A constant volume bomb experimental device suitable for liquid propellant ignition

Abstract

The application discloses a constant-volume bomb experimental device suitable for liquid propellant ignition, and can realize switching of a constant-volume experimental system for a counterflow combustion experiment of a self-igniting propellant and a constant-volume bomb experimental system for a combustion experiment of a non-self-igniting propellant. The device comprises a combustion chamber, an ignition system, a triggering system, a gas mixing tank, an exhaust system and an information acquisition system. When the device is used as the constant-volume experimental system for the counterflow combustion experiment of the self-igniting propellant, the ignition system is not needed, and a sampling system is added. The ignition electrode of the ignition system is replaced by a counterflow pipeline through a detachable mechanism, and the gas mixing tank is replaced by an ambient gas tank, so that the two systems can be quickly switched. The application effectively solves the problems of difficult switching and high cost of the existing experimental system.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of ignition system, in particular to a constant volume bomb experimental device suitable for liquid propellant ignition, which is suitable for calculating the collision ignition delay of self-igniting propellant and can also be used for calculating the laminar flame propagation speed of conventional non-self-igniting propellant. BACKGROUND

[0002] With the continuous deepening of human space exploration and the rapid development of space technology at home and abroad, the power systems such as launch vehicles, space vehicles and attitude control engines have also developed rapidly. Propellant is not only the power source of power systems such as launch vehicles, space vehicles and attitude control engines, but also a comprehensive embodiment of a country's advanced space technology and national defense strength. At present, for space propulsion devices, the jet fuel used must adapt to its related structure, so it is particularly important to master the combustion kinetics model of propellant fuel in detail, and the ignition delay and laminar flame propagation speed are the key indicators for verifying the combustion kinetics model.

[0003] At present, the ignition experiment of traditional propellant generally needs to be premixed with the oxidizer for a period of time before the experiment, but due to the high activity of self-igniting propellant, it is easy to react. If the traditional method of premixing is still used, accidents such as explosion and fire may occur, which will cause great harm to experimental equipment and experimental personnel, so it is often impossible to conduct controllable ignition experiments on self-igniting propellant.

[0004] For the ignition experiment of self-igniting propellant, the experimental device invented by scholars such as Wu Yingtao and Kong Xiangdong divides the compression cylinder into two chambers with an aluminum film, and the gas in the chamber is heated and pressurized by the compression of the piston to break the aluminum film and complete the ignition. It is only suitable for self-igniting propellant with ignition delay time of 101-102ms, and the scope of application is limited. SUMMARY

[0005] The purpose of the present application is to provide a constant volume bomb experimental device suitable for liquid propellant ignition, to solve the safety problems existing in the current ignition delay experiment system for self-igniting propellant, and the problem that the device cannot be used for both self-igniting and non-self-igniting propellants.

[0006] In order to achieve the above-mentioned task, the present application adopts the following technical scheme:

[0007] A constant volume bomb experimental device suitable for liquid propellant ignition can realize the switching of the constant volume experimental system for self-igniting propellant collision combustion experiment and the constant volume bomb experimental system for non-self-igniting propellant combustion experiment;

[0008] When the device is used as a constant volume bomb experimental system for non-self-igniting propellant combustion experiment, it comprises:

[0009] combustion chamber; the upper and lower ends of the combustion chamber are provided with transparent view windows;

[0010] ignition system; the ignition system comprises an ignition electrode which is detachably arranged on the inner wall of the combustion chamber;

[0011] triggering system; the triggering system comprises a synchronous triggering box, and the ignition electrode is controlled by the synchronous triggering box;

[0012] gas mixing tank; the gas mixing tank stores premixed gas, and is used for charging the premixed gas into the combustion chamber through a stainless steel pipeline;

[0013] exhaust system; the exhaust system comprises a vacuum gauge and a pressure gauge, and a vacuum pump, wherein the vacuum pump is connected to the combustion chamber through an exhaust pipe, is used for vacuumizing the combustion chamber, and a valve is arranged on the exhaust pipe; the vacuum gauge and the pressure gauge are arranged on the combustion chamber, and are used for monitoring the pressure in the combustion chamber in real time;

[0014] information acquisition system; the information acquisition system comprises a schlieren light source, a plane mirror, a mercury mirror, a high-speed camera, an amplifier and a collection card, and an electronic computer;

