A method for handling hazardous media

Abstract

This invention relates to the field of rocket engine testing technology and discloses a method for handling hazardous media, comprising: setting a first and a second field torch above the thrust chamber of the rocket engine, and setting a third field torch below the thrust chamber; the first, second, and third field torches are adapted to ignite the hydrogen-oxygen mixture discharged before the pre-combustion chamber ignites; a fourth and a fifth field torch are respectively arranged to the left and right of the thrust chamber of the rocket engine; the fourth and fifth field torches are adapted to ignite the hydrogen-rich gas discharged after the pre-combustion chamber ignites; both the hydrogen-oxygen mixture and the hydrogen-rich gas are hazardous media. This application, by setting five field torches and using field ignition, can promptly ignite the hazardous media discharged from the thrust chamber outlet of the rocket engine, safely handle the hydrogen-oxygen mixture and hydrogen-rich gas, and meet the safety testing requirements of rocket engines.

Description

Technical Field

[0001] This invention relates to the field of rocket engine testing technology, and more specifically to a method for handling hazardous media. Background Technology

[0002] In semi-system testing of rocket engines, the cryogenic hydrogen-oxygen mixture and hydrogen-rich gas discharged from the pre-combustion chamber within the rocket engine's thrust chamber require safe handling. The hydrogen-oxygen mixture discharged from the pre-combustion chamber before ignition and the hydrogen in the hydrogen-rich gas discharged after ignition, when mixed with air, can form a flammable mixture reaching the hydrogen explosion limit. As the discharge gas flow rate gradually increases and the gas temperature rises, the gas in the main stage begins to undergo afterburning, providing sufficient ignition energy. This can easily trigger a detonation of the aforementioned flammable mixture reaching the hydrogen explosion limit, causing significant damage to the test stand and surrounding area. Summary of the Invention

[0003] In view of this, the present invention provides a method for handling hazardous media to address the problem that the hydrogen-oxygen mixture discharged from the pre-combustion chamber of a rocket engine before ignition and the hydrogen in the hydrogen-rich gas discharged from the pre-combustion chamber after ignition, when mixed with air, form a combustible mixture that reaches the hydrogen explosion limit. As the flow rate and temperature of the discharged gas gradually increase, the gas in the main stage process begins to undergo afterburning, thereby providing sufficient ignition energy. This can easily cause the aforementioned combustible mixture that has reached the hydrogen explosion limit to detonate, causing significant damage to the test stand and surrounding areas.

[0004] This invention provides a method for handling hazardous media, comprising:

[0005] A first field torch and a second field torch are installed above the thrust chamber of the rocket engine, and a third field torch is installed below the thrust chamber of the rocket engine; the first field torch, the second field torch and the third field torch are suitable for igniting the hydrogen-oxygen mixture discharged before the pre-combustion chamber is ignited.

[0006] A fourth and a fifth field torch are respectively arranged to the left and right of the rocket engine's thrust chamber. These four and fifth field torches are suitable for igniting the hydrogen-rich gas discharged after the pre-combustion chamber ignites. Both the hydrogen-oxygen mixture and the hydrogen-rich gas are hazardous media. Beneficial effects: This application, by adopting the above technical solution and setting up five field torches, uses field ignition to promptly ignite the hazardous media discharged from the rocket engine's thrust chamber outlet, safely handling the hydrogen-oxygen mixture and hydrogen-rich gas, thus meeting the safety testing requirements of the rocket engine.

[0007] Optionally, the first, second, third, fourth, and fifth field torches are collectively referred to as field torches; the medium of the field torches is hydrogen. Beneficial effects: This application adopts the above technical solution, utilizing the low ignition energy of hydrogen; general ignition methods can meet the ignition energy requirements of hydrogen, facilitating rapid ignition.

[0008] Optionally, the hydrogen supply pressure is 1.5 MPa; the ignition energy source for the field torch is an ignition nozzle.

