Clamping and releasing device and method for hypersonic wind tunnel free flight test model

Abstract

The present application belongs to the technical field of hypersonic wind tunnel free flight test, and particularly relates to a clamping and releasing device and method for a hypersonic wind tunnel free flight test model. The clamping and releasing device is fixed with a plurality of guide rails parallel to the central axis on the inner wall of the sleeve. The clamp is located in the central cavity of the sleeve and is clamped on the guide rail. The front section clamps the test model, and the rear end is connected with the clamp mounting seat. The clamp mounting seat is fixedly connected with the piston rod of the launching device. The assembly method is quick and convenient, and can realize quick assembly. The clamping and releasing method can stably and non-interferingly drop the test model into the uniform flow field of the hypersonic wind tunnel and make it fly freely. The test method is simple and reliable, and has good social benefits in combination with the existing test system. The present application provides technical support for the establishment and development of hypersonic wind tunnel free flight test technology, can be applied to other hypersonic wind tunnel special test technology fields, and has engineering practical value.

Description

Technical Field

[0001] The present invention belongs to the technical field of hypersonic wind tunnel free flight tests, and in particular relates to a clamping and releasing device and method for a hypersonic wind tunnel free flight test model. Background Art

[0002] As hypersonic vehicles expand their flight envelope, maneuvering at high angles of attack and with sideslip is becoming possible. The nonlinear flow phenomena that arise during maneuvering have a significant impact on the dynamic stability of hypersonic vehicles. To predict the dynamic characteristics of hypersonic vehicles, it is necessary to establish a dynamic model and obtain dynamic stability derivatives. This is a crucial prerequisite and foundation for hypersonic vehicle control system design, flight quality evaluation, and ground simulation.

[0003] Research on the dynamic stability of hypersonic vehicles currently relies primarily on flight tests and wind tunnel simulations. Wind tunnel simulations can be divided into two categories: one with a constrained model and the other with a free-flight model. In the case of a constrained model, interference from the support system is noticeable and difficult to eliminate, significantly impacting the test results. In contrast, free-flight wind tunnel models offer the advantages of no support interference and no mechanical damping. This ensures a more realistic dynamic similarity between wind tunnel simulations and flight conditions, allowing for a more realistic reproduction of the dynamic aerodynamic characteristics of a hypersonic vehicle in continuous motion.

[0004] The free flight test of a wind tunnel model is to place the test model into the uniform flow field of the wind tunnel in some way, allowing the test model to fly freely. At the same time, a high-speed camera method is used to record in real time an image sequence of the test model's posture changing with time. The image sequence is then interpreted to obtain data on the test model's posture changing with time, that is, the motion trajectory. Then, based on the mass characteristic parameters and motion trajectory data of the test model, the aerodynamic force of the test model is calculated. Through qualitative or quantitative analysis, the aerodynamic characteristic parameters of the test model in the flow field are obtained.

[0005] Wind tunnel model free-flight tests offer advantages over conventional wind tunnel force and pressure tests, lacking support interference. Compared to wind tunnel tests measuring dynamic characteristics such as ball (pitch and yaw) damping and Magnus forces, they lack support interference and mechanical damping. However, in hypersonic wind tunnel testing, the impact of support interference cannot be ignored, and its impact on dynamic measurements is even more severe than on static measurements. The results of wind tunnel model free-flight tests can provide a reference for designing field free-flight tests of aircraft, providing important aerodynamic parameters for developing overall plans and verifying the rationality of aerodynamic layouts. This ensures the safety and reliability of field model free-flight tests and lays a solid foundation for hypersonic aircraft flight testing.

[0006] Conduct free flight tests of wind tunnel models. When the hypersonic wind tunnel is started, strong airflow will have a strong impact on the test model and mechanisms in the test section. At this time, the clamping and releasing device must ensure that the test model is reliably supported and does not shake. When launching the test model, the clamping and releasing device must ensure that the separation time from the test model is as short as possible, and must not collide with the test model during and after the release, which will interfere with the free flight of the test model.