[0015] the schlieren light source, the plane mirror and the mercury mirror cooperate with the view windows on the combustion chamber to form an optical path for acquiring the combustion condition in the combustion chamber, the combustion image is acquired by the high-speed camera and is sent to the electronic computer for analysis and processing; the amplifier and the collection card are used for collecting and amplifying the pressure signal detected by the pressure sensor arranged in the combustion chamber and then uploading the signal to the electronic computer;

[0016] when the device is used as a constant-volume experimental system for self-ignition type propellant counter-jet combustion experiment, the ignition system is removed and a sampling system is added on the basis of the above structure;

[0017] the sampling system comprises a fuel gas tank, an oxidant gas tank, an environmental gas tank and a counter-jet pipeline; a pair of the counter-jet pipelines are detachably and symmetrically arranged on the inner wall of the combustion chamber, the fuel gas tank and the oxidant gas tank are connected to the counter-jet pipelines through pipelines, electromagnetic valves and flow meters are arranged on the pipelines, and the electromagnetic valves are controlled by the synchronous triggering box; when the electromagnetic valves are controlled to be opened by the synchronous triggering box, the fuel in the fuel gas tank and the oxidant in the oxidant gas tank are combusted in the combustion chamber through the counter-jet pipelines, at this time, the gas mixing tank is replaced by the environmental gas tank to provide environmental gas into the combustion chamber, so that the combustion chamber simulates a real combustion environment.

[0018] further, the combustion chamber is a constant-volume bomb with a hollow cylinder structure with open ends, and quartz glass windows are arranged on the open ends as view windows, wherein the view windows are used for cooperating with an optical system to acquire data during the experiment.

[0019] Further, when the high-speed camera in the optical system starts shooting, a trigger signal is generated and sent to the synchronization trigger box, which controls the ignition electrode to start at the same time, generating an electric spark to complete ignition, or:

[0020] The synchronization trigger box controls the electromagnetic valves on the pipelines of the fuel gas tank and the oxidant gas tank to open at the same time, and synchronously sprays the opposite nozzles in the combustion chamber.

[0021] Further, the mercury mirror includes a first mercury mirror and a second mercury mirror, and the plane mirror includes a first plane mirror and a second plane mirror; the first mercury mirror is placed above the upper window of the combustion chamber, and the second mercury mirror is placed below the lower window of the combustion chamber, and the distance between the second mercury mirror and the combustion chamber is greater than that between the first mercury mirror and the combustion chamber; the first plane mirror and the schlieren light source are respectively located obliquely above and laterally below the lower mercury mirror; the light generated by the schlieren light source is reflected by the first plane mirror and the second mercury mirror, then enters the combustion chamber through the lower window of the combustion chamber, and is emitted to the first mercury mirror through the upper window of the combustion chamber, and then is reflected by the second plane mirror to the viewfinder of the high-speed camera, so that the high-speed camera can shoot the combustion process in the combustion chamber; in the experiment, the high-speed camera shoots the combustion process and uploads it to the computer for analysis of the flame propagation characteristics.

[0022] Further, the opposite nozzles in the combustion chamber are arranged on the same straight line along the radial direction of the combustion chamber, and the outlet ends of the opposite nozzles are ensured to be within the visible range of the window of the combustion chamber.

[0023] Further, the gas mixing tank is connected with the stainless steel pipeline through a connecting flange; when the system is switched, the gas mixing tank can be removed from the connecting flange, and an ambient gas tank can be installed.

[0024] Further, a pair of mounting interfaces are symmetrically arranged on the side wall of the combustion chamber, and a replaceable flange is detachably arranged on the mounting interface; the ignition electrode of the ignition system is mounted on the combustion chamber through the replaceable flange; correspondingly, a pair of opposite nozzles in the sample injection system are also mounted on the combustion chamber through the replaceable flange.

[0025] Further, when the device is used as a constant volume bomb experimental system for non-self-igniting propellant combustion experiments, the experimental process includes:

[0026] Step 1, open the vacuum pump to start pumping, and after the pressure display shows a negative value, close the valve and then close the vacuum pump to ensure the vacuum condition in the combustion chamber and the pipeline;

[0027] Step 2, introduce premixed gas from the gas mixing tank, and detect the pressure in the combustion chamber through the pressure sensor to make it reach the preset experimental value;

[0028] Step 3, after debugging the light path, open the high-speed camera to prepare for recording; through the use of a synchronous trigger box to discharge the ignition electrode, ignite the internal premixed gas;

[0029] Step 4, analyze and research the pressure change data collected by the pressure sensor and the combustion process images collected by the information acquisition system to obtain experimental results.

