Anti-deformation simulation test device for rocket thrust component

Abstract

The invention discloses an anti-deformation simulation test device for a rocket thrust component, and belongs to the technical field of thrust component detection, the anti-deformation simulation test device comprises a simulation wind tunnel detonation cavity and a simulation test cabin used for carrying out a simulation test on a spray pipe, and the inner side wall of the simulation test cabin is connected with a chamber pressure adjusting cavity through two mounting plates; the inner side wall of the chamber pressure adjusting cavity is connected with a plurality of arc-shaped spraying covers, the end of the chamber pressure adjusting cavity is connected with a limiting assembly used for installing the head of the spraying pipe, and a plurality of protection baffles are arranged on the outer side of the tail of the spraying pipe. Through the arrangement of the liquid buffer assembly and the vibration expansion plate, non-linear damping can be achieved through the variable cross-section design of a liquid buffer channel in the low-amplitude stage, self-locking type rigid support is made to quickly intervene in the high-amplitude critical state, vibration is restrained, and dual-mode work of a hydraulic damping system is achieved; and a multi-scale vibration monitoring system for the spray pipe can be constructed.

Description

Technical Field

[0001] The present invention relates to the technical field of thrust member detection, and particularly to a deformation prevention simulation test device for a rocket thrust member. Background Art

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

[0003] The design goal of the nozzle is to make the outlet gas pressure equal to the external environmental pressure, at which time the thrust efficiency reaches the maximum value. However, in actual use, as the rocket continues to fly, the external environmental pressure constantly changes. After the rocket leaves the atmosphere and enters the vacuum working stage, the nozzle outlet pressure is higher than the external air pressure, and the gas continues to expand outside the nozzle, forming an expansion fan. The airflow direction deflects outward. At the same time, the gas forms a bright diamond-shaped shock wave chain, resulting in energy loss and reduced efficiency. And at the end of the combustion of some solid rockets, when the fuel is exhausted and the chamber pressure drops, 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 gas, and the gas is compressed outside the nozzle, generating an oblique shock wave or a normal shock wave, resulting in a sudden change in the airflow direction and a sharp rise in pressure. The high-pressure external gas may reverse and invade the expansion section of the nozzle, causing the airflow to separate from the nozzle wall and triggering violent vibrations. In severe cases, it may damage the nozzle structure. However, the probability of such a situation occurring is relatively low. Therefore, when testing for such a situation, it is necessary to conduct tests to avoid damaging the nozzle structure and causing unnecessary economic losses. At the same time, the integrated nozzle structure makes it difficult to directly observe and detect its internal conditions during the test stage. Based on this, a deformation prevention simulation test device for a rocket thrust member is proposed. Summary of the Invention

[0004] The purpose of the present invention is to solve the problems in the prior art, and a deformation prevention simulation test device for a rocket thrust member is proposed.

[0005] In order to achieve the above purpose, the present invention adopts the following technical solutions: An anti-deformation simulation test device for a rocket thrust member, comprising a simulated wind tunnel detonation chamber and a simulated test chamber for simulating tests on a nozzle. The inner side wall of the simulated test chamber is connected with a chamber pressure adjustment chamber through two mounting plates. The inner side wall of the chamber pressure adjustment chamber is connected with a plurality of arc-shaped spray covers. The end of the chamber pressure adjustment chamber is connected with a limit component for installing the head of the nozzle. A plurality of protective baffles are arranged on the outer side of the tail of the nozzle. The outer side wall of the protective baffle is connected with a buffer piston plate through two support columns. The buffer piston plate is connected with a liquid buffer component for buffering and then supporting the protection when the nozzle has a shock wave. An installation telescopic column is arranged on the liquid buffer component. Auxiliary support components are arranged on both the left and right sides of the installation telescopic column. The end of the protective baffle is connected with a vibration amplification plate; The inner side wall of the simulated test chamber is respectively connected with four fixing frames through four bolt locking cylinders. The fixing frame is connected with a probe rod. A flow measurement component is arranged on the probe rod. The outer side wall of the probe rod is connected with a reinforcing ring through a plurality of reinforcing rods. An inner support component is arranged on the outer side wall of the reinforcing ring.

[0006] Preferably, the limit component is composed of two limit sliding rails and two limit closing covers. The outer side wall of the chamber pressure adjustment chamber is fixedly connected with the limit sliding rail through a fixing plate. The limit sliding rail is slidably connected with the closing cover. Tightening bolts are arranged on both the top and bottom of the closing cover.

