An anti-deformation simulation test device for rocket thrust components

Abstract

The present invention discloses an anti-deformation simulation test device for rocket thrust components, which belongs to the field of thrust component detection technology. The device comprises a simulated wind tunnel detonation chamber and a simulation test chamber for conducting simulation tests on a nozzle. The inner side wall of the simulation test chamber is connected to a chamber pressure adjustment chamber via two mounting plates. The inner side wall of the chamber pressure adjustment chamber is connected to a plurality of arc-shaped spray hoods. The end of the chamber pressure adjustment chamber is connected to a limit assembly for mounting the nozzle head. The outer side of the nozzle tail is provided with a plurality of protective baffles. The present invention, through the provision of a liquid damping assembly and a vibration expansion plate, can achieve nonlinear damping through the variable cross-section design of the liquid damping channel in the low amplitude stage. In the high amplitude critical state, the self-locking rigid support is quickly intervened to suppress vibration, thereby achieving dual-mode operation of the hydraulic damping system. At the same time, the amplification system of the laser sensor and the vibration expansion plate can construct a multi-scale vibration monitoring system for the nozzle.

Description

Technical Field

[0001] The present invention relates to the technical field of thrust component detection, in particular to an anti-deformation simulation test device for rocket thrust components. Background Art

[0002] The nozzle is an important component of a rocket engine. Its core function is to convert the thermal energy of high-temperature and high-pressure combustion gas in the combustion chamber into kinetic energy to propel the rocket into flight. Among them, the Laval nozzle structure that first converges and then diverges is more widely used.

[0003] The design goal of the nozzle is to make the outlet gas pressure equal to the external environmental pressure, at which point the thrust efficiency reaches its maximum. However, in actual use, as the rocket continues to fly, the external environmental pressure continues to change. After the rocket leaves the atmosphere and enters the vacuum working stage, the nozzle outlet pressure is higher than the external air pressure. The gas continues to expand outside the nozzle, forming an expansion fan, and the airflow direction is deflected outward. At the same time, the gas forms a bright diamond-shaped shock wave chain, resulting in energy loss and reduced efficiency. In addition, at the end of combustion of some solid rockets, the chamber pressure drops when the fuel is exhausted, and the outlet pressure may be lower than the external air pressure at the end of low-altitude flight, making the tube outlet pressure lower than the external air pressure. The external air compresses the combustion gas, which is compressed outside the nozzle, generating oblique shock waves or normal shock waves, resulting in a sudden change in the direction of the airflow and a sudden increase in pressure. The high-pressure external gas may reversely invade the nozzle expansion section, causing the airflow to separate from the nozzle wall, triggering violent vibrations, and in severe cases, the nozzle structure may be damaged. However, the probability of such a situation occurring is low, so when testing such a situation, it is necessary to use the test as the purpose to avoid damage to the nozzle structure and unnecessary economic losses. At the same time, the integrated nozzle structure makes it difficult to directly observe and detect its interior during the test phase. Based on this, an anti-deformation simulation test device for rocket thrust components is proposed. Summary of the Invention

[0004] The purpose of the present invention is to solve the problems in the prior art and to propose an anti-deformation simulation test device for rocket thrust components.

[0005] In order to achieve the above object, the present invention adopts the following technical solutions:

[0006] A deformation prevention simulation test device for rocket thrust components, comprising a simulated wind tunnel detonation chamber and a simulation test chamber for conducting simulation tests on a nozzle, wherein the inner side wall of the simulation test chamber is connected to a chamber pressure adjustment chamber via two mounting plates, the inner side wall of the chamber pressure adjustment chamber is connected to a plurality of arc-shaped spray hoods, the end of the chamber pressure adjustment chamber is connected to a limit assembly for mounting a nozzle head, a plurality of protective baffles are provided on the outer side of the nozzle tail, the outer side wall of the protective baffle is connected to a buffer piston plate via two pillars, the buffer piston plate is connected to a liquid buffer assembly for first buffering and then supporting and protecting the nozzle shock wave, the liquid buffer assembly is provided with a mounting telescopic column, auxiliary support assemblies are provided on the left and right sides of the mounting telescopic column, and a vibration expansion plate is connected to the end of the protective baffle;

[0007] The inner side wall of the simulation test chamber is connected to four retaining frames through four bolt locking cylinders, the retaining frames are connected to a probe rod, a flow measuring assembly is provided on the probe rod, the outer side wall of the probe rod is connected to a reinforcement ring through multiple reinforcement rods, and an inner support assembly is provided on the outer side wall of the reinforcement ring.