[0009] Optionally, the jet center point of the field torch is located within 1.2m of the ignition zone of the thrust chamber outlet jet. Beneficial effect: This application employs the above technical solution to ensure that the hydrogen-oxygen mixture or hydrogen-rich gas discharged from the thrust chamber outlet of the rocket engine can be reliably ignited.

[0010] Optionally, the jet center point of the field torch is positioned within a range of 0.48m to 0.86m from the ignition zone of the thrust chamber outlet jet. Beneficial effects: This application, employing the above technical solution, further ensures the reliable ignition of the hydrogen-oxygen mixture or hydrogen-rich gas discharged from the rocket engine's thrust chamber outlet and increases the ignition area.

[0011] Optionally, it also includes:

[0012] Before the rocket engine starts, the first, second, third, fourth and fifth field torches are ignited simultaneously.

[0013] After confirming through temperature feedback indicator lights that the first, second, third, fourth, and fifth field torches have all ignited normally, the rocket engine is then started.

[0014] After the rocket engine shuts down normally, the first, second, third, fourth, and fifth field flares are manually shut down. Beneficial effect: This application employs the above technical solution to ensure that the rocket engine undergoes afterburning immediately after startup, preventing the accumulation of cold hydrogen or hydrogen-rich gas near the thrust chamber outlet.

[0015] Optionally, an annular baffle is provided at the outlet of the thrust chamber; the surface of the baffle is perpendicular to the outlet direction of the thrust chamber; the center of the baffle is located on the central axis of the thrust chamber; the outer radius of the baffle is larger than the outer radius of the thrust chamber; the first jet center point of the first field torch is located at the center of the hydrogen diffusion at the upper edge of the baffle; and the first jet center point of the first field torch is flush with the surface of the baffle.

[0016] The second jet center point of the second field torch is located at the middle of the first jet center point of the first field torch and the upper edge of the fire baffle plate, and the second jet center point of the second field torch is flush with the surface of the fire baffle plate.

[0017] The third jet center point of the third field torch and the second jet center point of the second field torch are symmetrical about the center of the baffle plate. Beneficial effects: This application adopts the above technical solution, by aligning the first jet center point of the first field torch with the surface of the baffle plate, avoiding the influence of diffused hydrogen-oxygen mixture on torch combustion; by setting up the second and third field torches, the field torches can ignite hydrogen gas diffused over a wider area, promptly igniting the newly emerged hydrogen-oxygen mixture, while further increasing ignition reliability.

[0018] Optionally, the jet direction of the first external torch is parallel to the central axis of the thrust chamber; the jet direction of the second external torch forms a 60-degree angle with the central axis of the thrust chamber. Beneficial effects: By adopting the above technical solution, the jet flame of the first external torch, being parallel to the central axis of the thrust chamber, can cover the upwardly diffusing hydrogen-oxygen mixture; and by setting the jet direction of the second external torch at a 60-degree angle with the central axis of the thrust chamber, the flame is prevented from being obstructed by the baffle plate.

[0019] Optionally, the two intersection points of the fourth and fifth field torches, located 1m from the outlet of the thrust chamber nozzle along the central axis of the thrust chamber and the boundary of the combustible zone, are respectively designated as the flame midpoints of the fourth and fifth field torches. The fourth jet center point of the fourth field torch is located 0.6m from the flame midpoint located to the left of the thrust chamber nozzle, extending along a direction at a 30-degree angle to the central axis of the thrust chamber. The fifth jet center point of the fifth field torch is located 0.6m from the flame midpoint located to the right of the thrust chamber nozzle, extending along a direction at a 30-degree angle to the central axis of the thrust chamber.

[0020] Optionally, the angle between the jet direction of the fourth field torch and the central axis of the thrust chamber is 30 degrees; the angle between the jet direction of the fifth field torch and the central axis of the thrust chamber is 30 degrees. Attached Figure Description

[0021] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0022] Figure 1 The static temperature cloud map is used to simulate the combustion process of hydrogen jet in an external torch, as provided in the embodiments of the present invention.

[0023] Figure 2 This is a static temperature cloud map with dimension annotations for areas with temperatures above 847K when simulating the combustion process of hydrogen jet in an external torch, as provided in an embodiment of the present invention.

