug-in positioning groove is provided on the plug-in surface of the aircraft model. The second plug-in positioning key is plugged and positioned with the second plug-in positioning groove.

6. The rapid installation device for a tail support of an aircraft model for wind tunnel testing according to claim 1, characterized in that: A second transfer threaded hole is provided at the center of the front end of the rod-type balance, and a fastening screw is installed on the aircraft model, and the fastening screw is threadedly connected and matched with the second transfer threaded hole.

7. The rapid installation device for a tail support of an aircraft model for wind tunnel testing according to claim 1, characterized in that: A first laser ranging sensor and a second laser ranging sensor are respectively installed directly below the wingtips on both sides of the aircraft model, and the first laser ranging sensor and the second laser ranging sensor are electrically connected to the wind tunnel main control computer; an aircraft model torsion angle adjustment indicator light is provided outside the wind tunnel, and the aircraft model torsion angle adjustment indicator light is electrically connected to the wind tunnel main control computer.

8. A method for quickly installing a tail support of an aircraft model for a wind tunnel test, using the device for quickly installing a tail support of an aircraft model for a wind tunnel test according to claim 1, characterized in that: The steps include: Step 1: Select a beam balance according to the size of the aircraft model; Step 2: Select the installation points of the first laser ranging sensor and the second laser ranging sensor according to the wing size of the aircraft model, and then complete the installation of the first laser ranging sensor and the second laser ranging sensor at the selected installation points so that the first laser ranging sensor and the second laser ranging sensor are respectively located directly below the wingtips on both sides of the aircraft model; Step 3: Perform equal height adjustment on the installed first laser ranging sensor and the second laser ranging sensor. First, install a height gauge directly above the first laser ranging sensor and the second laser ranging sensor, adjust the two height gauges to the same height, and then use the first laser ranging sensor and the second laser ranging sensor to measure the distance of the two height gauges in the same height state. If the aircraft model torsion angle adjustment indicator light is on, it means that the first laser ranging sensor and the second laser ranging sensor have not reached the equal height setting requirement. It is necessary to fine-tune the height of the first laser ranging sensor and the second laser ranging sensor until the aircraft model torsion angle adjustment indicator light goes out, indicating that the first laser ranging sensor and the second laser ranging sensor have reached the equal height setting requirement. Step 4: Set the thread tightening force of the servo motor in the wind tunnel main control computer; Step 5: First, align and press the rear end of the rod balance with the front end of the torsion angle adjustment force transmission hollow rod, so that the first plug-in positioning key extends into the first plug-in positioning slot. At the same time, the opening of the first transfer threaded hole at the rear end of the rod balance and the column head of the transfer stud at the front end of the installation execution force transmission shaft are in abutment and docking state. Then, start the installation execution servo motor to drive the installation execution force transmission shaft to rotate, thereby screwing the transfer stud into the first transfer threaded hole and generating a backward pulling force on the rod balance along the axial direction until the thread tightening force of the installation execution servo motor reaches the set value. At this time, the fixed installation of the rod balance is completed; Step 6: Zero the initial torsion angle of the beam balance. First, hang a weight at the front end of the beam balance as a counterweight to put the beam balance in a loaded state. At this time, the wind tunnel main control computer will automatically determine the initial torsion angle of the beam balance based on the measured value of the beam balance. If the initial torsion angle exceeds the error threshold, the torsion angle adjustment hollow servo motor will be started, and the inner rotor of the torsion angle adjustment hollow servo motor will sequentially drive the torsion angle adjustment force transmission hollow rod, the first plug-in positioning key and the beam balance to rotate until the initial torsion angle of the beam balance is within the error threshold. At this time, the initial torsion angle zeroing of the beam balance is completed. Step 7: First, align the second plug-in positioning groove on the aircraft model with the second plug-in positioning key on the front end of the rod-type balance. Then, move the fuselage of the aircraft model axially so that the second plug-in positioning key is completely inserted into the second plug-in positioning groove. Then, screw the fastening screw into the second adapter threaded hole on the front end of the rod-type balance until the fastening screw is tightened. Then, assemble the nose and fuselage of the aircraft model together. At this time, the fixed installation of the aircraft model is completed. Step 8: Zeroing the initial torsion angle of the aircraft model. First, start the first laser ranging sensor and the second laser ranging sensor. Then, the first laser ranging sensor and the second laser ranging sensor measure the height of the wingtips on both sides of the aircraft model. If the aircraft model torsion angle adjustment indicator light is on, it means that the height difference between the wingtips on both sides of the aircraft model exceeds the error threshold range. At this time, the initial torsion angle of the aircraft model is fine-tuned by tapping the wings until the aircraft model torsion angle adjustment indicator light goes out, indicating that the height difference between the wingtips on both sides of the aircraft model is within the error threshold range. At this time, the initial torsion angle of the aircraft model is zeroed.

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