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

Abstract

The invention belongs to the technical field of hypersonic wind tunnel free flight tests, 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 arranged on the inner wall of the sleeve, a plurality of guide rails parallel to the central axis are fixed on the inner wall of the sleeve, the clamper is located in a central cavity of the sleeve and clamped on the guide rails, the front section clamps the test model, the rear end is connected with a clamper mounting seat, and the clamper mounting seat is fixedly connected with a piston rod of the launching device. The assembling method is rapid and convenient, and rapid assembling can be achieved; according to the clamping and releasing method, the test model can be stably released to the uniform flow field of the hypersonic wind tunnel without interference and freely flies; the test method is simple and reliable, and has good social benefits in combination with an existing test system. Technical support is provided for establishment and development of a hypersonic wind tunnel free flight test technology, the method can be expanded and applied to the technical field of other hypersonic wind tunnel special tests, and the method 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 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. 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. 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.

[0010] 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: Insert the ball into the ball mounting seat, with the upper part of the ball protruding from the ball mounting seat; 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; 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; 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.

[0011] 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; The clamping method includes the following steps: 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. The release method includes the following steps: When the launcher is launched, the launcher's piston rod pushes the gripper mounting seat to move rapidly from back to front, driving the gripper and test model to move rapidly from back to front. The gripper's ball bearings move linearly within the arc-section groove of the guide rail, reducing resistance through rolling friction and improving motion stability. At the same time, the arc-section groove provides a guiding function, preventing the gripper from rolling. When the compression spring extends out of the sleeve, the sleeve's restriction is removed, and the compression spring quickly rebounds the compression spring mounting seat, thereby rebounding the claw. At the same time, under the restriction of the limit block, the compression spring mounting seat is only rebounded and will not be ejected out of mounting hole I. After the claw rebounds, the constraint between the test model and the model adapter pad is released, and the test model continues to accelerate forward against the gripper. Due to the linear displacement restriction of the gripper, the test model separates from the gripper and is launched into the hypersonic wind tunnel test section at a pre-set initial velocity. After the claw rebounds to its maximum angle, it rebounds. The position of the compression spring mounting seat, which is rebounded by the compression spring, limits the claw's rebound angle, preventing the claw rebound from affecting the test model's posture and achieving interference-free release of the test model.

[0012] The test method of the clamping and releasing device for a hypersonic wind tunnel free flight test model of the present invention comprises the following steps: The test model is mounted on the launch device at a pre-set attack angle, and the clamp fixes the test model; The hypersonic wind tunnel is started. After the airflow stabilizes, high-pressure gas is used to drive the piston from back to front. The piston pushes the clamp from back to front. When the compression spring extends out of the sleeve, the clamp releases the model. The test model is launched into the hypersonic wind tunnel test section with a preset initial velocity and flies freely against the direction of the airflow. The test model flies against the airflow from the downstream of the observation area to the upstream of the observation area, and then flies with the airflow to the downstream of the observation area, obtaining the complete motion trajectory data of the free flight of the test model.

[0013] The clamping and releasing device and method for a hypersonic wind tunnel free flight test model of the present invention have the following characteristics: 1. A novel clamping and releasing method was designed. The test model is fixed in the sleeve by a compression spring, claws, and a model adapter pad on the clamp. The space constraints of the sleeve compress the compression spring. After the test model is installed, the compression spring maintains elastic force in the sleeve. When the test model is released, the elastic force of the compression spring provides the power to open the claws at the moment the compression spring exits the sleeve. 2. The test model is reliably clamped, capable of withstanding the strong impact during hypersonic wind tunnel startup. This prevents the test model from shaking and affecting its initial attitude during launch, thereby affecting its flight trajectory. This ensures the safety and reliability of the hypersonic wind tunnel model free flight test. 3. A novel anti-rebound structure has been designed to ensure reliable release of the test model. After the claw reaches its maximum angle, it rebounds in the opposite direction. At this time, the compression spring mounting seat has been ejected. The ejected compression spring mounting seat acts as a limiter for the claw's movement, effectively limiting the claw's rebound angle and preventing the claw's rebound from interfering with the test model and affecting its posture. 4. A new rolling guide structure is designed, in which a guide rail is installed on the sleeve and a ball is installed on the clamp. Since the clamp moves at a high speed, in order to avoid damage to mechanical parts during rapid movement of the clamp and to prevent jamming, most of the balls are buried in the ball mounting seat and a small part is buried in the guide rail. The balls move linearly along the guide rail, which reduces friction resistance and improves the reliability of the clamp movement.