[0024] Figure 3 This is a cloud map of the molar volume fraction of hydrogen gas at the thrust chamber outlet under steady state during the operation of a simulated rocket engine, provided in an embodiment of the present invention.

[0025] Figure 4 This is a schematic diagram of the molar volume fraction cloud map of hydrogen gas located at the thrust chamber outlet during simulated rocket engine operation, showing the position of the first jet center point of the first field torch and the second jet center point of the second field torch provided in the embodiments of the present invention.

[0026] Figure 5 This is a cloud map showing the volume concentration ratio of hydrogen and oxygen in the simulated pre-combustion chamber 0.75 s after ignition, as provided in this embodiment of the invention.

[0027] Figure 6 This is a cloud map showing the volume concentration ratio of hydrogen and oxygen 2 seconds after the simulated pre-combustion chamber is ignited, as provided in this embodiment of the invention.

[0028] Figure 7 This is a schematic diagram comparing the flammable range boundaries on the hydrogen and oxygen volume concentration ratio cloud map at 0.75s and 2s after the simulated pre-combustion chamber is ignited, as provided in this embodiment of the invention.

[0029] Figure 8 This is a schematic diagram showing the positional distribution of the volume concentration ratio of hydrogen and oxygen on the cloud map of the fourth jet center point of the fourth field torch and the fifth jet center point of the fifth field torch provided in the embodiments of the present invention, 0.75s after the start of ignition in the simulated pre-combustion chamber.

[0030] Explanation of reference numerals in the attached figures:

[0031] 1. Fire baffle; 2. First jet center point; 3. Second jet center point; 4. Fourth jet center point; 5. Fifth jet center point; 6. Thrust chamber nozzle; 7. Combustible range of hydrogen. Detailed Implementation

[0032] 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 with reference to the accompanying drawings. 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.

[0033] like Figures 1 to 8 One specific embodiment of the hazardous media handling method shown includes:

[0034] A first and second field torch are installed above the thrust chamber of the rocket engine, and a third field torch is installed below the thrust chamber. These three field torches are designed to ignite the hydrogen-oxygen mixture discharged before ignition in the pre-combustion chamber. The hydrogen-oxygen mixture is a cryogenic mixture, which can be simply referred to as cold hydrogen. A fourth and fifth field torch are arranged to the left and right of the thrust chamber of the rocket engine, respectively. These torches are designed to ignite the hydrogen-rich gas discharged after ignition in the pre-combustion chamber. Both the hydrogen-oxygen mixture and the hydrogen-rich gas are hazardous media. The hazardous media handling method described in this application aims to promptly ignite hazardous media generated during experiments on a rocket engine test bench, thereby safely handling the hazardous media.

[0035] Specifically, the first, second, third, fourth, and fifth field torches are collectively referred to as field torches; field torches are also known as field ignition torches. The medium of the field torches is hydrogen. The ignition energy of hydrogen is very low, typically 0.02 mJ, so ordinary ignition methods can meet the ignition energy requirements of hydrogen.

[0036] The process of discharging the medium from the rocket engine thrust chamber outlet can be divided into two stages. The first stage involves discharging a cryogenic hydrogen-oxygen mixture before ignition in the rocket engine pre-combustion chamber. The discharge time of the hydrogen-oxygen mixture is 0.35s to 0.57s, totaling 0.22s, with a total discharge of 0.83kg of hydrogen and 0.34kg of oxygen. Analysis of the diffusion flow field and concentration field of the hydrogen-oxygen mixture is required, and an external flare is set up to ignite the mixture. The second stage involves discharging hydrogen-rich gas from the rocket engine thrust chamber after ignition in the pre-combustion chamber. As the rocket engine's operating conditions gradually increase, analysis of the initial and stable operating conditions is required, and an external flare is set up to address potential issues with non-combustion of the hydrogen-rich gas. This application specifically designs targeted solutions for these two stages. In the first stage, the diffusion flow field and concentration field of the discharged medium are analyzed, and an external flare is set up in the vertical direction of the rocket engine to ignite the hydrogen-oxygen mixture. In the second stage, the medium flow field under the start-up and maximum operating conditions of the rocket engine was analyzed. Hydrogen-rich gas was ignited by setting up field torches in the left and right directions of the rocket engine.