[0008] Preferably, the limiting assembly consists of two limiting slide rails and two limiting retracting covers. The outer side wall of the chamber pressure adjustment chamber is fixedly connected to the limiting slide rails through a fixed plate. The limiting slide rails are slidably connected to the retracting covers. Fastening bolts are provided on the top and bottom of the retracting covers.

[0009] Preferably, the inner side wall of the chamber pressure adjustment chamber is provided with a plurality of arc-shaped grooves for installing the arc-shaped spray hood, the end of the chamber pressure adjustment chamber is connected with an inner sealing ring, the two ends of the retracting hood are connected with outer sealing rings, and the internal chamber of the chamber pressure adjustment chamber is filled with marking liquid.

[0010] Preferably, the liquid buffer assembly consists of a liquid buffer cylinder and a plurality of liquid buffer channels, the outer side wall of the protective baffle is fixedly connected to the pillar, and the pillar is slidably connected to the liquid buffer cylinder through a buffer piston plate.

[0011] Preferably, the bottoms of the multiple liquid buffer channels are respectively connected to the middle of the liquid buffer cylinder, the top of the liquid buffer channel is connected to a buffer chamber, the top of the buffer chamber is fixedly connected to the mounting telescopic column through an adapter plate, and the side wall of the adapter plate is fixedly connected to a guide inclined plate through a horizontal plate.

[0012] Preferably, the auxiliary support assembly consists of a threaded support rod and a screw-out impeller, the adapter plate is fixedly connected to a threaded sleeve, the threaded sleeve is threadedly connected to the threaded support rod, the threaded support rod is fixedly connected to the screw-out impeller, the mounting telescopic column is fixedly connected to the inner side wall of the simulation test chamber, and the side wall of the mounting telescopic column is fixedly connected to two symmetrically arranged limit plates.

[0013] Preferably, the adapter plate is fixedly connected to a laser sensor via a right-angle rod, the end of the protective baffle is fixedly connected to a sensing plate via a vibration expansion plate, and the sensing parts of the laser sensor and the sensing plate are symmetrically arranged.

[0014] Preferably, the flow measurement component includes a plurality of dynamic cameras, a plurality of receiving grooves are provided on the probe rod, the inner side walls of the receiving grooves are fixedly connected to the plurality of dynamic cameras, and a glass cover is fixedly connected to the side walls of the receiving grooves.

[0015] Preferably, the inner support assembly is composed of multiple pressure-sensitive support columns and multiple inner support arc plates, the outer side wall of the reinforcement ring is fixedly connected to the inner side walls of the multiple inner support arc plates through multiple pressure-sensitive support columns, and a pressure sensor is provided in the pressure-sensitive support column.

[0016] Compared with the prior art, the present invention has the following beneficial effects:

[0017] 1. This solution uses a double-retractable cover sliding docking system through the arrangement of a limit assembly, an inner sealing ring, and an outer sealing ring. The inner and outer sealing rings are squeezed to form an annular sealing belt, which is combined with a limit slide rail and bolt locking to achieve rapid and accurate positioning of the nozzle head, ensuring consistency between the test state and the actual working conditions.

[0018] 2. This solution, through the setting of liquid damping components and vibration expansion plates, can achieve nonlinear damping through the variable cross-section design of the liquid damping channel in the low-amplitude stage. In the high-amplitude critical state, the self-locking rigid support can quickly intervene to suppress vibration and realize the dual-mode operation of the hydraulic damping system. At the same time, the amplification system of the laser sensor and the vibration expansion plate can construct a multi-scale vibration monitoring system for the nozzle.

[0019] 3. This solution uses a plurality of internal support arc plates and pressure-sensing support columns. The internal support arc plate array can be used in conjunction with a pressure-sensing device to form an active support network at the tail of the nozzle, thereby compensating for the internal and external pressure differences in real time and effectively suppressing the risk of deformation.