[0030] Further, when the device is used as a constant volume experiment system for the self-ignition type propellant pair jet combustion experiment, the experimental process comprises:

[0031] Step 1, open the vacuum pump to start pumping, and after the pressure display shows a negative value, first close the valve and then close the vacuum pump to ensure the vacuum condition in the combustion chamber and the pipeline;

[0032] Step 2, under the condition that the information acquisition system is debugged, open the high-speed camera 2 to prepare for recording; use the synchronous trigger box to open the electromagnetic valve connected with the fuel gas tank and the oxidant gas tank, observe and record the flowmeter data, and close the electromagnetic valve in time after the combustion is completed to prevent backfire;

[0033] Step 3, analyze and research the pressure change data collected by the pressure sensor and the combustion process images collected by the information acquisition system to obtain experimental results.

[0034] Compared with the prior art, the present application has the following technical features:

[0035] The constant volume bomb experiment device for liquid propellant ignition of the present application can be simultaneously applied to the constant volume bomb experiment system for self-ignition type and non-self-ignition type propellant combustion experiments, and the two different types of experiments of self-ignition type and non-self-ignition type propellant are concentrated in one set of experimental device, and the switching mode is convenient and fast; the cost required by the experiment can be greatly reduced, and for the self-ignition type propellant, it is safer and can make further research on the ignition delay, combustion characteristics and the like, and the reaction mechanism can be further understood. BRIEF DESCRIPTION OF DRAWINGS

[0036] Figure 1 It is a device structure diagram for non-self-ignition type propellant ignition;

[0037] Figure 2 It is a device structure diagram for self-ignition type propellant pair jet ignition.

[0038] Label explanation in the figure: 1 electronic computer, 2 high-speed camera, 3 amplifier and acquisition card, 4 synchronous trigger box, 5 mercury mirror, 6 plane mirror, 7 schlieren instrument light source, 8 combustion chamber, 9 vacuum gauge and pressure gauge, 10 gas mixing tank, 11 vacuum pump, 12 fuel gas tank, 13 environment gas tank, 14 oxidant gas tank, 15 pair jet pipeline. DETAILED DESCRIPTION

[0039] Referring to the drawings, the present application provides a constant volume bomb experimental device suitable for liquid propellant ignition, which can realize switching between a constant volume experimental system for self-combustion propellant jet combustion experiment and a constant volume bomb experimental system for non-self-combustion propellant combustion experiment.

[0040] When the device is used as the constant volume bomb experimental system for non-self-combustion propellant combustion experiment, it comprises:

[0041] A combustion chamber 8; the combustion chamber 8 is a constant volume bomb with a hollow cylinder structure with open ends, and the open end is provided with a quartz glass window as a viewing window, wherein the viewing window is used for data acquisition in cooperation with an optical system during the experiment.

[0042] An ignition system; the ignition system comprises an ignition electrode which is detachably arranged on the inner wall of the combustion chamber 8.

[0043] A triggering system; the triggering system comprises a synchronous triggering box 4, and the ignition electrode is controlled by the synchronous triggering box 4; a triggering signal is generated when a high-speed camera 2 in the optical system starts shooting and is sent to the synchronous triggering box 4, and the synchronous triggering box 4 controls the ignition electrode to start at the same time to generate an electric spark to complete ignition.

[0044] A gas mixing tank 10; the gas mixing tank 10 is connected to the combustion chamber 8 through a stainless steel pipeline, and the gas mixing tank 10 stores premixed gas, which is used to fill the premixed gas into the combustion chamber 8 through the stainless steel pipeline.

[0045] An exhaust system; the exhaust system comprises a vacuum gauge and pressure gauge 9 and a vacuum pump 11, wherein the vacuum pump 11 is connected to the combustion chamber 8 through an exhaust pipe, and is used to extract the combustion chamber 8 to a vacuum state, and a valve is installed on the exhaust pipe; the vacuum gauge and pressure gauge 9 are installed on the combustion chamber 8, and are used to monitor the pressure in the combustion chamber 8 in real time; and the vacuum pump 11 can also clean the gas generated by combustion in time after a single experiment.