[0007] The clamping and releasing technology of test models is one of the key technologies that need to be mastered in wind tunnel model free-flight tests. Currently, there is an urgent need to develop a clamping and releasing device and method for hypersonic wind tunnel free-flight test models. Summary of the Invention

[0008] The first technical problem to be solved by the present invention is to provide a clamping and releasing device for a hypersonic wind tunnel free flight test model, the second technical problem to be solved is to provide an assembly method for a clamping and releasing device for a hypersonic wind tunnel free flight test model, the third technical problem to be solved is to provide a clamping and releasing method for a hypersonic wind tunnel free flight test model, and the third technical problem to be solved is to provide a testing method for a clamping and releasing device for a hypersonic wind tunnel free flight test model.

[0009] The clamping and releasing device for a hypersonic wind tunnel free flight test model of the present invention comprises a sleeve, a guide rail, a clamp and a clamp mounting seat

[0010] Several guide rails parallel to the central axis are fixed on the inner wall of the sleeve. The clamp is located in the central cavity of the sleeve and is clamped on the guide rails. The front end of the clamp clamps the test model, and the rear end of the clamp is connected to the clamp mounting base, which is fixedly connected to the piston rod of the launch device.

[0011] The main body of the clamp is a clamping claw mounting seat. Several claws suspended from the back to the front are fixed by pins around the clamping claw mounting seat. At the front end of the claw, a model adapter pad is fixed on the lower surface, and a ball mounting seat is fixed on the upper surface. The ball mounting seat is embedded in the ball, and the upper part of the ball protrudes from the ball mounting seat and is embedded in the arc-section groove of the guide rail. The upper height of the ball is less than the lower height of the ball.

[0012] A mounting hole I is provided at the contact surface between the clamping claw mounting seat and the rear section of the claw, and a compression spring mounting seat is embedded in the mounting hole I. A compression spring is placed in the mounting hole II of the compression spring mounting seat, and the contact end surface between the compression spring mounting seat and the rear section of the claw is closed as a closed end; a limit block mounting surface is also provided at the contact surface, and a limit block is installed on the limit block mounting surface, and the two limit blocks are distributed on both sides of the claw.

[0013] The assembly method of the clamping and releasing device for a hypersonic wind tunnel free flight test model of the present invention comprises the following steps:

[0014] Insert the ball into the ball mounting seat, with the upper part of the ball protruding from the ball mounting seat;

[0015] The model adapter pad is mounted on the lower surface of the claw, and the ball mount is mounted on the upper surface of the claw;

[0016] Place the compression spring in mounting hole II of the compression spring mounting seat, and then place the compression spring mounting seat in mounting hole I, with the open end of the compression spring mounting seat facing the central axis of the clamp and the closed end facing the claw; the height of the compression spring mounting seat is less than the depth of mounting hole II, and the compression spring mounting seat moves in the radial direction of the clamp in mounting hole II to achieve compression of the compression spring;

[0017] Install the claw on the clamping claw mounting seat through the pin, press the claw to the horizontal level, and then install the limit block on the limit block mounting surface. The two limit blocks are distributed on both sides of the claw. The limit blocks limit the height of the compression spring mounting seat to pop out of the mounting hole Ⅰ.

[0018] The clamping and releasing method for a hypersonic wind tunnel free flight test model of the present invention comprises a clamping method and a releasing method;

[0019] The clamping method includes the following steps:

[0020] After the gripper is assembled, pull the gripper mounting base to the exit edge of the sleeve and install the gripper on the gripper mounting base. Then, insert the test model into the gripper from front to back, and press the claws to make the model adapter pad fit the test model. At this time, the compression spring is compressed to generate elastic force. Then, push the test model, gripper, and gripper mounting base into the sleeve from front to back until the bottom of the sleeve. When pushing, ensure that the ball enters the arc section groove of the guide rail. The compression spring is restricted by the sleeve and always maintains elastic force inside the sleeve. The claws and model adapter pad clamp and fix the test model.