[0007] Preferably, a plurality of arc-shaped through grooves for installing the arc-shaped spray covers are opened on the inner side wall of the chamber pressure adjustment chamber. The end of the chamber pressure adjustment chamber is connected with an inner sealing ring. Outer sealing rings are connected to the ends of both closing covers. A marked liquid is contained in the inner chamber of the chamber pressure adjustment chamber.

[0008] Preferably, the liquid buffer component is composed of a liquid buffer cylinder and a plurality of liquid buffer channels. The outer side wall of the protective baffle is fixedly connected with the support column. The support column is slidably connected with the liquid buffer cylinder through the buffer piston plate.

[0009] Preferably, the bottoms of the plurality of liquid buffer channels are respectively communicated with the middle part of the liquid buffer cylinder. The top of the liquid buffer channel is communicated with a buffer chamber. The top end of the buffer chamber is fixedly connected with the installation telescopic column through an adapter plate. A flow guiding inclined plate is fixedly connected to the side wall of the adapter plate through a cross plate.

[0010] Preferably, the auxiliary support component is composed of a threaded support rod and a screw-out impeller. The adapter plate is fixedly connected with a threaded sleeve. The threaded sleeve is threadedly connected with the threaded support rod. The threaded support rod is fixedly connected with the screw-out impeller. The installation telescopic column is fixedly connected with the inner side wall of the simulated test chamber. Two symmetrically arranged limit plates are fixedly connected to the side wall of the installation telescopic column.

[0011] Preferably, the adapter plate is fixedly connected with a laser sensor through a right-angle rod, the end of the protective baffle is fixedly connected with an induction plate through a vibration amplification plate, and the induction parts of the laser sensor and the induction plate are symmetrically arranged.

[0012] Preferably, the flow measurement assembly includes a plurality of dynamic cameras. A plurality of storage grooves are formed in the probe rod. The inner side walls of the storage grooves are fixedly connected with the plurality of dynamic cameras, and a glass cover is fixedly connected to the side walls of the storage grooves.

[0013] Preferably, the inner support assembly is composed of a plurality of pressure-sensitive support columns and a plurality of inner support arc plates. The outer side wall of the reinforcement ring is fixedly connected with the inner side walls of the plurality of inner support arc plates through the plurality of pressure-sensitive support columns respectively, and a pressure sensor is arranged in the pressure-sensitive support column.

[0014] Compared with the prior art, the beneficial effects of the present invention are as follows: 1. Through the settings of the limit assembly, the inner sealing ring and the outer sealing ring, this solution can utilize the double retractable cover sliding docking system to form an annular sealing belt by the extrusion of the inner sealing ring and the outer sealing ring, and cooperate with the limit slide rail and bolt locking to realize the rapid and accurate positioning of the nozzle head, ensuring the consistency between the test state and the actual working condition.

[0015] 2. Through the settings of the liquid buffer assembly and the vibration amplification plate, this solution can achieve non-linear damping through the variable cross-section design of the liquid buffer channel in the low-amplitude stage, and let the self-locking rigid support quickly intervene in the high-amplitude critical state to suppress vibration, realizing the dual-mode operation of the hydraulic damping system. At the same time, the laser sensor and the amplification system of the vibration amplification plate can construct a multi-scale vibration monitoring system for the nozzle.

[0016] 3. Through the settings of the plurality of inner support arc plates and the pressure-sensitive support columns, this solution can utilize the inner support arc plate array and the pressure sensing device to form an active support network at the nozzle tail, compensate the internal and external pressure difference in real time, and effectively suppress the risk of deformation.

[0017] 4. Through the settings of the arc-shaped spray cover and the flow measurement assembly, this solution can utilize the fluorescently labeled liquid with high-pressure atomization and cooperate with the high-speed dynamic camera system to realize the three-dimensional visualization reconstruction of the flow field, increasing the test data on the air flow state inside the integrated nozzle. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a three-dimensional structural schematic diagram of a deformation prevention simulation test device for a rocket thrust component proposed by the present invention; Figure 2 It is an assembly drawing of a deformation prevention simulation test device for a rocket thrust component proposed by the present invention; Figure 3 It is Figure 2 The enlarged view of part A in Figure 4Schematic structural diagram of the limit component in an anti-deformation simulation test device for a rocket thrust component proposed by the present invention; Figure 5 Schematic structural diagram of the position of the protective baffle in an anti-deformation simulation test device for a rocket thrust component proposed by the present invention; Figure 6 Schematic structural diagram of the position of the vibration amplification plate in an anti-deformation simulation test device for a rocket thrust component proposed by the present invention; Figure 7 Schematic structural diagram of the auxiliary support component in an anti-deformation simulation test device for a rocket thrust component proposed by the present invention; Figure 8 Schematic structural diagram of the liquid buffer component in an anti-deformation simulation test device for a rocket thrust component proposed by the present invention; Figure 9 Schematic structural diagram of the flow measurement component in an anti-deformation simulation test device for a rocket thrust component proposed by the present invention.

