An experimental device and method for simulating non-uniform rocket kerosene vapor cloud combustion in an oxygen-rich atmosphere

Abstract

The application discloses a kind of simulation non-uniform rocket kerosene vapor cloud combustion experiment device and method in oxygen-rich atmosphere, including simulation oxygen-rich atmosphere tank, gas supply system, heating temperature control system, multi-channel electric ignition system, data test acquisition system and exhaust system;Gas supply system is connected in sequence external oxygen gas cylinder, gas flowmeter, one-way valve to oxygen-rich atmosphere tank;Silicone rubber electric hot plate in heating temperature control system is fixed in the inner wall of oxygen-rich atmosphere tank, oil pool heater is fixed in the bottom of oxygen-rich atmosphere tank;Multi-channel electric ignition system includes adjustable igniter, ignition electrode;In data test acquisition system, hydrocarbon sensor, first oxygen sensor extends to outside multichannel data acquisition module, transmission module and computer;The exhaust system is respectively connected with second oxygen sensor and vacuum pump.The application simulates non-uniform concentration field distribution formed by rocket kerosene heated evaporation diffusion in oxygen-rich atmosphere under actual environmental conditions and tests its vapor cloud combustion characteristics, with good reliability and strong practicability.

Description

Technical Field

[0001] This invention relates to the technical field of flammable liquid combustion and explosion testing devices, and more specifically to an experimental device and method for simulating non-uniform rocket kerosene vapor cloud combustion and explosion in an oxygen-rich atmosphere. Background Technology

[0002] Among the various accident risks at space launch sites, propellant leakage leading to fire and explosion is the most serious catastrophic accident. Therefore, in addition to actively preventing propellant leakage, further controlling the risk of fire and explosion of leaked propellant is a crucial technical aspect affecting the launch safety of high-thrust rockets. Rocket kerosene is a type of fuel that is prone to leakage, has a high calorific value, and is highly dangerous. It is prone to leakage during transportation, storage, and use, and may form a combustible vapor cloud with a non-uniform concentration field in a certain space. Once it encounters an ignition source in air or a high-concentration oxygen atmosphere (hereinafter referred to as "oxygen-rich atmosphere"), it is more likely to cause combustion and explosion accidents. Therefore, studying the explosion characteristics of rocket kerosene vapor clouds in oxygen-rich atmospheres is of great significance for preventing rocket kerosene vapor cloud explosion accidents.

[0003] Currently, there is limited research both domestically and internationally on testing systems for the combustion and explosion characteristics of combustible fuels. Instead, there is considerable research on the combustion and explosion characteristics and suppression of combustible gases or dusts. However, these studies are generally conducted at room temperature and pressure in narrow pipes or cylindrical or spherical experimental devices with a limited volume (below 100L). This differs significantly from real-world environments, and the experimental results obtained are not particularly relevant for guiding combustion and explosion research in larger spaces. Furthermore, they cannot realistically simulate the combustion and explosion process of combustible vapor clouds in a non-uniform concentration field that actually exists. Therefore, to study the combustion and explosion characteristics of combustible fuel vapors, especially to test the combustion and explosion characteristics of vapor clouds in a non-uniform concentration field formed by the thermal evaporation and diffusion of rocket kerosene in an oxygen-rich atmosphere, it is necessary to invent an experimental device capable of simulating the combustion and explosion of a non-uniform rocket kerosene vapor cloud in an oxygen-rich atmosphere. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to provide an experimental device and method for simulating the combustion and explosion of a non-uniform rocket kerosene vapor cloud in an oxygen-rich atmosphere.

[0005] This invention solves the aforementioned technical problems through the following technical means: an experimental device for simulating the combustion and explosion of a non-uniform rocket kerosene vapor cloud in an oxygen-enriched atmosphere, comprising a simulated oxygen-enriched atmosphere tank, a heating and temperature control system, a gas supply system, a multi-channel electric ignition system, a data testing and acquisition system, and an exhaust system. The simulated oxygen-enriched atmosphere tank is a 100L cylindrical pressure-resistant tank capable of withstanding a gas pressure of 1MPa; the side wall of the simulated oxygen-enriched atmosphere tank is provided with two observation windows and six through holes; the through holes are respectively connected to a pressure relief valve, the pipeline of the gas supply system, the circuit of the heating and temperature control system, the exhaust pipeline, the circuit of the data acquisition system, and a pressure transmitter.