[0020] 4. Through the setting of the arc-shaped spray hood and flow measurement components, this scheme can use high-pressure atomized fluorescent marker liquid and cooperate with a high-speed dynamic camera system to achieve three-dimensional flow field visualization reconstruction and increase the experimental data of the airflow state inside the integrated nozzle. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 This is a schematic diagram of the three-dimensional structure of an anti-deformation simulation test device for rocket thrust components proposed by the present invention;

[0022] Figure 2 This is an assembly diagram of an anti-deformation simulation test device for rocket thrust components proposed by the present invention;

[0023] Figure 3 for Figure 2 Enlarged view of point A in the middle;

[0024] Figure 4 This is a schematic structural diagram of a limit assembly in an anti-deformation simulation test device for rocket thrust components proposed by the present invention;

[0025] Figure 5 This is a structural schematic diagram of the position of the protective baffle in the anti-deformation simulation test device for rocket thrust components proposed by the present invention;

[0026] Figure 6 This is a structural schematic diagram of the position of the vibration expansion plate in an anti-deformation simulation test device for rocket thrust components proposed by the present invention;

[0027] Figure 7 This is a schematic structural diagram of an auxiliary support assembly in an anti-deformation simulation test device for rocket thrust components proposed by the present invention;

[0028] Figure 8 This is a schematic structural diagram of a liquid buffer assembly in an anti-deformation simulation test device for rocket thrust components proposed by the present invention;

[0029] Figure 9 This is a structural schematic diagram of the flow measurement component in an anti-deformation simulation test device for rocket thrust components proposed by the present invention.

[0030] In the figure: 1. Simulated wind tunnel detonation chamber; 2. Simulated test chamber; 3. Nozzle; 4. Chamber pressure adjustment chamber; 5. Arc-shaped spray hood; 6. Inner sealing ring; 7. Limiting slide rail; 8. Retracting hood; 9. Outer sealing ring; 10. Fastening bolts; 11. Protective baffle; 12. Pillar; 13. Buffer piston plate; 14. Liquid buffer cylinder; 15. Liquid buffer channel; 16. Buffer chamber; 17. Guide ramp; 18. Install telescopic column; 19. Limiting plate; 20. Threaded sleeve; 21. Threaded support rod; 22. Unscrew impeller; 23. Bolt locking cylinder; 24. Retaining frame; 25. Probe rod; 26. Dynamic camera; 27. Reinforcement ring; 28. Pressure-sensing support column; 29. Inner support arc plate; 30. Laser sensor; 31. Vibration expansion plate; 32. Induction plate. DETAILED DESCRIPTION

[0031] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0032] In the description of the present invention, it should be noted that the terms "upper," "lower," "inner," "outer," "top / bottom," and the like, indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings and are intended solely to facilitate and simplify the description of the present invention. They are not intended to indicate or imply that the devices or components referred to must have, be constructed, or operate in a specific orientation, and therefore should not be construed as limitations on the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0033] In the description of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "installed," "provided with," "mounted / connected," and "connected" should be understood in a broad sense. For example, "connected" can mean a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, and it can be internal communication between two components. Those skilled in the art will be able to understand the specific meanings of the above terms in the present invention in specific circumstances.

[0034] Example, see Figures 1 to 9 A rocket thrust component anti-deformation simulation test device includes a simulated wind tunnel detonation chamber 1 and a simulation test chamber 2 for conducting simulation tests on a nozzle 3. The inner wall of the simulation test chamber 2 is connected to a chamber pressure adjustment chamber 4 via two mounting plates. The inner wall of the chamber pressure adjustment chamber 4 is connected to a plurality of arc-shaped spray shields 5. The end of the chamber pressure adjustment chamber 4 is connected to a limit assembly for mounting the nozzle 3 head.

[0035] Furthermore, the limiting assembly is composed of two limiting slide rails 7 and two limiting retracting covers 8. The outer wall of the chamber pressure adjustment chamber 4 is fixedly connected to the limiting slide rail 7 through a fixing plate. The limiting slide rail 7 is slidably connected to the retracting cover 8. The top and bottom of the retracting cover 8 are both provided with fastening bolts 10. The inner wall of the chamber pressure adjustment chamber 4 is provided with a plurality of arc-shaped through grooves for installing the arc-shaped spray cover 5. The end of the chamber pressure adjustment chamber 4 is connected to an inner sealing ring 6. The ends of the two retracting covers 8 are both connected to outer sealing rings 9. The internal chamber of the chamber pressure adjustment chamber 4 is filled with a marking liquid.