[0019] In the figure: 1, simulated wind tunnel detonation chamber; 2, simulated test chamber; 3, nozzle; 4, chamber pressure adjustment chamber; 5, arc-shaped spray cover; 6, inner sealing ring; 7, limit slide rail; 8, retractable cover; 9, outer sealing ring; 10, fastening bolt; 11, protective baffle; 12, support pillar; 13, buffer piston plate; 14, liquid buffer cylinder; 15, liquid buffer channel; 16, buffer chamber; 17, guide inclined plate; 18, installation telescopic column; 19, limit plate; 20, threaded sleeve; 21, threaded support rod; 22, screw-out impeller; 23, bolt locking cylinder; 24, retaining frame; 25, probe; 26, dynamic camera; 27, reinforcement ring; 28, pressure-sensing support column; 29, inner support arc plate; 30, laser sensor; 31, vibration amplification plate; 32, induction plate. Detailed implementation manners

[0020] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a 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 those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0021] In the description of the present invention, it should be noted that the orientation or positional relationship indicated by the terms "upper", "lower", "inner", "outer", "top / bottom end", etc. is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation to the present invention. In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance.

[0022] In the description of the present invention, it should be noted that unless otherwise clearly specified and defined, the terms "installation", "provided with", "sheathed / connected", "connection", etc. should be understood in a broad sense. For example, "connection" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0023] Example, refer to Figures 1 to 9 , a deformation prevention simulation test device for a rocket thrust member, comprising a simulated wind tunnel detonation chamber 1 and a simulated test chamber 2 for simulating the test of a nozzle 3. The inner side wall of the simulated test chamber 2 is connected with a chamber pressure adjustment chamber 4 through two mounting plates. The inner side wall of the chamber pressure adjustment chamber 4 is connected with a plurality of arc-shaped spray covers 5. The end of the chamber pressure adjustment chamber 4 is connected with a limit component for mounting the head of the nozzle 3. Furthermore, the limit component consists of two limit slide rails 7 and two limit converging covers 8. The outer side wall of the chamber pressure adjustment chamber 4 is fixedly connected with the limit slide rails 7 through fixing plates. The limit slide rails 7 are slidably connected with the converging covers 8. Fastening bolts 10 are arranged at the top and bottom of the converging covers 8. A plurality of arc-shaped through grooves for mounting the arc-shaped spray covers 5 are opened on the inner side wall of the chamber pressure adjustment chamber 4. The end of the chamber pressure adjustment chamber 4 is connected with an inner sealing ring 6. The ends of the two converging covers 8 are both connected with outer sealing rings 9. The internal chamber of the chamber pressure adjustment chamber 4 is filled with a marking liquid. It should be noted that: a high-speed air flow is generated by the shock tunnel in the simulated wind tunnel detonation chamber 1 and enters the simulated test chamber 2. 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 this field and will not be elaborated here. Before testing the nozzle 3, the head of the nozzle 3 is placed between two converging covers 8. Subsequently, the converging covers 8 are slid on the limit slide rails 7 to make the two converging covers 8 dock with each other. During this process, the inner sealing ring 6 and the outer sealing ring 9 are pressed against each other to form an assembled annular sealing belt. Then, the fastening bolts 10 on the converging covers 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 in a mist form from multiple arc-shaped spray covers 5 by means of high-pressure pumping, so that the subsequent mist-like marking liquid can flow along with the high-pressure air flow; Based on the above advantages: The converging covers 8 can be slid and docked on the limit slide rails 7 to limit the head of the nozzle 3, which is convenient for subsequent simulation of the state where the nozzle 3 faces the air flow directly, making the detection effect more in line with the actual use state; A plurality of protective baffles 11 are arranged on the outer side of the tail of the nozzle 3. The outer side wall of the protective baffle 11 is connected with a buffer piston plate 13 through two struts 12. The buffer piston plate 13 is connected with a liquid buffer assembly for buffering and then supporting the nozzle 3 when it is shocked. An installation telescopic column 18 is arranged on the liquid buffer assembly. Auxiliary support components are arranged on both the left and right sides of the installation telescopic column 18. The end of the protective baffle 11 is connected with a vibration amplification plate 31; Further, the liquid buffer assembly is composed 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 with the strut 12. The strut 12 is slidably connected with the liquid buffer cylinder 14 through the buffer piston plate 13. The bottoms of the plurality of liquid buffer channels 15 communicate with the middle part of the liquid buffer cylinder 14 respectively. The top of the liquid buffer channel 15 is communicated with a buffer cavity 16. The top end of the buffer cavity 16 is fixedly connected with the installation telescopic column 18 through an adapter plate. The side wall of the adapter plate is fixedly connected with a diversion inclined plate 17 through a cross plate. The auxiliary support component is composed of a threaded support rod 21 and a screwed-out impeller 22. The adapter plate is fixedly connected with a threaded sleeve 20. The threaded sleeve 20 is threadedly connected with the threaded support rod 21. The threaded support rod 21 is fixedly connected with the screwed-out impeller 22. The installation telescopic column 18 is fixedly connected with the inner side wall of the simulated test chamber 2. Two symmetrically arranged limit plates 19 are fixedly connected to the side wall of the installation telescopic column 18. The adapter plate is fixedly connected with a laser sensor 30 through a right-angle rod. The end of the protective baffle 11 is fixedly connected with an induction plate 32 through a vibration amplification plate 31. The laser sensor 30 and the induction part of the induction plate 32 are symmetrically arranged; It should be noted that: The diversion inclined plate 17 is arranged at the front end of the adapter plate. The side of the diversion inclined plate 17 facing the simulated wind tunnel detonation chamber 1 is the windward side, that is, the inclined surface of the diversion inclined plate 17 is V-shaped. During the test, the diversion inclined plate 17 will guide the airflow to avoid continuous wind pressure on the test device. Among them, the airflow blows the screw-out impeller 22, causing the screw-out impeller 22 to rotate and drive the threaded support rod 21 to rotate in the threaded sleeve 20, so that the threaded support rod 21 continuously screws out in the threaded sleeve 20. Wait until the external thread of the threaded support rod 21 rotates to the end of the internal thread of the threaded sleeve 20 and stops (the final screw-out lengths of the two threaded support rods 21 are the same, so as to maintain stable limit for the installation telescopic column 18. After the test of the nozzle 3 is completed, screw the