[0006] Specifically, an experimental device for simulating non-uniform rocket kerosene vapor cloud combustion and explosion in an oxygen-enriched atmosphere includes a simulated oxygen-enriched atmosphere tank (1), a gas supply system, a heating and temperature control system, a multi-channel electric ignition system, a data testing and acquisition system, and an exhaust system.

[0007] The simulated oxygen-enriched atmosphere tank (1) is a sealed cylindrical structure with an observation window (16) on its side wall;

[0008] The gas supply system includes a one-way valve (21), a gas flow meter (22), and an external oxygen cylinder (23). The external oxygen cylinder (23) is connected in sequence to the one-way valve (21), the gas flow meter (22), and the simulated oxygen-enriched atmosphere tank (1).

[0009] The heating and temperature control system includes a silicone rubber heating plate (31), a constant temperature controller (32), a fixed bracket (33), and an oil bath heater (34); the silicone rubber heating plate (31) is fixed on the inner wall of the simulated oxygen-enriched atmosphere tank (1); the constant temperature controller (32) is connected to the oil bath heater (34); the oil bath heater (34) is fixed at the bottom center of the simulated oxygen-enriched atmosphere tank (1) through the fixed bracket (33);

[0010] The multi-channel electric ignition system includes an adjustable igniter (41) and an ignition electrode (42), which are connected together.

[0011] The data testing and acquisition system includes a hydrocarbon sensor (51), a first oxygen sensor (52), a multi-channel data acquisition module (53), a transmission module (54), and a pressure transmitter (7); the ignition electrode (42) is connected to the multi-channel data acquisition module (53); the hydrocarbon sensor (51) and the first oxygen sensor (52) are installed inside the simulated oxygen-enriched atmosphere tank (1); the pressure transmitter (7) is fixed to the side wall of the simulated oxygen-enriched atmosphere tank (1); the hydrocarbon sensor (51) and the first oxygen sensor (52) are respectively connected to the multi-channel data acquisition module (53); the multi-channel data acquisition module (53) is connected to the transmission module (54);

[0012] The exhaust system includes a three-way valve (61), a second oxygen sensor (62), and a vacuum pump (63); the vacuum pump (63) is connected in sequence to the three-way valve (61), the second oxygen sensor (62), and the simulated oxygen-enriched atmosphere tank (1).

[0013] Preferably, the observation window in the simulated oxygen-enriched atmosphere tank is a transparent fire-resistant glass panel, which facilitates the use of appropriate camera equipment to obtain combustion and explosion experimental phenomena.

[0014] Preferably, the simulated oxygen-enriched atmosphere tank is made of 304 stainless steel.

[0015] The gas supply system includes an inlet pipe, a one-way valve, a gas flow meter, and an external oxygen cylinder. The external oxygen cylinder is connected to the inside of the tank through a through-hole I via a gas flow meter, a one-way valve, and an inlet pipe. The oxygen atmosphere of different concentrations inside the tank is effectively adjusted by the inlet purging method.

[0016] The multi-channel electric ignition system includes ignition electrodes, adjustable igniters, and connecting lines. The multi-channel ignition electrodes are installed inside the simulated oxygen-enriched atmosphere tank via gantry-type linear modules and adjustable positioning brackets, and are positioned at different heights directly above the center of the oil tank heater.

[0017] Preferably, the ignition electrode consists of a discharge probe and an insulating sleeve, with the discharge probe fixed inside the insulating sleeve.

[0018] The data testing and acquisition system includes a first oxygen sensor, a hydrocarbon sensor, a temperature feedback thermocouple, a multi-channel data acquisition module, a transmission module, and a computer. The first oxygen sensor and hydrocarbon sensor are connected to the multi-channel data acquisition module, transmission module, and computer via through-hole II. The first oxygen sensor and hydrocarbon sensor are fixed at different heights above the oil tank heater using positioning brackets, enabling effective monitoring of oxygen and kerosene vapor cloud concentrations at different heights away from the liquid rocket kerosene surface. The temperature feedback thermocouple is also fixed at different heights above the oil tank heater, enabling effective recording of air temperature and temperature changes after combustion.