[0036] It should be noted that: a high-speed airflow is generated by using the shock wave wind tunnel in the simulated wind tunnel detonation chamber 1 to enter the simulated test chamber 2, and the chamber pressure adjustment chamber 4 simulates the high-pressure flow rate in the rocket engine combustion chamber. This is an existing technical means in this field and will not be described in detail here. Before testing the nozzle 3, the head of the nozzle 3 is placed between the two retracting covers 8, and then the retracting cover 8 is slid on the limiting slide rail 7, so that the two retracting covers 8 are docked with each other. During this process, the inner sealing ring 6 and the outer sealing ring 9 are squeezed against each other to form an assembled annular sealing belt, and then the fastening bolts 10 on the retracting cover 8 are tightened to limit the head of the nozzle 3. The marking liquid in the chamber pressure adjustment chamber 4 has a fluorescent color and is sprayed out in a mist form from multiple arc-shaped spray covers 5 by a high-pressure pump, so that the subsequent mist marking liquid flows with the high-pressure airflow;

[0037] The above advantages are as follows: in this way, the retractable cover 8 can be slidably docked on the limiting slide rail 7 to limit the head of the nozzle 3, which is convenient for subsequent simulation of the state of the nozzle 3 facing the airflow, making the detection effect more suitable for the use state;

[0038] A plurality of protective baffles 11 are provided on the outside of the tail of the nozzle 3. The outer wall of the protective baffle 11 is connected to a buffer piston plate 13 through two pillars 12. The buffer piston plate 13 is connected to a liquid buffer assembly for buffering and then supporting the nozzle 3 during shock waves. The liquid buffer assembly is provided with a mounting telescopic column 18. Auxiliary support components are provided on both sides of the mounting telescopic column 18. The end of the protective baffle 11 is connected to a vibration expansion plate 31;

[0039] Furthermore, the liquid buffer assembly consists of a liquid buffer cylinder 14 and a plurality of liquid buffer channels 15. The outer wall of the protective baffle 11 is fixedly connected to the pillar 12. The pillar 12 is slidably connected to the liquid buffer cylinder 14 through the buffer piston plate 13. The bottoms of the plurality of liquid buffer channels 15 are respectively connected to the middle of the liquid buffer cylinder 14. The top of the liquid buffer channel 15 is connected to a buffer chamber 16. The top of the buffer chamber 16 is fixedly connected to the mounting telescopic column 18 through an adapter plate. The side wall of the adapter plate is fixedly connected to a guide inclined plate 17 through a horizontal plate. The auxiliary support assembly is composed of a threaded support rod 21 and a screw-out impeller. 22, the adapter plate is fixedly connected to the threaded sleeve 20, the threaded sleeve 20 is threadedly connected to the threaded support rod 21, the threaded support rod 21 is fixedly connected to the unscrewed impeller 22, the installation telescopic column 18 is fixedly connected to the inner wall of the simulation test chamber 2, the installation telescopic column 18 is fixedly connected to the side wall of the simulation test chamber 2 with two symmetrically arranged limit plates 19, the adapter plate is fixedly connected to the laser sensor 30 through a right-angle rod, the end of the protective baffle 11 is fixedly connected to the sensing plate 32 through the vibration expansion plate 31, and the sensing parts of the laser sensor 30 and the sensing plate 32 are symmetrically arranged;