[0014] The clamping and releasing device for a hypersonic wind tunnel free-flight test model of the present invention has a compact structure, a reasonable layout, and is stable and reliable. It is suitable for installation in a space-constrained environment and can meet the clamping and releasing requirements of a hypersonic wind tunnel free-flight test model. The assembly method for the clamping and releasing device for a hypersonic wind tunnel free-flight test model of the present invention is quick and convenient, and can achieve rapid assembly. The clamping and releasing method for a hypersonic wind tunnel free-flight test model of the present invention can stably and non-interference-release the test model into a uniform flow field of a hypersonic wind tunnel and allow it to fly freely. The test method for the clamping and releasing device for a hypersonic wind tunnel free-flight test model of the present invention is simple and reliable, and combined with the existing test system, has good social benefits.

[0015] The clamping and releasing device and method for a hypersonic wind tunnel free-flight test model of the present invention provide technical support for establishing and developing hypersonic wind tunnel free-flight test technology, and can also be expanded to other fields of special hypersonic wind tunnel test technology, and has engineering practical value. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 Schematic diagram of the structure of the clamping and releasing device for a hypersonic wind tunnel free flight test model according to the present invention; Figure 2a A schematic diagram (perspective view) of the structure of a clamp in a clamping and releasing device for a hypersonic wind tunnel free flight test model according to the present invention; Figure 2b Schematic diagram of the structure of the clamp in the clamping and releasing device for a hypersonic wind tunnel free flight test model according to the present invention (front view); Figure 2c Schematic diagram (cross-sectional view) of the structure of a clamp in a clamping and releasing device for a hypersonic wind tunnel free flight test model according to the present invention; Figure 3 This is a schematic structural diagram of a clamping claw mounting seat in a clamping and releasing device for a hypersonic wind tunnel free flight test model according to the present invention; Figure 4 Schematic diagram of the sleeve structure of the clamping and releasing device for a hypersonic wind tunnel free flight test model according to the present invention; Figure 5 Schematic diagram of the structure of the limit block in the clamping and releasing device for a hypersonic wind tunnel free flight test model according to the present invention; Figure 6 The figure is a schematic structural diagram of a compression spring mounting seat in a clamping and releasing device for a hypersonic wind tunnel free flight test model according to the present invention.

[0017] In the figure, 1. Test model; 2. Sleeve; 3. Guide rail; 4. Clamp; 5. Clamp mounting base; 401. Claw; 402. Model adapter pad; 403. Ball; 404. Ball mounting seat; 405. Compression spring mounting seat; 406. Compression spring; 407. Pin; 408. Clamping claw mounting seat; 409. Limit block; 410. Mounting hole I; 411. Limit block mounting surface; 412. Mounting hole II. DETAILED DESCRIPTION

[0018] The present invention will be described in detail below with reference to the accompanying drawings and embodiments.

[0019] Example: Figure 1 、 Figure 2a to Figure 2c 、 Figures 3 to 6 As shown, the clamping and releasing device for a hypersonic wind tunnel free flight test model of this embodiment includes a sleeve 2, a guide rail 3, a clamp 4 and a clamp mounting seat 5. Several guide rails 3 parallel to the central axis are fixed to the inner wall of the sleeve 2. A 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 base 5, which 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. 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 to the lower surface, and a ball mounting seat 404 is fixed to the upper surface. The ball mounting seat 404 is embedded with a ball 403. The upper part of the ball 403 protrudes from the ball mounting seat 404 and is embedded in the arc-section groove of the guide rail 3. The upper part of the ball 403 is smaller than the lower part 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, and the compression spring mounting seat 405 is embedded in the mounting hole I 410. The 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, and a limit block 409 is installed on the limit block mounting surface 411, and the two limit blocks 409 are distributed on both sides of the claw 401.

[0020] The assembly method of the clamping and releasing device for a hypersonic wind tunnel free flight test model of this embodiment includes the following steps: The ball 403 is inserted into the ball mounting seat 404 , and the upper portion of the ball 403 protrudes from the ball mounting seat 404 ; The model adapter 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; Place the compression spring 406 in the mounting hole II 412 of the compression spring mounting seat 405, and then place the compression spring mounting seat 405 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 mounting hole II 412 along the radial direction of the clamp 4 to compress the compression spring 406; Install the claw 401 on the clamping claw mounting seat 408 through the pin 407. After pressing the claw 401 to a horizontal position, install the limit block 409 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 to pop out of the mounting hole Ⅰ410.

[0021] The clamping and releasing method for a hypersonic wind tunnel free flight test model of this embodiment 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 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; 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 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.

[0022] 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: The test model 1 is mounted on the launch device at a preset attack angle, and the clamp 4 fixes the test model 1; 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.

[0023] 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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