[0037] Specifically, the hydrogen supply pressure is 1.5 MPa; hydrogen can be transported using a DN6 pipeline with a length of several tens of meters. The ignition energy for the field flare is an electric ignition nozzle. The electric ignition nozzle has an ignition energy of 12 J and a spark frequency of 14 times / second. During the use of the electric ignition nozzle, the electric spark is energized first, then the hydrogen source supplies hydrogen. The hydrogen and the outside air mix rapidly and are ignited by the electric spark, forming a continuous and stable flame.

[0038] The static temperature cloud map obtained by simulating the hydrogen jet combustion process of the field torch is shown below. Figure 1 As shown. The simulation results are similar to the flame shape of the actual field torch. In the core region of the jet, due to the high hydrogen concentration, it does not mix with oxygen to form a flame; the flame is concentrated in the outer region of the hydrogen jet. The ignition point of hydrogen is 574℃, corresponding to a thermodynamic temperature of 847K. Figure 2 As shown, the area with a temperature above 847K is within 1.2m of the external flare nozzle, with a maximum width of 0.25m, concentrated between 0.48m and 0.86m from the nozzle. To ensure reliable ignition of the cryogenic hydrogen-oxygen mixture or hydrogen-rich gas discharged from the rocket engine's thrust chamber outlet, the jet center point of the external flare is positioned within 1.2m of the ignition zone of the thrust chamber outlet jet. The jet center point is the location of the external flare nozzle.

[0039] Preferably, to increase the ignition area, the jet center point of the field torch is positioned within a range of 0.48m to 0.86m from the ignition zone of the thrust chamber outlet jet. Before the rocket engine test, the field torch will be tested to ensure that the flame length meets the requirements.

[0040] Based on previous test data, the field flares ignite approximately 1-2 seconds after receiving the ignition command. To ensure that the rocket engine performs afterburning immediately after startup and to prevent the accumulation of cold hydrogen or hydrogen-rich gas near the thrust chamber outlet, the hazardous medium handling method described in this application further includes: simultaneously igniting the first, second, third, fourth, and fifth field flares before starting the rocket engine. After confirming through temperature feedback indicator lights that all five field flares have ignited normally, the rocket engine is then started. After the rocket engine shuts down normally, the first, second, third, fourth, and fifth field flares are manually shut down.

[0041] To accurately locate the field flare position, the following basic principles must be followed when placing the field flare: First, the flame area of ​​the field flare must be able to cover the hydrogen-oxygen mixture discharged from the rocket engine thrust chamber within the combustible concentration range; second, the airflow velocity in the ignition area should not be too high; third, the larger the flame coverage area and the higher the ignition temperature, the better; fourth, the field flare must not be affected by the jet from the thrust chamber, because the field flare only sprays hydrogen and requires oxygen to maintain stable ignition; fifth, the placement of the field flare must not interfere with the structure of the rocket engine.

[0042] Before ignition in the pre-combustion chamber, the flow field of the hydrogen-oxygen mixture was analyzed, combined with the rocket engine's startup process and simulation results. The analysis revealed that before ignition in the pre-combustion chamber, the discharged hydrogen-oxygen mixture, due to an unsuitable mixing ratio, did not burn within the chamber and was not ignited by the igniter. After being discharged from the rocket engine's thrust chamber, the hydrogen-oxygen mixture mixed with external air in its edge region, forming a combustible hydrogen-oxygen mixture. An external torch on the rocket engine test rig promptly ignited this mixture. The rocket engine model was constructed using a rotational axisymmetric method, with the inlet condition being a mass flow rate inlet and the outlet condition being a pressure outlet. Figure 3 The results are steady-state simulations of hydrogen discharged from the upper part of the thrust chamber nozzle 6, i.e., the results after an infinitely long period of stabilization. They do not represent the actual diffusion area at the thrust chamber outlet. However, the diffusion trend can be seen from the steady-state simulation results. The cryogenic hydrogen-oxygen mixture will diffuse upwards in the thrust chamber after being discharged. Therefore, it is necessary to add an external torch above the thrust chamber to ignite the upward-diffusing hydrogen-oxygen mixture in a timely manner.