threaded support rod 21 into the threaded sleeve 20 to release the extended limit of the installation telescopic column 18), and let the threaded support rod 21 move outwards and continuously press against the limit plate 19, so that the installation telescopic column 18 extends, driving the protective baffle 11 to fit on the outer side wall of the tail of the nozzle 3. If the air pressure inside the nozzle 3 is lower than the external air pressure, a shock wave phenomenon will occur in the nozzle 3, and the unrestrained tail of the nozzle 3 will vibrate at a certain frequency. During this process, the displacement of the protective baffle 11 will push the buffer piston plate 13 through the support column 12. Among them, the support column 12 and the buffer piston plate 13 are connected by a universal joint-like 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 and buffering the movement of the buffer piston plate 13. During continuous vibration, the protective baffle 11 will drive the vibration amplification plate 31 to move together. The characteristics of the thin plate at the edge of the vibration amplification plate 31 will amplify the vibration, increasing the offset amplitude of the induction plate 32 on the vibration amplification plate 31, which is convenient 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, so that the hydraulic oil in the liquid buffer cylinder 14 cannot flow, turning 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 expand; Based on the above benefits: In this way, the vibration amplitude and frequency of the nozzle 3 can be detected by using the protective baffle 11 at a low vibration amplitude of the nozzle 3. At a high vibration amplitude of the nozzle 3, the hydraulic buffer is transformed into a relatively rigid support to avoid structural damage caused by a large vibration amplitude of the nozzle 3, ensuring the safety of the nozzle 3 during the test; Four fixing frames 24 are respectively connected to the inner side wall of the simulation test chamber 2 through four bolt locking cylinders 23. The fixing frame 24 is connected with a probe rod 25. A flow measurement component is arranged on the probe rod 25. The outer side wall of the probe rod 25 is connected with a reinforcing ring 27 through a plurality of reinforcing rods. An inner support component is arranged on the outer side wall of the reinforcing ring 27; Further, the flow measurement assembly includes a plurality of dynamic cameras 26. A plurality of storage grooves are formed in the probe rod 25. The inner side walls of the storage grooves are fixedly connected to the plurality of dynamic cameras 26. The side walls of the storage grooves are fixedly connected with glass covers. 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 reinforcing ring 27 are respectively 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. A pressure sensor is arranged in the pressure-sensitive support column 28; It should be noted that during the installation of the nozzle 3, the probe rod 25 is inserted into the axial center position of the nozzle 3. Subsequently, the end of the retainer 24 is locked and limited through the bolt locking cylinder 23, so that the plurality of inner support arc plates 29 are placed on the inner wall of the tail end of the nozzle 3. By changing the chamber pressure in the nozzle 3, the chamber pressure in the nozzle 3 is made lower than the external wind pressure. Then, the exhaust part at the tail end of the nozzle 3 will continuously receive an inward pressure. Then, the inner support arc plate 29 will continuously maintain rigid support for the inner wall of the tail end of the nozzle 3 to avoid deformation of the nozzle 3 under pressure. At the same time, the pressure sensor in the pressure-sensitive support column 28 will also monitor the pressure condition received by the inner support arc plate 29 in real time. The airflow in the nozzle 3 drives the mist-like marking liquid to flow together during the flow process. Then, the dynamic camera 26 in the storage groove of the probe rod 25 will continuously capture the flow state of the mist-like marking liquid, simulating the flow states of the airflow at different parts in the integrated nozzle 3, increasing the simulation test data of the airflow inside the nozzle 3. Among them, abnormal flow in the nozzle 3 will cause the shock wave surface to deviate from the designed shape. The position deviation of the shock wave can be observed through the atomization trajectory of the fluorescent marking liquid. At this time, the dynamic camera 26 will capture the abnormal region of the flow field brightness gradient. And when the airflow is abnormal, the boundary layer separation point moves forward, and the fluorescent particles form obvious vortex clusters in the separation region, resulting in a sudden increase in local negative pressure detected by the pressure sensor; The benefits based on the above are as follows: In this way, the plurality of inner support arc plates 29 can be used to continuously provide rigid support for the inner wall of the tail part of the nozzle 3, avoiding deformation of the airflow outlet of the nozzle 3 under pressure. At the same time, the plurality of dynamic cameras 26 cooperate with the mist-like marking liquid in the airflow, which is convenient for increasing the test data of the airflow flow state inside the integrated nozzle 3, making the detection more comprehensive; When the present invention is in use, a high-speed air flow is generated by a shock tunnel in the simulated wind tunnel detonation chamber 1 and enters the simulated test chamber 2. 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 elaborated here. Before testing the nozzle 3, the head of the nozzle 3 is placed between two converging covers 8. Subsequently, the converging covers 8 are slid on the limit slide rails 7 to make the two converging covers 8 butt against each other. During this process, the inner sealing ring 6 and the outer sealing ring 9 are pressed against each other to form an assembled annular sealing band. Then, the fastening bolts 10 on the converging covers 8 are tightened to limit the head of the nozzle 3. The marked liquid in the chamber pressure adjustment chamber 4 has a fluorescent color and is sprayed in a mist form from multiple arc-shaped spray covers 5 by means of high-pressure pumping, facilitating the subsequent flow of the mist-shaped marked liquid along with the high-pressure air flow. In this way, the converging covers 8 can be slid and butted on the limit slide rails 7 to limit the head of the nozzle 3, facilitating the subsequent simulation of the state where the nozzle 3 faces the air flow directly, making the detection effect more conform to the actual use state; The vibration amplitude and frequency of the nozzle 3 are detected by using the protective baffle 11 under the condition of low vibration amplitude of the nozzle 3. Under the condition of high vibration amplitude of the nozzle 3, the hydraulic buffer is transformed into a relatively rigid support to avoid structural damage caused by a large vibration amplitude of the nozzle 3, ensuring the safety of the nozzle 3 during the test; Multiple inner support arc plates 29 are used to continuously provide rigid support for the inner wall of the tail of the nozzle 3 to prevent the air flow outlet of the nozzle 3 from being deformed under pressure. At the same time, multiple dynamic cameras 26 cooperate with the mist-shaped marked liquid in the air flow, facilitating the increase of test data on the air flow state inside the integrated nozzle 3 and making the detection more comprehensive.