[0019] The heating and temperature control system includes an oil bath heater, a silicone rubber heating plate, a constant temperature controller, and a temperature feedback thermocouple. The oil bath heater is positioned at the bottom center of the simulated oxygen-rich atmosphere tank via a fixed bracket, thereby heating and evaporating the rocket kerosene. The silicone rubber heating plate is fixed to the inner wall of the tank. The temperature feedback thermocouple is fixed to the bottom center of the oil bath and the heating plate of the oil bath heater, enabling precise control of the air temperature and oil bath temperature inside the tank. The constant temperature controller, located outside the tank, is connected to the oil bath heater and the silicone rubber heating plate through a through-hole III at the bottom of the tank, enabling the temperature to be adjusted to a specified range.

[0020] Preferably, in the heating and temperature control system, the temperature feedback thermocouple extends from the bottom of the tank through through hole III to the outside and is connected to the temperature data acquisition system.

[0021] The exhaust system includes an exhaust pipe, a second oxygen sensor, and a vacuum pump. The vacuum pump is connected to the side wall through hole IV via the exhaust pipe and the second oxygen sensor in sequence. The vacuum pump quickly and effectively extracts air from the tank, and the second oxygen sensor measures the oxygen concentration in the tank.

[0022] The pressure transmitter is connected to the tank through through hole V, and can accurately record the change process of pressure signal before and after the explosion and collect data through a computer.

[0023] Preferably, the pressure transmitter is an explosion-proof pressure transmitter controller, which can measure dynamic pressure changes with accuracy down to the millisecond level.

[0024] This invention also provides a method for simulating a non-uniform rocket kerosene vapor cloud combustion explosion experiment in an oxygen-enriched atmosphere using any of the above-described schemes, comprising the following steps: checking the airtightness, closing the one-way valve switch of the gas supply system, turning on the vacuum pump of the exhaust system, monitoring the change in the pressure transmitter value to negative pressure, turning off the vacuum pump, and turning on the gas supply system and external oxygen cylinder, introducing oxygen of a predetermined concentration into the simulated oxygen-enriched atmosphere tank through air purging, ensuring the oxygen atmosphere in the tank through the second oxygen sensor in the exhaust pipe, and after the oxygen concentration and pressure reach the preset values, turning off the external oxygen cylinder, controlling the oil pool heater and silicone rubber heating plate through a constant temperature controller, and monitoring the temperature feedback thermocouple to reach the preset value, detecting the numerical change of the non-uniform concentration field through the first oxygen sensor and hydrocarbon sensor, determining the equivalence ratio of oxygen to rocket kerosene, determining the ignition position through a gantry-type linear module, and then using an adjustable igniter to adjust the ignition energy of the ignition electrode to conduct the ignition experiment, and after the experiment is completed, turning on the external oxygen cylinder for re-purging, and repeating the above steps until the experiment is completed.

[0025] Compared with existing technologies, the advantages of this invention are as follows: The heating and temperature control system allows for accurate temperature control, effectively solving the difficulties in experimentation and measurement caused by numerous influencing factors that must be considered in combustion and explosion experiments under conditions higher than normal temperature and pressure. The pressure transmitter allows for effective observation of pressure changes during the combustion and explosion of rocket kerosene vapor clouds. The simulated oxygen-rich atmosphere tank is equipped with a pressure relief valve that activates when the pressure exceeds 1 MPa, effectively protecting the device and ensuring the health and safety of experimental personnel. The first oxygen sensor and hydrocarbon sensor allow for online monitoring of the concentration distribution of oxygen and kerosene vapor clouds in a non-uniform concentration field, providing a basis for the combustion equivalence ratio for ignition location. Furthermore, this invention effectively solves technical problems in existing experimental devices, such as simulating oxygen-rich atmospheres, heating methods, electric ignition methods, and air intake and exhaust methods, effectively improving the practicality and accuracy of the device and providing experimental basis for testing the combustion and explosion of combustible liquid vapor clouds with non-uniform concentration fields. Attached Figure Description

[0026] Figure 1 This is a schematic diagram of the overall structure of an experimental device and method for simulating non-uniform rocket kerosene vapor cloud combustion and explosion in an oxygen-rich atmosphere according to Embodiment 1 of the present invention.