[0043] Specifically, a circular fire baffle 1 is provided at the outlet of the thrust chamber. The surface of the fire baffle 1 is perpendicular to the outlet direction of the thrust chamber; the center of the fire baffle 1 is located on the central axis of the thrust chamber; the outer radius of the fire baffle 1 is larger than the outer radius of the thrust chamber. The inner diameter of the rocket engine thrust chamber outlet is 0.7m, the outer diameter of the thrust chamber outlet is 0.8m, the outer diameter of the fire baffle 1 is 2.2m, and the outer radius of the fire baffle 1 is an extension of 0.7m from the outer radius of the thrust chamber (0.4m).

[0044] like Figure 3 and Figure 4 As shown, the axial direction of the thrust chamber is defined as the y-axis, and the direction perpendicular to the y-axis on the plane perpendicular to the baffle plate 1 is defined as the x-axis. The molar volume fraction cloud diagram of hydrogen in steady state is adjusted to a 45-degree oblique angle view, with the thrust chamber outlet section as the reference plane, and the diffused hydrogen along the x-axis direction is 0.6m above the upper edge of the baffle plate. As the jet from the thrust chamber diffuses, the hydrogen gradually diffuses. Since this is a steady-state simulation, Figure 4 This can be considered the final result of diffusion; in practice, the field torch can be ignited before the hydrogen diffuses, rather than waiting until it diffuses to the desired point. Figure 4 The result will be determined later. The length of the flame area above 874K in the field torch is 1.2m, and the width is 0.25m. The edge of the baffle plate 1 is 0.7m away from the edge of the thrust chamber along the x-axis, and the distance of the diffused hydrogen along the x-axis at the upper edge of the baffle plate 1 is 0.6m. In order to enable the field torch to ignite a larger area of ​​diffused hydrogen, the first jet center point 2 of the first field torch can be located at the center of the diffused hydrogen at the upper edge of the baffle plate 1; that is, at a distance of 0.3m from the upper edge of the baffle plate 1 along the x-axis. In the y-axis direction, the first jet center point 2 of the first field torch is flush with the surface of the baffle plate 1, and the jet flame length of the first field torch is 1.2m. Figure 4 As shown, the jet direction of the first external flare is parallel to the central axis of the thrust chamber, and the jet flame can basically cover the range of hydrogen concentration diffusing upwards. The first jet center point 2 of the first external flare is flush with the baffle plate 1, which can prevent the diffusing hydrogen-oxygen mixture from affecting the flare combustion.

[0045] As the hydrogen-oxygen mixture gradually diffuses out of the thrust chamber outlet, to promptly ignite the newly emerged mixture and further increase ignition reliability, two additional field torches are added above and below the thrust chamber: a second field torch and a third field torch. These two torches are symmetrical, with the jet flame directed towards the hydrogen-oxygen mixture at the thrust chamber outlet. Calculations show that the jet direction of the second field torch forms a 60-degree angle with the central axis of the thrust chamber, preventing the flame from being obstructed by the baffle plate 1. Figure 4As shown, the second jet center point 3 of the second field torch is located 0.15m away from the edge of the fire baffle 1 along the x-axis. In the y-axis direction, the second jet center point 3 is flush with the fire baffle 1. That is, the second jet center point 3 of the second field torch is located midway between the first jet center point 2 of the first field torch and the upper edge of the fire baffle 1, and the second jet center point 3 of the second field torch is flush with the surface of the fire baffle 1. The third jet center point of the third field torch is symmetrical to the second jet center point 3 of the second field torch about the center of the fire baffle 1. Therefore, the coordinates of the three torches can be determined. The 1.2m flame length of the field torch forms a "penetrating" ignition for the low-temperature hydrogen-oxygen mixture, covering all combustible areas.