[0021] The release method includes the following steps:

[0022] When the launching device is launched, the piston rod of the launching device pushes the gripper mounting seat to move quickly from back to front, and drives the gripper and the test model to move quickly from back to front; the ball of the gripper moves linearly in the arc section chute of the guide rail, the resistance is reduced through rolling friction, and the movement stability is improved, at the same time, the arc section chute has a guiding effect, and prevents the gripper from rolling; when the compression spring extends out of the sleeve, the compression spring is quickly bounced up due to the disappearance of the limitation of the sleeve, so that the claw is opened, and under the limitation of the limiting block, the compression spring mounting seat is only bounced up, and will not be bounced out of the mounting hole I; after the claw is opened, the constraint relationship between the test model and the model fitting pad is released, the test model continues to accelerate forward movement closely to the gripper, and the test model is separated from the gripper due to the linear displacement limitation of the gripper, and the test model is launched to the hypersonic wind tunnel test section at a pre-set initial speed; the claw is bounced back after being opened to the maximum angle, the position of the compression spring mounting seat bounced up by the compression spring limits the angle of the claw bounce back, avoids the influence of the claw bounce back on the posture of the test model, and realizes the release of the test model without interference.

[0023] The test method of the holding and releasing device for the hypersonic wind tunnel free flight test model of the application comprises the following processes:

[0024] The test model is installed on the launching device at a pre-set attack angle, and the gripper fixes the test model;

[0025] The hypersonic wind tunnel is started, and after the airflow is stabilized, the piston is driven to move from back to front in a high-pressure gas driving mode, the piston drives the gripper to move from back to front, the gripper releases the model after the compression spring extends out of the sleeve, the test model is launched to the hypersonic wind tunnel test section at a pre-set initial speed, flies freely in the opposite direction of the airflow, realizes the test model from flying in the opposite direction of the airflow to the upstream of the observation area to flying in the airflow to the downstream of the observation area, and obtains all the motion trajectory data of the free flight of the test model.

[0026] The holding and releasing device and method for the hypersonic wind tunnel free flight test model of the application have the following characteristics:

[0027] 1. A new type of holding and releasing method is designed; the test model is fixed in the sleeve through the compression spring, the claw and the model fitting pad on the gripper, the space limitation of the sleeve makes the compression spring be compressed, the compression spring maintains the elastic force in the sleeve after the test model is installed, and the elastic force of the compression spring provides the power for opening the claw at the moment when the compression spring is out of the sleeve;

[0028] 2. The test model is clamped reliably, can withstand the strong impact during the start of the hypersonic wind tunnel, avoids the shaking of the test model, affects the initial attitude of the test model during the launch, thereby affecting the flight trajectory, and ensures the safety and reliability of the hypersonic wind tunnel model free flight test;

[0029] 3. A new anti-rebound structure is designed to ensure the reliable release of the test model; when the claw reaches the maximum angle and rebounds in the opposite direction, the compressed spring mounting seat has been lifted, the lifted compressed spring mounting seat serves as a limiting component for the claw movement, can effectively limit the rebound angle of the claw, and avoids the interference between the claw rebound and the test model, affecting the attitude of the test model;

[0030] 4. A new rolling guide structure is designed, the rolling guide structure is provided with a guide rail on the sleeve and a ball on the clamp; since the clamp moves at a high speed, in order to avoid the damage of mechanical components during the rapid movement of the clamp and prevent the jamming phenomenon, the ball is mostly embedded in the ball mounting seat, and a small part is embedded in the guide rail, the ball moves linearly along the guide rail, the frictional resistance is reduced, and the reliability of the movement of the clamp is improved.