[0027] Figure 2 This is a schematic diagram of the ignition system control platform and measurement structure according to Embodiment 1 of the present invention.

[0028] In the diagram: 1-Simulated oxygen-enriched atmosphere tank; 11-Through hole I; 12-Through hole II; 13-Through hole III; 14-Through hole IV; 15-Through hole V; 16-Observation window; 21-One-way valve; 22-Gas flow meter; 23-External oxygen cylinder; 31-Silicone rubber heating plate; 32-Constant temperature controller; 33-Fixed bracket; 34-Oil bath heater; 41-Adjustable igniter; 42-Ignition electrode; 51-Hydrocarbon sensor; 52-First oxygen sensor; 53-Multi-channel data acquisition module; 54-Transmission module; 55-Computer; 61-Three-way valve; 62-Second oxygen sensor; 63-Vacuum pump; 7-Pressure transmitter; 8-Pressure relief valve; 9-Gantry linear module; 91-Gantry linear module bracket; 92-Gantry linear module stepper motor; 93-Connecting orifice plate; 94-Lead screw. Detailed Implementation

[0029] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below in conjunction with the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0030] See Figure 1 This embodiment discloses an experimental device for simulating non-uniform rocket kerosene vapor cloud combustion and explosion in an oxygen-enriched atmosphere, including a simulated oxygen-enriched atmosphere tank 1, a gas supply system, a heating and temperature control system, a multi-channel electric ignition system, a data testing and acquisition system, and an exhaust system.

[0031] See Figure 1 The simulated oxygen-enriched atmosphere container 1 is a sealed cylindrical structure. The side wall of the simulated oxygen-enriched atmosphere container 1 is provided with through holes I11, II12, III13, IV14, V15, and two observation windows 16. The observation windows 16 in the simulated oxygen-enriched atmosphere container are transparent fire-resistant glass panels, which facilitate the acquisition of combustion and explosion experimental phenomena using appropriate camera equipment. The simulated oxygen-enriched atmosphere container is made of 304 stainless steel.

[0032] See Figure 1 The gas supply system includes a one-way valve 21, a gas flow meter 22, and an external oxygen cylinder 23, which effectively simulates oxygen atmospheres of different concentrations through air intake purging. The external oxygen cylinder 23 is connected in sequence to the gas flow meter 22, the one-way valve 21, and the through-hole I11.

[0033] See Figure 1The heating and temperature control system includes a silicone rubber heating plate 31, a constant temperature controller 32, a fixed bracket 33, and an oil bath heater 34. Through temperature feedback thermocouples, it can precisely control the air temperature and oil bath temperature inside the simulated oxygen-enriched atmosphere tank 1, effectively solving experimental problems related to existing insulation and heating methods. The silicone rubber heating plate 31 is fixed to the inner wall of the simulated oxygen-enriched atmosphere tank 1. The oil bath heater 34 is fixed to the center of the bottom of the simulated oxygen-enriched atmosphere tank 1 via the fixed bracket 33, and its temperature is precisely controlled by the constant temperature controller 32. Multiple temperature feedback thermocouples are respectively fixed to the center of the bottom of the oil bath in the oil bath heater 34 and to the silicone rubber heating plate 31, enabling precise control of the air temperature and oil bath temperature inside the tank. The constant temperature controller 32, located outside the tank, is connected to the oil bath heater 34 and the silicone rubber heating plate 31 through a through-hole III 13 at the bottom of the tank, allowing the temperature to be adjusted to a specified range.