[0046] The flow field after ignition in the pre-combustion chamber was analyzed. After ignition in the rocket engine's pre-combustion chamber, the operating conditions rapidly increase, and the rocket engine's thrust chamber begins to discharge hydrogen-rich gas. The analysis first focuses on the operating condition at 0.75 seconds immediately after pre-combustion chamber ignition, when the rocket engine's operating conditions are just beginning to increase. At 2 seconds after main stage ignition, the rocket engine's operating conditions reach their maximum. Combustion is possible when the hydrogen to oxygen volume concentration ratio is between 4% and 94%. The simulated hydrogen to oxygen volume concentration ratio contour plot at 0.75 seconds after pre-combustion chamber ignition is shown below. Figure 5 As shown in the figure; the volume concentration ratio of hydrogen and oxygen 2 seconds after ignition in the simulated pre-combustion chamber is shown in the cloud map. Figure 6 As shown. By Figure 5 and Figure 6 As can be seen, the overall diffusion trend of the hydrogen jet in the thrust chamber is a conical diffusion. For ease of comparison, as shown... Figure 7 As shown, the positions of the outer isosurfaces of the hydrogen and oxygen volume concentration ratio at 0.75s and 2s of the main stage are basically the same, both being inclined planes with an expansion half-angle of 16.2 degrees.

[0047] Since the outer isosurfaces of the hydrogen and oxygen volume concentration ratio at 0.75s and 2s are basically at the same position, these isosurfaces can reflect the flammability range of hydrogen. Therefore, the flammability range of hydrogen at 0.75s can be used for analysis, such as... Figure 8 As shown, the relative concentration of hydrogen is relatively high within a 2m radius of the thrust chamber outlet axis. Therefore, the ignition point can be chosen in the middle, specifically 1m from the thrust chamber outlet along the central axis of the thrust chamber. The flame length of the field torch is 1.2m, with the widest area concentrated within a 0.48m to 0.86m radius of the nozzle. The temperature is also high, far exceeding the ignition point of hydrogen (574℃), corresponding to a thermodynamic temperature of 847K. Therefore, a point 0.6m long, at the intersection of the flame length and the boundary of the hydrogen flammable zone 7, can be chosen. Figure 8As shown. The boundary of the flammable range 7 of hydrogen can be used as the flammable range boundary. Referring to the experience of torch arrangement angles on rocket engine test rigs, the angle between the torch jet and the central axis of the thrust chamber is set at 30 degrees, which can determine the three-dimensional coordinates of the field torch arrangement. Referring to the number of field torches arranged on rocket engine test rigs, one field torch is arranged on each of the left and right sides of the thrust chamber. Figure 8 The circle in the diagram represents the torch injection point, and the arrow indicates the direction and length of the torch flame. The torch injection point is the center point of the jet.

[0048] In short, such as Figure 8 As shown, the two intersection points of the fourth and fifth field torches, located 1m from the outlet of the thrust chamber nozzle 6 along the central axis of the thrust chamber and at the boundary of the combustible zone, are respectively designated as the flame midpoints of the fourth and fifth field torches. The fourth jet center point 4 of the fourth field torch is located 0.6m extending from the flame midpoint to the left of the thrust chamber nozzle 6 at a 30-degree angle to the central axis of the thrust chamber. The fifth jet center point 5 of the fifth field torch is located 0.6m extending from the flame midpoint to the right of the thrust chamber nozzle 6 at a 30-degree angle to the central axis of the thrust chamber. The jet direction of the fourth field torch forms a 30-degree angle with the central axis of the thrust chamber; the jet direction of the fifth field torch also forms a 30-degree angle with the central axis of the thrust chamber.

[0049] Although embodiments of the invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the invention, and such modifications and variations all fall within the scope defined by this application.