[0031] The clamping and releasing device for the hypersonic wind tunnel free flight test model is compact in structure, reasonable in layout, stable and reliable, is suitable for being installed in a space-limited environment, and can meet the clamping and releasing requirements of the hypersonic wind tunnel model free flight test model; the assembly method of the clamping and releasing device for the hypersonic wind tunnel free flight test model is rapid and convenient, and can realize rapid assembly; the clamping and releasing method for the hypersonic wind tunnel free flight test model can stably and non-interferingly drop the test model into the uniform flow field of the hypersonic wind tunnel and make the test model fly freely; the test method of the clamping and releasing device for the hypersonic wind tunnel free flight test model is simple and reliable, has good social benefits in combination with the existing test system.

[0032] The clamping and releasing device and method for the hypersonic wind tunnel free flight test model provide technical support for the establishment and development of the hypersonic wind tunnel free flight test technology, can be applied to other hypersonic wind tunnel special test technology fields, and have engineering practical value. BRIEF DESCRIPTION OF DRAWINGS

[0033] Figure 1 Fig. 1 is a structural schematic view of the clamping and releasing device for the hypersonic wind tunnel free flight test model;

[0034] Figure 2a Fig. 3 is a structural schematic view (perspective view) of the clamp in the clamping and releasing device for the hypersonic wind tunnel free flight test model;

[0035] Figure 2bThe schematic view (front view) of the gripper structure in the holding and releasing device for the hypersonic wind tunnel free-flight test model of the present application;

[0036] Figure 2c The schematic view (cross-sectional view) of the gripper structure in the holding and releasing device for the hypersonic wind tunnel free-flight test model of the present application;

[0037] Figure 3 The schematic view of the gripper mounting seat structure in the holding and releasing device for the hypersonic wind tunnel free-flight test model of the present application;

[0038] Figure 4 The schematic view of the sleeve structure in the holding and releasing device for the hypersonic wind tunnel free-flight test model of the present application;

[0039] Figure 5 The schematic view of the limiting block structure in the holding and releasing device for the hypersonic wind tunnel free-flight test model of the present application;

[0040] Figure 6 The schematic view of the compressed spring mounting seat structure in the holding and releasing device for the hypersonic wind tunnel free-flight test model of the present application.

[0041] In the figure, 1. test model; 2. sleeve; 3. guide rail; 4. gripper; 5. gripper mounting seat;

[0042] 401. claw; 402. model fitting pad; 403. ball; 404. ball mounting seat; 405. compressed spring mounting seat; 406. compressed spring; 407. pin; 408. gripper mounting seat; 409. limiting block; 410. mounting hole I; 411. limiting block mounting face; 412. mounting hole II. DETAILED DESCRIPTION

[0043] The present application will be described in detail below with reference to the accompanying drawings and examples.

[0044] Example: as shown in Figure 1 , Figure 2a to Figure 2c , Figures 3 to 6 The holding and releasing device for the hypersonic wind tunnel free-flight test model of the present embodiment comprises a sleeve 2, a guide rail 3, a gripper 4 and a gripper mounting seat 5

[0045] On the inner wall of the sleeve 2, a plurality of guide rails 3 parallel to the central axis are fixed, the gripper 4 is located in the central cavity of the sleeve 2 and clamped on the guide rails 3; the front section of the gripper 4 holds the test model 1, the rear end of the gripper 4 is connected to the gripper mounting seat 5, and the gripper mounting seat 5 is fixedly connected to the piston rod of the launching device;

[0046] The main body of the gripper 4 is a gripper jaw mounting seat 408, and a plurality of rear-to-front overhanging claws 401 are fixed on the circumference of the gripper jaw mounting seat 408 through a pin 407; at the front end of the claw 401, a model adaptive pad 402 is fixed on the lower surface, and a ball mounting seat 404 is fixed on the upper surface, the ball mounting seat 404 is embedded with a ball 403, the upper part of the ball 403 protrudes out of the ball mounting seat 404 and is embedded into the arc cross-section sliding groove of the guide rail 3; the height of the upper part of the ball 403 is less than the height of the lower part of the ball 403;

[0047] An installation hole I 410 is arranged at the contact surface between the gripper jaw mounting seat 408 and the rear segment of the claw 401, a compression spring mounting seat 405 is embedded in the installation hole I 410, a compression spring 406 is placed in the installation hole II 412 of the compression spring mounting seat 405, and the contact end surface of the compression spring mounting seat 405 and the rear segment of the claw 401 is closed as a closed end; a limiting block mounting surface 411 is further arranged at the contact surface, and a limiting block 409 is mounted on the limiting block mounting surface 411, and the two limiting blocks 409 are distributed on the two sides of the claw 401.