[0024] The above is only a preferred specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention, according to the technical solution and inventive concept of the present invention, making equivalent substitutions or changes should be covered within the protection scope 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 simulation test chamber (2) for conducting a simulation test on a nozzle (3), characterized in that, The inner sidewall of the simulation test chamber (2) is connected with a chamber pressure adjustment cavity (4) through two mounting plates. The inner sidewall of the chamber pressure adjustment cavity (4) is connected with a plurality of arc-shaped spray nozzles (5). The end of the chamber pressure adjustment cavity (4) is connected with a limiting component for mounting the head of the nozzle (3). A plurality of protective baffles (11) are arranged on the outer side of the tail of the nozzle (3). The outer sidewall of the protective baffle (11) is connected with a buffer piston plate (13) through two support columns (12). The buffer piston plate (13) is connected with a liquid buffer component for buffering and then supporting the nozzle (3) when a shock wave occurs. An installation telescopic column (18) is arranged on the liquid buffer component. Auxiliary support components are arranged on both the left and right sides of the installation telescopic column (18). The end of the protective baffle (11) is connected with a vibration amplification plate (31). The inner sidewall of the simulation test chamber (2) is respectively connected with four retaining frames (24) through four bolt locking cylinders (23). The retaining frame (24) is connected with a probe rod (25). A flow measurement component is arranged on the probe rod (25). The outer sidewall of the probe rod (25) is connected with a reinforcing ring (27) through a plurality of reinforcing rods. An inner support component is arranged on the outer sidewall of the reinforcing ring (27).