[0034] See Figure 1 , 2 The multi-channel electric ignition system includes an adjustable igniter 41 and an ignition electrode 42. The ignition position under non-uniform concentration fields is determined by detecting the oxygen / rocket kerosene vapor concentration equivalence ratio using a hydrocarbon sensor 51 and a first oxygen sensor 52. Simultaneously, the adjustable igniter 41 can adjust the electric ignition energy from millijoules to cokes, achieving different energy electric ignition conditions. The ignition electrode 42 is located inside the simulated oxygen-enriched atmosphere tank 1, and is connected to the adjustable igniter 41 and the multi-channel data acquisition module 53 via through-hole II 12. The multi-channel data acquisition module 53 is sequentially connected to the transmission module 54 and the computer 55. The multi-channel ignition electrode 42 is fixed on a gantry-type linear module bracket 91 and positioned at different heights directly above the center of the oil bath heater 34. The ignition electrode consists of a discharge probe and an insulating sleeve, with the discharge probe fixed inside the insulating sleeve.

[0035] See Figure 1 , 2The data testing and acquisition system includes a hydrocarbon sensor 51, a first oxygen sensor 52, a temperature feedback thermocouple, a multi-channel data acquisition module 53, a transmission module 54, a computer 55, and a pressure transmitter 7. The hydrocarbon sensor 51 and the first oxygen sensor 52 can measure the non-uniform concentration of oxygen / rocket kerosene vapor at different locations and provide concentration equivalence ratio data support for electric ignition. The pressure transmitter 7 can accurately record the millisecond-level pressure signal changes before and after the explosion. The temperature feedback thermocouple is installed inside the simulated oxygen-enriched atmosphere tank 1 and is connected to the multi-channel data acquisition module 53. The hydrocarbon sensor 51 and the first oxygen sensor 52 are also fixed on the gantry-type linear module bracket 91 in the data testing and acquisition system. The first oxygen sensor 52 and the hydrocarbon sensor 51 are connected sequentially to the multi-channel data acquisition module 53, the transmission module 54, and the computer 55 through through-hole II 12. The pressure transmitter 7 is connected to the multi-channel data acquisition module 53. The pressure transmitter 7 is fixed to the side wall of the simulated oxygen-enriched atmosphere tank 1 through through hole V15. The first oxygen sensor 52 and hydrocarbon sensor 51 are fixed at different heights above the oil tank heater 34 by positioning brackets, which can effectively monitor the oxygen and kerosene vapor cloud concentrations at different heights away from the liquid rocket kerosene surface. In addition, multiple temperature feedback thermocouples are also fixed at different heights above the oil tank heater 34, which can effectively record the air temperature and the temperature change after combustion.

[0036] See Figure 1 The exhaust system includes a three-way valve 61, a second oxygen sensor 62, and a vacuum pump 63. The second oxygen sensor 62 determines the oxygen atmosphere in the simulated oxygen-enriched atmosphere tank 1. The vacuum pump 63 is connected in sequence to the three-way valve 61 and the second oxygen sensor 62. The second oxygen sensor 62 extends into the simulated oxygen-enriched atmosphere tank 1 through through hole IV14.

[0037] In this embodiment, a pressure relief valve 8 is fixedly installed on the top of the simulated oxygen-enriched atmosphere tank 1. When the pressure exceeds 1 MPa, it will activate, effectively protecting the device and ensuring the life and health of the experimental personnel.

[0038] In this embodiment, a gantry-type linear module 9 is installed inside the simulated oxygen-enriched atmosphere tank 1. This module includes a gantry-type linear module support 91, a gantry-type linear module stepper motor 92, and a connecting perforated plate 93. The gantry-type linear module support 91 includes a lead screw 94 and a positioning bracket. The gantry-type linear module 9 can position the ignition system to different heights in a non-uniform concentration field. The positioning bracket is fixed to the lead screw 94 via the connecting perforated plate 93. Each positioning bracket is equipped with a hydrocarbon sensor 51 and a first oxygen sensor 52. An ignition electrode 42 is provided at one end of each positioning bracket. The gantry-type linear module stepper motor 92 is mounted on the lead screw 94. The gantry-type linear module stepper motor 92 drives the gantry-type linear module support 91 to move.