[0048] The assembly method of the holding and releasing device for the hypersonic wind tunnel free flight test model of the embodiment comprises the following processes:

[0049] The ball 403 is embedded into the ball mounting seat 404, and the upper part of the ball 403 protrudes out of the ball mounting seat 404;

[0050] The model adaptive pad 402 is mounted on the lower surface of the claw 401, and the ball mounting seat 404 is mounted on the upper surface of the claw 401;

[0051] The compression spring 406 is placed in the installation hole II 412 of the compression spring mounting seat 405, and then the compression spring mounting seat 405 is placed in the installation hole I 410, the open end of the compression spring mounting seat 405 faces the central axis of the gripper 4, and the closed end faces the claw 401; the height of the compression spring mounting seat 405 is less than the depth of the installation hole II 412, the compression spring mounting seat 405 moves in the radial direction of the gripper 4 in the installation hole II 412, and the compression spring 406 is compressed;

[0052] The claw 401 is mounted on the gripper jaw mounting seat 408 through the pin 407, the claw 401 is pressed to be horizontal, the limiting block 409 is mounted on the limiting block mounting surface 411, and the two limiting blocks 409 are distributed on the two sides of the claw 401, and the limiting block 409 limits the height of the compression spring mounting seat 405 from the installation hole I 410.

[0053] The holding and releasing method for the hypersonic wind tunnel free flight test model of the embodiment comprises a holding method and a releasing method;

[0054] The holding method comprises the following processes:

[0055] After the clamp 4 is assembled, the clamp mounting seat 5 is pulled to the exit edge of the sleeve 2, and the clamp 4 is mounted on the clamp mounting seat 5; then the test model 1 is inserted into the clamp 4 from front to back, and the claws 401 are pressed so that the model adapter pad 402 fits the test model 1; at this time, the compression spring 406 is compressed to generate elastic force, and then the test model 1, the clamp 4 and the clamp mounting seat 5 are pushed into the sleeve 2 from front to back until the bottom of the sleeve 2, and when pushing, ensure that the ball 403 enters the arc cross-section groove of the guide rail 3; the compression spring 406 is restricted by the sleeve 2 and always maintains elastic force in the sleeve 2, and the claws 401 and the model adapter pad 402 clamp and fix the test model 1;

[0056] The release method includes the following steps:

[0057] When the launch device is launched, the piston rod of the launch device pushes the clamp mounting seat 5 to move rapidly from back to front, driving the clamp 4 and the test model 1 to move rapidly from back to front; the ball 403 of the clamp 4 moves linearly in the arc cross-section groove of the guide rail 3, reducing resistance by rolling friction and improving movement stability. At the same time, the arc cross-section groove has a guiding effect to prevent the clamp 4 from rolling; when the compression spring 406 extends out of the sleeve 2, the restriction of the sleeve 2 disappears, and the compression spring 406 quickly bounces up the compression spring mounting seat 405, thereby bouncing the claw 401 open. At the same time, under the restriction of the limit block 409, the compression spring mounting seat 40 5 will only be bounced up, and will not be ejected from the mounting hole I 410; after the claw 401 bounces off, the constraint relationship between the test model 1 and the model adapter pad 402 is released, and the test model 1 continues to accelerate forward close to the clamp 4. Due to the linear displacement restriction of the clamp 4, the test model 1 is separated from the clamp 4, and the test model 1 is launched into the hypersonic wind tunnel test section at a preset initial velocity; the claw 401 rebounds after being opened to the maximum angle, and the compression spring mounting seat 405 is pushed up by the compression spring 406, which limits the rebound angle of the claw 401, preventing the rebound of the claw 401 from affecting the posture of the test model 1, and realizing the interference-free release of the test model 1.