2. The anti-deformation simulation test device for a rocket thrust member according to claim 1, characterized in that, The limiting component is composed of two limiting slide rails (7) and two limiting retracting covers (8). The outer sidewall of the chamber pressure adjustment cavity (4) is fixedly connected with the limiting slide rail (7) through a fixing plate. The limiting slide rail (7) is slidably connected with the retracting cover (8). Tightening bolts (10) are arranged at both the top and bottom of the retracting cover (8).

3. The anti-deformation simulation test device for a rocket thrust component according to claim 2, wherein, A plurality of arc-shaped through grooves for installing the arc-shaped spray nozzles (5) are formed in the inner sidewall of the chamber pressure adjustment cavity (4). The end of the chamber pressure adjustment cavity (4) is connected with an inner sealing ring (6). Outer sealing rings (9) are connected to the ends of both the retracting covers (8). The internal cavity of the chamber pressure adjustment cavity (4) is filled with a marking liquid.

4. A deformation prevention simulation test device for a rocket thrust component according to claim 1, characterized in that, The liquid buffer component is composed of a liquid buffer cylinder (14) and a plurality of liquid buffer channels (15). The outer sidewall of the protective baffle (11) is fixedly connected with the support column (12). The support column (12) is slidably connected with the liquid buffer cylinder (14) through the buffer piston plate (13).

5. The anti-deformation simulation test device for a rocket thrust member according to claim 4, characterized in that, The bottoms of a plurality of the liquid buffer channels (15) communicate with the middle of the liquid buffer cylinder (14) respectively. The top of the liquid buffer channel (15) is communicated with a buffer cavity (16). The top end of the buffer cavity (16) is fixedly connected with the installation telescopic column (18) through an adapter plate. A flow guiding inclined plate (17) is fixedly connected to the sidewall of the adapter plate through a cross plate.

6. The anti-deformation simulation test device for a rocket thrust component according to claim 5, characterized in that, The auxiliary support component is composed of a threaded support rod (21) and a screw-out impeller (22). The adapter plate is fixedly connected with a threaded sleeve (20). The threaded sleeve (20) is threadedly connected with the threaded support rod (21). The threaded support rod (21) is fixedly connected with the screw-out impeller (22). The installation telescopic column (18) is fixedly connected with the inner sidewall of the simulation test chamber (2). Two symmetrically arranged limiting plates (19) are fixedly connected to the sidewall of the installation telescopic column (18).

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

8. A deformation prevention simulation test device for a rocket thrust member according to claim 1, characterized in that, The flow measurement assembly includes a plurality of dynamic cameras (26). A plurality of storage grooves are formed in the probe rod (25). The inner side walls of the storage grooves are fixedly connected with the plurality of dynamic cameras (26). A glass cover is fixedly connected to the side wall of the storage groove.

9. A deformation prevention simulation test device for a rocket thrust component 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 wall of the reinforcement ring (27) is fixedly connected with the inner side walls of the plurality of inner support arc plates (29) through the plurality of pressure-sensitive support columns (28). A pressure sensor is arranged in the pressure-sensitive support column (28).

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