Claims

1. A method for handling hazardous media, characterized in that, include: A first field torch and a second field torch are installed above the thrust chamber of the rocket engine, and a third field torch is installed below the thrust chamber of the rocket engine; the first field torch, the second field torch and the third field torch are suitable for igniting the hydrogen-oxygen mixture discharged before the pre-combustion chamber is ignited. A fourth field torch and a fifth field torch are respectively arranged to the left and right of the thrust chamber of the rocket engine; the fourth field torch and the fifth field torch are suitable for igniting the hydrogen-rich gas discharged after the pre-combustion chamber is ignited; the hydrogen-oxygen mixture and the hydrogen-rich gas are both hazardous media. The jet center point of the field torch is located within 1.2m of the ignition zone of the jet exiting the thrust chamber; Based on previous test data, the field torch ignites after a 1-2 second delay following the ignition command. To ensure that the rocket engine performs afterburning immediately after startup and to prevent the accumulation of cold hydrogen or hydrogen-rich gas near the thrust chamber outlet, the hazardous medium handling method also includes: Before the rocket engine starts, the first, second, third, fourth and fifth field torches are ignited simultaneously. After confirming through temperature feedback indicator lights that the first, second, third, fourth, and fifth field torches have all ignited normally, the rocket engine is then started. After the rocket engine shuts down normally, manually shut down the first, second, third, fourth, and fifth field torches.

2. The hazardous medium handling method according to claim 1, characterized in that, The first, second, third, fourth, and fifth field torches are collectively referred to as field torches; the medium of the field torches is hydrogen gas.

3. The hazardous medium handling method according to claim 2, characterized in that, The hydrogen supply pressure is 1.5 MPa; the ignition energy source for the field torch is an ignition nozzle.

4. The hazardous medium handling method according to claim 1, characterized in that, The jet center point of the field torch is located within a range of 0.48m to 0.86m from the ignition zone of the jet exiting the thrust chamber.

5. The method for handling hazardous media according to any one of claims 1-4, characterized in that, A circular baffle plate (1) is provided at the outlet of the thrust chamber; the surface of the baffle plate (1) is perpendicular to the outlet direction of the thrust chamber; the center of the baffle plate (1) is located on the central axis of the thrust chamber; the outer radius of the baffle plate (1) is greater than the outer radius of the thrust chamber; the first jet center point (2) of the first field torch is located at the center of the hydrogen diffusion on the upper edge of the baffle plate (1); and the first jet center point (2) of the first field torch is flush with the surface of the baffle plate (1). The second jet center point (3) of the second field torch is located at the middle of the first jet center point (2) of the first field torch and the upper edge of the fire baffle (1), and the second jet center point (3) of the second field torch is flush with the surface of the fire baffle (1). The third jet center point of the third field torch and the second jet center point (3) of the second field torch are symmetrical about the center of the fire baffle (1).

6. The method for handling hazardous media according to claim 5, characterized in that, The jet direction of the first field torch is parallel to the central axis of the thrust chamber; the jet direction of the second field torch makes an angle of 60 degrees with the central axis of the thrust chamber.

7. The method for handling hazardous media according to any one of claims 1-4, characterized in that, The two intersections of the position 1m away from the outlet of the thrust chamber nozzle (6) along the central axis of the thrust chamber and the boundary of the combustible range are respectively designated as the flame midpoints of the fourth and fifth field torches; the position extending 0.6m from the flame midpoint located to the left of the thrust chamber nozzle (6) along a direction at a 30-degree angle to the central axis of the thrust chamber is designated as the fourth jet center point (4) of the fourth field torch; the position extending 0.6m from the flame midpoint located to the right of the thrust chamber nozzle (6) along a direction at a 30-degree angle to the central axis of the thrust chamber is designated as the fifth jet center point (5) of the fifth field torch.

8. The method for handling hazardous media according to claim 7, characterized in that, The angle between the jet direction of the fourth field torch and the central axis of the thrust chamber is 30 degrees; the angle between the jet direction of the fifth field torch and the central axis of the thrust chamber is 30 degrees.

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