[0058] The test method of the clamping and releasing device for a hypersonic wind tunnel free flight test model of this embodiment includes the following steps:

[0059] The test model 1 is mounted on the launch device at a preset attack angle, and the clamp 4 fixes the test model 1;

[0060] After the hypersonic wind tunnel is started and the airflow stabilizes, high-pressure gas is used to drive the piston from back to front. The piston pushes the clamp 4 from back to front. When the compression spring 406 extends out of the sleeve 2, the clamp 4 releases the model, and the test model 1 is launched into the hypersonic wind tunnel test section at a preset initial velocity. It flies freely against the direction of the airflow, and the test model 1 flies from the downstream of the observation area against the airflow to the upstream of the observation area, and then flies with the airflow to the downstream of the observation area, thereby obtaining the complete motion trajectory data of the free flight of the test model 1.

[0061] Although the embodiments of the present invention have been disclosed as above, they are not limited to the applications listed in the description and implementation methods. For those familiar with the art, all features disclosed in the present invention, or all steps in the disclosed methods or processes, except for mutually exclusive features and / or steps, can be combined in any way without departing from the principles of the present invention. The present invention is not limited to the specific details and illustrations shown and described herein.

Claims

1. A clamping and releasing device for a hypersonic wind tunnel free flight test model, characterized in that: The clamping and releasing device comprises a sleeve (2), a guide rail (3), a clamp (4) and a clamp mounting seat (5). A plurality of guide rails (3) parallel to the central axis are fixed on the inner wall of the sleeve (2); the clamp (4) is located in the central cavity of the sleeve (2) and is clamped on the guide rails (3); the front end of the clamp (4) clamps the test model (1), and the rear end of the clamp (4) is connected to the clamp mounting seat (5), and the clamp mounting seat (5) is fixedly connected to the piston rod of the launch device; The main body of the clamp (4) is a clamping claw mounting seat (408), and a plurality of claws (401) suspended from the back to the front are fixed by pins (407) in the circumference of the clamping claw mounting seat (408); at the front end of the claw (401), a model adapter pad (402) is fixed on the lower surface, and a ball mounting seat (404) is fixed on the upper surface, and a ball (403) is embedded in the ball mounting seat (404), and the upper part of the ball (403) protrudes from the ball mounting seat (404) and is embedded in the arc cross-section groove of the guide rail (3); the upper part height of the ball (403) is less than the lower part height of the ball (403); A mounting hole I (410) is provided at the contact surface between the clamping claw mounting seat (408) and the rear section of the claw (401), a compression spring mounting seat (405) is embedded in the mounting hole I (410), a compression spring (406) is placed in the mounting hole II (412) of the compression spring mounting seat (405), and the contact end surface between the compression spring mounting seat (405) and the rear section of the claw (401) is closed as a closed end; a limit block mounting surface (411) is also provided at the contact surface, a limit block (409) is installed on the limit block mounting surface (411), and two limit blocks (409) are distributed on both sides of the claw (401).

2. A clamping and releasing method for a hypersonic wind tunnel free flight test model, which is used for the clamping and releasing device for a hypersonic wind tunnel free flight test model according to claim 1, characterized in that: The method is a method for assembling a clamping and releasing device for a hypersonic wind tunnel free flight test model. The following processes are included: The ball (403) is embedded in the ball mounting seat (404), and the upper portion of the ball (403) protrudes from the ball mounting seat (404); The model adapting pad (402) is mounted on the lower surface of the claw (401), and the ball mounting seat (404) is mounted on the upper surface of the claw (401); The compression spring (406) is placed in the mounting hole II (412) of the compression spring mounting seat (405), and then the compression spring mounting seat (405) is placed in the mounting hole I (410), with the open end of the compression spring mounting seat (405) facing the central axis of the clamp (4) and the closed end facing the claw (401); the height of the compression spring mounting seat (405) is less than the depth of the mounting hole II (412), and the compression spring mounting seat (405) moves in the radial direction of the clamp (4) in the mounting hole II (412) to achieve compression of the compression spring (406); The claw (401) is mounted on the clamping claw mounting seat (408) through the pin (407). After the claw (401) is pressed to a horizontal position, a limit block (409) is mounted on the limit block mounting surface (411). The two limit blocks (409) are distributed on both sides of the claw (401). The limit blocks (409) limit the height of the compression spring mounting seat (405) popping out of the mounting hole I (410).