[0040] It should be noted that: the guide ramp 17 is arranged at the front end of the adapter plate, and the side of the guide ramp 17 facing the simulated wind tunnel detonation chamber 1 is the windward side, that is, the guide ramp 17 is a V-shaped slope. During the test, the guide ramp 17 will guide the airflow to avoid causing continuous wind pressure on the test device, wherein the airflow blows the screw-out impeller 22, so that the screw-out impeller 22 rotates and drives the threaded support rod 21 to rotate in the threaded sleeve 20, so that the threaded support rod 21 is continuously screwed out in the threaded sleeve 20, and the outer thread of the threaded support rod 21 is rotated to the threaded sleeve 20. The two threaded rods 21 stop at the end of the internal thread (the final unscrewing length of the two threaded rods 21 is the same, which can maintain the stable limit of the installation telescopic column 18. After the nozzle 3 test is completed, the threaded rod 21 is screwed into the threaded sleeve 20 to release the extension limit of the installation telescopic column 18). The threaded rod 21 is moved outward and continuously pressed against the limit plate 19, so that the installation telescopic column 18 is extended, driving the protective baffle 11 to fit the outer wall of the tail of the nozzle 3. If the air pressure inside the nozzle 3 is lower than the external air pressure, the nozzle 3 will have a shock wave phenomenon, and the tail of the nozzle 3 that is not restricted will produce The protective baffle 11 generates vibrations of a certain frequency. During this process, the displacement of the protective baffle 11 will push the buffer piston plate 13 through the support 12, wherein the support 12 and the buffer piston plate 13 are connected by a universal joint structure, so that the buffer piston plate 13 slides in the liquid buffer cylinder 14, squeezing the hydraulic oil in the liquid buffer cylinder 14, so that the hydraulic oil enters the liquid buffer channel 15. Since the flow channel of the hydraulic oil becomes narrower, the flow of the hydraulic oil is blocked, thereby hindering the movement of the buffer piston plate 13. In the continuous vibration process, the protective baffle 11 will The vibration expansion plate 31 is driven to move together. The characteristics of the thin plate at the edge of the vibration expansion plate 31 will amplify the vibration, thereby increasing the offset amplitude of the sensing plate 32 on the vibration expansion plate 31, making it easier for the laser sensor 30 to better measure the amplitude and frequency of the vibration during this process. When the vibration of the nozzle 3 is large, the buffer piston plate 13 slides in the liquid buffer cylinder 14 to the liquid buffer channel 15, blocking the bottom port of the liquid buffer channel 15. The hydraulic oil in the liquid buffer cylinder 14 cannot flow, and the hydraulic oil is converted into a relatively rigid support for the buffer piston plate 13, so that the vibration of the nozzle 3 within a certain range will not be amplified.

[0041] The above advantages are as follows: the protective baffle 11 can be used to detect the vibration amplitude and frequency of the nozzle 3 when the vibration amplitude of the nozzle 3 is low. When the vibration amplitude of the nozzle 3 is high, the hydraulic buffer is converted into a relatively rigid support, thereby avoiding structural damage caused by large vibration amplitude of the nozzle 3 and ensuring the safety of the nozzle 3 during the test.

[0042] The inner wall of the simulation test chamber 2 is connected to four retaining frames 24 through four bolt locking cylinders 23. The retaining frames 24 are connected to a probe rod 25. The probe rod 25 is provided with a flow measurement component. The outer wall of the probe rod 25 is connected to a reinforcement ring 27 through multiple reinforcement rods. The outer wall of the reinforcement ring 27 is provided with an internal support component.

[0043] Furthermore, the flow measurement assembly includes multiple dynamic cameras 26, and the probe rod 25 is provided with multiple storage slots. The inner sidewalls of the storage slots are fixedly connected to the multiple dynamic cameras 26, and the sidewalls of the storage slots are fixedly connected to the glass covers. The inner support assembly consists of multiple pressure-sensitive support columns 28 and multiple inner support arc plates 29. The outer sidewalls of the reinforcement ring 27 are respectively fixedly connected to the inner sidewalls of the multiple inner support arc plates 29 through the multiple pressure-sensitive support columns 28. Pressure sensors are provided in the pressure-sensitive support columns 28.

[0044] It should be noted that: during the installation of the nozzle 3, the probe rod 25 is inserted into the axial position of the nozzle 3, and then the end of the retaining frame 24 is locked and limited by the bolt locking tube 23, so that multiple inner support arc plates 29 are placed on the inner wall of the tail end of the nozzle 3, and the room pressure in the nozzle 3 is changed, so that the room pressure in the nozzle 3 is lower than the external wind pressure, then the exhaust part of the tail end of the nozzle 3 will continue to be subjected to inward pressure, and the inner support arc plate 29 will continue to maintain rigid support for the inner wall of the tail end of the nozzle 3 to prevent the nozzle 3 from being deformed by pressure. At the same time, the pressure sensor in the pressure-sensing support column 28 will also monitor the pressure on the inner support arc plate 29 in real time, and the airflow in the nozzle 3 is flowing. During the process, the mist-like marker liquid is driven to flow together, and the dynamic camera 26 in the receiving groove of the probe rod 25 will continuously capture the flow state of the mist-like marker liquid, simulate the flow state of the airflow in different parts of the integrated nozzle 3, and increase the simulation test data of the airflow inside the nozzle 3. The abnormal flow in the nozzle 3 will cause the shock wave surface to deviate from the design shape. The shock wave position offset can be observed through the atomization trajectory of the fluorescent marker liquid. At this time, the dynamic camera 26 will capture the abnormal area of the flow field brightness gradient, and when the airflow is abnormal, the boundary layer separation point moves forward, and the fluorescent particles form an obvious vortex group in the separation area, causing the pressure sensor to detect a sudden increase in local negative pressure;