[0039] The method for conducting the experiment using the above-mentioned combustion device is as follows: Check the airtightness, close the one-way valve 21 switch of the gas supply system, turn on the vacuum pump 63 of the exhaust system, monitor the change of the pressure transmitter 7 value to -0.1MPa, turn off the vacuum pump 63, and turn on the gas supply system and the external oxygen cylinder 23. Introduce a certain concentration of oxygen into the simulated oxygen-enriched atmosphere tank 1 through intake purging. Ensure the oxygen atmosphere inside the simulated oxygen-enriched atmosphere tank 1 through the second oxygen sensor 62 in the exhaust pipe. After the oxygen concentration and pressure reach the preset values, turn off the external oxygen cylinder 23. The gas cylinder 23 controls the oil tank heater 34 and the silicone rubber heating plate 31 through the constant temperature controller 32, and monitors the temperature feedback thermocouple to reach the preset value. The changes in the non-uniform concentration field are detected by the hydrocarbon sensor 51 and the first oxygen sensor 52. After determining the equivalence ratio of oxygen and rocket kerosene, the ignition position is determined by the gantry linear module 9. Then, the ignition energy of the ignition electrode 42 is adjusted by the adjustable igniter 41 to conduct the ignition experiment. After the experiment, the external oxygen cylinder is opened for rescanning. The above steps are repeated until the experiment is completed.

[0040] The above embodiments are only used to illustrate the technical solutions of the present invention, and are not intended to limit it. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. An experimental apparatus for simulating the combustion and explosion of a non-uniform rocket kerosene vapor cloud in an oxygen-rich atmosphere, characterized in that, It includes a simulated oxygen-enriched atmosphere tank (1), an air supply system, a heating and temperature control system, a multi-channel electric ignition system, a data testing and acquisition system, and an exhaust system; The simulated oxygen-enriched atmosphere tank (1) is a sealed cylindrical structure. The simulated oxygen-enriched atmosphere tank (1) is fixedly equipped with a pressure relief valve (8). The simulated oxygen-enriched atmosphere tank (1) is a pressure-resistant tank that can withstand a gas pressure of 1MPa. The side wall is provided with two observation windows (16) and six through holes. The through holes are respectively connected to the pressure relief valve (8), the gas supply system pipeline, the heating and temperature control system line, the exhaust pipeline, the data acquisition system line, and the pressure transmitter (7). The gas supply system includes a one-way valve (21), a gas flow meter (22) and an external oxygen cylinder (23). The external oxygen cylinder (23) is connected in sequence to the one-way valve (21), the gas flow meter (22) and the simulated oxygen-enriched atmosphere tank (1). Different concentrations of oxygen-enriched atmosphere are simulated by the air intake purging method. The heating and temperature control system includes a silicone rubber heating plate (31), a constant temperature controller (32), a fixed bracket (33), and an oil bath heater (34); the silicone rubber heating plate (31) is fixed on the inner wall of the simulated oxygen-enriched atmosphere tank (1); the constant temperature controller (32) is connected to the oil bath heater (34); the oil bath heater (34) is fixed at the bottom center of the simulated oxygen-enriched atmosphere tank (1) through the fixed bracket (33); The multi-channel electric ignition system includes an adjustable igniter (41) and an ignition electrode (42), which are connected together. The multi-channel ignition electrode (42) is installed inside the simulated oxygen-enriched atmosphere tank (1) through a gantry-type linear module (9) and an adjustable positioning bracket, and is positioned at different heights directly above the center of the oil bath heater (34). The data testing and acquisition system includes a hydrocarbon sensor (51), a first oxygen sensor (52), a multi-channel data acquisition module (53), a transmission module (54), and a pressure transmitter (7). The pressure transmitter (7) uses an explosion-proof pressure transmitter controller, which can accurately measure dynamic pressure changes down to the millisecond level. The ignition electrode (42) is connected to the multi-channel data acquisition module (53). The hydrocarbon sensor (51) and the first oxygen sensor (52) are installed inside the simulated oxygen-enriched atmosphere tank (1). The hydrocarbon sensor (51) and the first oxygen sensor (52) are fixed at different heights above the oil tank heater (34) by positioning brackets, which can effectively monitor the oxygen and kerosene vapor cloud concentrations at different heights away from the liquid rocket kerosene surface. The pressure transmitter (7) is fixed to the side wall of the simulated oxygen-enriched atmosphere tank (1). The hydrocarbon sensor (51) and the first oxygen sensor (52) are respectively connected to the multi-channel data acquisition module (53). The multi-channel data acquisition module (53) is connected to the transmission module (54). The exhaust system includes a three-way valve (61), a second oxygen sensor (62), and a vacuum pump (63); the vacuum pump (63) is connected in sequence to the three-way valve (61), the second oxygen sensor (62), and the simulated oxygen-enriched atmosphere tank (1), and the oxygen concentration in the simulated oxygen-enriched atmosphere tank (1) is tested by the second oxygen sensor (62); The constant temperature controller (32) is located outside the simulated oxygen-enriched atmosphere tank (1), and the fixed bracket (33) and the oil bath heater (34) are located inside the simulated oxygen-enriched atmosphere tank (1). The adjustable igniter (41) is located outside the simulated oxygen-enriched atmosphere tank (1); The multi-channel data acquisition module (53) and the transmission module (54) are located outside the simulated oxygen-enriched atmosphere tank (1).