3. A clamping and releasing method for a hypersonic wind tunnel free flight test model, which is used for the clamping and releasing device for a hypersonic wind tunnel free flight test model according to claim 1, characterized in that: The clamping and releasing method includes a clamping method and a releasing method; The clamping method includes the following steps: After the clamp (4) is assembled, the clamp mounting seat (5) is pulled to the exit edge of the sleeve (2), and the clamp (4) is mounted on the clamp mounting seat (5); then the test model (1) is inserted into the clamp (4) from front to back, and the claw (401) is pressed so that the model adapter pad (402) fits the test model (1); at this time, the compression spring (406) is compressed to generate elastic force, and then the test model (1), the clamp (4) and the clamp mounting seat (5) are pushed into the sleeve (2) from front to back until the bottom of the sleeve (2), and when pushing in, it is ensured that the ball (403) enters the arc section groove of the guide rail (3); the compression spring (406) is restricted by the sleeve (2) and always maintains elastic force in the sleeve (2), and the claw (401) and the model adapter pad (402) clamp and fix the test model (1); The release method includes the following steps: When the launch device is launched, the piston rod of the launch device pushes the clamp mounting seat (5) to move rapidly from back to front, driving the clamp (4) and the test model (1) to move rapidly from back to front; the ball (403) of the clamp (4) moves linearly in the arc cross-section groove of the guide rail (3), reducing resistance through rolling friction and improving movement stability. At the same time, the arc cross-section groove has a guiding function to prevent the clamp (4) from rolling; when the compression spring (406) extends out of the sleeve (2), the restriction of the sleeve (2) disappears, and the compression spring (406) quickly bounces up the compression spring mounting seat (405), thereby bouncing the claw (401) open. At the same time, under the restriction of the limit block (409), the compression spring mounting seat (405) can only will be bounced up and will not be ejected from the mounting hole I (410); after the claw (401) is ejected, the constraint relationship between the test model (1) and the model adapter pad (402) is released, and the test model (1) is close to the clamp (4) and continues to accelerate forward. Due to the linear displacement limitation of the clamp (4), the test model (1) is separated from the clamp (4), and the test model (1) is launched into the hypersonic wind tunnel test section at a preset initial velocity; the claw (401) rebounds after being ejected to the maximum angle, and the compression spring mounting seat (405) is ejected from the position of the compression spring (406), which limits the rebound angle of the claw (401), avoids the rebound of the claw (401) affecting the posture of the test model (1), and realizes the interference-free release of the test model (1).

4. A clamping and releasing method for a hypersonic wind tunnel free flight test model, which is used for the clamping and releasing device for a hypersonic wind tunnel free flight test model according to claim 1, characterized in that: The method is a test method for a clamping and releasing device for a hypersonic wind tunnel free flight test model, comprising the following steps: The test model (1) is mounted on the launch device at a preset attack angle, and the clamp (4) fixes the test model (1); The hypersonic wind tunnel is started, and after the airflow stabilizes, the piston is driven by high-pressure gas to move from the back to the front. The piston pushes the clamp (4) to move from the back to the front. When the compression spring (406) extends out of the sleeve (2), the clamp (4) releases the model. The test model (1) is launched into the hypersonic wind tunnel test section at a preset initial velocity and flies freely against the direction of the airflow. The test model (1) flies against the airflow from the downstream of the observation area to the upstream of the observation area, and then flies along the airflow to the downstream of the observation area, thereby obtaining all the motion trajectory data of the free flight of the test model (1).

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