[0045] The advantages of the above are as follows: the multiple inner support arc plates 29 can be used to provide continuous rigid support to the inner wall of the tail of the nozzle 3, thereby preventing the airflow outlet of the nozzle 3 from being deformed by pressure. At the same time, the multiple dynamic cameras 26 cooperate with the mist-like marking liquid in the airflow to increase the test data of the airflow state inside the integrated nozzle 3, making the detection more comprehensive.

[0046] When the present invention is in use, a shock wave wind tunnel in a simulated wind tunnel detonation chamber 1 is used to generate a high-speed airflow into the simulated test chamber 2, and the chamber pressure adjustment chamber 4 simulates the high-pressure flow rate in the combustion chamber of a rocket engine. This is an existing technical means in the art and will not be described in detail here. Before testing the nozzle 3, the head of the nozzle 3 is placed between two retractable covers 8, and then the retractable cover 8 is slid on the limiting slide 7 so that the two retractable covers 8 are docked with each other. During this process, the inner sealing ring 6 and the outer sealing ring 9 are squeezed against each other to form an assembled annular sealing belt. Then, the fastening bolts 10 on the retractable cover 8 are tightened to limit the head of the nozzle 3. The marking liquid in the chamber pressure adjustment chamber 4 has a fluorescent color and is sprayed out in a mist form from multiple arc-shaped spray covers 5 by a high-pressure pump, so that the subsequent mist marking liquid flows along with the high-pressure airflow. In this way, the retractable cover 8 can be used to slide and dock on the limiting slide 7 to limit the head of the nozzle 3, so as to facilitate the subsequent simulation of the state of the nozzle 3 facing the airflow, so that the detection effect is more in line with the use state.

[0047] The protective baffle 11 is used to detect the vibration amplitude and frequency of the nozzle 3 when the vibration amplitude is low. When the vibration amplitude of the nozzle 3 is high, the hydraulic buffer is converted into a relatively rigid support to avoid structural damage caused by large vibration amplitude of the nozzle 3, thereby ensuring the safety of the nozzle 3 during the test.

[0048] Multiple inner support arc plates 29 are used to provide continuous rigid support to the inner wall of the tail of the nozzle 3 to prevent the airflow outlet of the nozzle 3 from being deformed by pressure. At the same time, multiple dynamic cameras 26 cooperate with the mist-like marking liquid in the airflow to increase the test data of the airflow flow state inside the integrated nozzle 3, making the detection more comprehensive.

[0049] The above description is only a preferred specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any technician familiar with the technical field, within the technical scope disclosed by the present invention, who makes equivalent replacements or changes based on the technical solution and inventive concept of the present invention, should be covered by the scope of protection of the present invention.

Claims

1. A deformation prevention simulation test device for a rocket thrust component, comprising a simulated wind tunnel detonation chamber (1) and a simulated test chamber (2) for performing a simulation test on a nozzle (3), characterized in that: The inner wall of the simulation test chamber (2) is connected to a chamber pressure adjustment chamber (4) through two mounting plates, the inner wall of the chamber pressure adjustment chamber (4) is connected to a plurality of arc-shaped spray hoods (5), the end of the chamber pressure adjustment chamber (4) is connected to a limit assembly for mounting the nozzle (3) head, the outer side of the nozzle (3) is provided with a plurality of protective baffles (11), the outer side wall of the protective baffle (11) is connected to a buffer piston plate (13) through two pillars (12), the buffer piston plate (13) is connected to a liquid buffer assembly for first buffering and then supporting the nozzle (3) during shock wave, the liquid buffer assembly is provided with a mounting telescopic column (18), the left and right sides of the mounting telescopic column (18) are provided with auxiliary support assemblies, and the end of the protective baffle (11) is connected to a vibration expansion plate (31); The inner side wall of the simulation test chamber (2) is connected to four retaining frames (24) through four bolt locking cylinders (23), the retaining frames (24) are connected to a probe rod (25), a flow measuring assembly is provided on the probe rod (25), and the outer side wall of the probe rod (25) is connected to a reinforcement ring (27) through a plurality of reinforcement rods, and an inner support assembly is provided on the outer side wall of the reinforcement ring (27); The internal chamber of the chamber pressure adjustment chamber (4) is filled with a marking liquid. The marking liquid in the chamber pressure adjustment chamber (4) has a fluorescent color and is sprayed out in a mist form from multiple arc-shaped spray hoods (5) by means of a high-pressure pump, so that the subsequent mist-like marking liquid flows along with the high-pressure airflow.