2. The experimental apparatus for simulating non-uniform rocket kerosene vapor cloud combustion and explosion in an oxygen-rich atmosphere according to claim 1, characterized in that, The simulated oxygen-enriched atmosphere tank (1) is equipped with a gantry-type linear module (9), and the ignition electrode (42), hydrocarbon sensor (51), and first oxygen sensor (52) are all fixed on the gantry-type linear module (9).

3. The experimental apparatus for simulating non-uniform rocket kerosene vapor cloud combustion and explosion in an oxygen-rich atmosphere according to claim 2, characterized in that, The gantry linear module (9) includes a gantry linear module bracket (91), a gantry linear module stepper motor (92), and a connecting plate (93); the gantry linear module bracket (91) includes a lead screw (94) and a positioning bracket; the positioning bracket is fixed on the lead screw (94) through the connecting plate (93); each positioning bracket is provided with a hydrocarbon sensor (51) and a first oxygen sensor (52); one end of each positioning bracket is provided with an ignition electrode (42); the gantry linear module stepper motor (92) is mounted on the lead screw (94).

4. The experimental apparatus for simulating non-uniform rocket kerosene vapor cloud combustion and explosion in an oxygen-rich atmosphere according to claim 1, characterized in that, Multiple temperature feedback thermocouples are fixed at different heights above the oil bath heater (34), at the center of the bottom of the oil bath heater, and on the silicone rubber heating plate (31).

5. A method for simulating the combustion and explosion of a non-uniform rocket kerosene vapor cloud in an oxygen-rich atmosphere, characterized in that, Using the experimental apparatus of claim 1, the method includes the following steps: checking the airtightness, closing the one-way valve (21) switch of the gas supply system, turning on the vacuum pump (63) of the exhaust system, monitoring the value of the pressure transmitter (7) to the preset value, turning off the vacuum pump (63), and turning on the gas supply system and the external oxygen cylinder (23), introducing oxygen of a predetermined concentration into the simulated oxygen-enriched atmosphere tank (1) through air intake purging, ensuring the oxygen atmosphere concentration inside the simulated oxygen-enriched atmosphere tank (1) through the second oxygen sensor (62) in the exhaust pipe, and turning off the external oxygen cylinder (23) after the oxygen concentration and pressure reach the preset values. The oxygen cylinder (23) controls the oil tank heater (34) and the silicone rubber heating plate (31) through the constant temperature controller (32), and monitors the temperature feedback thermocouple to reach the preset value. The changes in the non-uniform concentration field are detected by the hydrocarbon sensor (51) and the first oxygen sensor (52). After determining the equivalence ratio of oxygen and rocket kerosene, the ignition position is determined by the gantry linear module (9). Then, the ignition energy of the ignition electrode (42) is adjusted by the adjustable igniter (41) to conduct the ignition experiment. After the experiment, the external oxygen cylinder is opened for rescanning. The above steps are repeated until the experiment is completed.

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