2. The anti-deformation simulation test device for rocket thrust components according to claim 1, characterized in that: The limiting assembly consists of two limiting slide rails (7) and two limiting retracting covers (8); the outer side wall of the chamber pressure adjustment chamber (4) is fixedly connected to the limiting slide rails (7) via a fixed plate; the limiting slide rails (7) are slidably connected to the retracting covers (8); and fastening bolts (10) are provided on the top and bottom of the retracting covers (8).

3. The anti-deformation simulation test device for rocket thrust components according to claim 2, characterized in that: The inner side wall of the chamber pressure adjustment chamber (4) is provided with a plurality of arc-shaped through grooves for installing the arc-shaped spray hood (5). The end of the chamber pressure adjustment chamber (4) is connected to an inner sealing ring (6), and the ends of the two retracting hoods (8) are both connected to outer sealing rings (9).

4. The anti-deformation simulation test device for rocket thrust components according to claim 1, characterized in that: The liquid buffer assembly consists of a liquid buffer cylinder (14) and a plurality of liquid buffer channels (15); the outer side wall of the protective baffle (11) is fixedly connected to the support column (12); and the support column (12) is slidably connected to the liquid buffer cylinder (14) via a buffer piston plate (13).

5. The anti-deformation simulation test device for rocket thrust components according to claim 4, characterized in that: The bottoms of the plurality of liquid buffer channels (15) are respectively connected to the middle of the liquid buffer cylinder (14); the tops of the liquid buffer channels (15) are connected to a buffer chamber (16); the tops of the buffer chambers (16) are fixedly connected to the mounting telescopic columns (18) via adapter plates; and the side walls of the adapter plates are fixedly connected to the guide inclined plates (17) via transverse plates.

6. The anti-deformation simulation test device for rocket thrust components according to claim 5, characterized in that: The auxiliary support assembly consists of a threaded support rod (21) and a screw-out impeller (22); the adapter plate is fixedly connected to a threaded sleeve (20); the threaded sleeve (20) is threadedly connected to the threaded support rod (21); the threaded support rod (21) is fixedly connected to the screw-out impeller (22); the mounting telescopic column (18) is fixedly connected to the inner side wall of the simulation test chamber (2); and the side wall of the mounting telescopic column (18) is fixedly connected to two symmetrically arranged limit plates (19).

7. The anti-deformation simulation test device for rocket thrust components according to claim 5, characterized in that: The adapter plate is fixedly connected to a laser sensor (30) via a right-angle rod, and the end of the protective baffle (11) is fixedly connected to a sensing plate (32) via a vibration expansion plate (31). The sensing parts of the laser sensor (30) and the sensing plate (32) are symmetrically arranged.

8. The anti-deformation simulation test device for rocket thrust components according to claim 1, characterized in that: The flow measurement assembly includes a plurality of dynamic cameras (26), a plurality of receiving grooves are provided on the probe rod (25), the inner side walls of the receiving grooves are fixedly connected to the plurality of dynamic cameras (26), and the side walls of the receiving grooves are fixedly connected to glass covers.

9. The anti-deformation simulation test device for rocket thrust components according to claim 1, characterized in that: The inner support assembly is composed of a plurality of pressure-sensitive support columns (28) and a plurality of inner support arc plates (29); the outer side walls of the reinforcement ring (27) are fixedly connected to the inner side walls of the plurality of inner support arc plates (29) through the plurality of pressure-sensitive support columns (28); and a pressure sensor is provided in the pressure-sensitive support column (28).

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