[0046] The information acquisition system comprises a schlieren instrument light source 7, a plane mirror 6, a mercury mirror 5, a high-speed camera 2, an amplifier and an acquisition card 3, and an electronic computer 1. The mercury mirror 5 comprises a first mercury mirror and a second mercury mirror, and the plane mirror 6 comprises a first plane mirror and a second plane mirror. The first mercury mirror is arranged above an upper window of the combustion chamber 8, and the second mercury mirror is arranged below a lower window of the combustion chamber 8. The distance between the second mercury mirror and the combustion chamber 8 is greater than that between the first mercury mirror and the combustion chamber 8. The first plane mirror and the schlieren instrument light source 7 are arranged obliquely above and laterally below the lower mercury mirror 5 respectively. The light generated by the schlieren instrument light source 7 is reflected by the first plane mirror and the second mercury mirror, enters the combustion chamber 8 through the lower window of the combustion chamber 8, and then is emitted to the first mercury mirror through the upper window of the combustion chamber 8. Then, the light is reflected by the second plane mirror and enters the viewfinder of the high-speed camera 2, so that the high-speed camera 2 can capture the combustion process in the combustion chamber 8. The positions and angles of the plane mirror 6 and the mercury mirror 5 are adjusted to make the light path reasonable and the view clear. In the experiment, the combustion process is captured by the high-speed camera 2 and uploaded to the electronic computer 1 for analysis of the flame propagation characteristics. A pressure sensor is arranged in the combustion chamber 8 to detect the pressure change. The collected pressure signals are collected by the amplifier and the acquisition card 3 and then uploaded to the electronic computer 1, from which the effective experimental data are extracted.

[0047] When the device is used as a constant-volume experimental system for the opposed jet combustion experiment of the self-ignition type propellant, the ignition system is removed and a sampling system is added on the basis of the above structure.

[0048] The sampling system comprises a fuel gas tank 12, an oxidant gas tank 14, an environmental gas tank 13 and an opposed jet pipeline 15. The opposed jet pipeline 15 is symmetrically arranged on the inner wall of the combustion chamber 8 and has a detachable structure. The fuel gas tank 12 and the oxidant gas tank 14 are connected to the opposed jet pipeline 15 through pipelines, respectively. Electromagnetic valves and flow meters are installed on the pipelines, and the electromagnetic valves are controlled by the synchronous trigger box 4. When the synchronous trigger box 5 controls the electromagnetic valves to be opened, the fuel in the fuel gas tank 12 and the oxidant in the oxidant gas tank 14 are combusted in the combustion chamber 8 through the opposed jet pipeline 15. At this time, the mixing gas tank 10 is replaced by the environmental gas tank 13 to provide environmental gas to the combustion chamber 8, so that the combustion chamber simulates the real combustion environment.

[0049] It should be noted that the opposed jet pipeline 15 should be arranged on the same straight line along the radial direction of the combustion chamber 8, and the outlet end of the opposed jet pipeline 15 should be within the visible range of the window of the combustion chamber 8.

[0050] Preferably, the mixing gas tank 10 is connected to the stainless steel pipeline through a connecting flange. When the system is switched, the mixing gas tank 10 can be removed from the connecting flange, and the environmental gas tank 13 is installed.

[0051] Preferably, a pair of mounting interfaces are symmetrically arranged on the side wall of the combustion chamber 8, and a replacement flange is detachably arranged on the mounting interface, and the ignition electrode of the ignition system is mounted on the combustion chamber 8 through the replacement flange; correspondingly, a pair of the opposite jet pipes 15 in the sample feeding system are also mounted on the combustion chamber 8 through the replacement flange; thus, when the constant volume bomb experimental system of the non-self-ignition propellant combustion experiment is switched to the constant volume experimental system of the self-ignition propellant opposite jet combustion experiment, only the ignition electrode needs to be replaced into the opposite jet pipe 15 through the replacement flange, and the gas mixing tank 10 needs to be replaced into the environment gas tank 13 through the connecting flange.

[0052] Based on the above device, when the device is used as the constant volume bomb experimental system of the non-self-ignition propellant combustion experiment, the experimental process comprises the following steps:

[0053] Step 1, open the vacuum pump 11 to start pumping, and then close the valve and the vacuum pump 11 after the pressure display value is negative, so as to ensure the vacuum condition in the combustion chamber 8 and the pipeline;

[0054] Step 2, the premixed gas is introduced from the gas mixing tank 10, and the internal pressure of the combustion chamber 8 is detected by the pressure sensor to reach the preset value of the experiment;

[0055] Step 3, after adjusting the light path, the high-speed camera 2 is started to prepare for recording; the ignition electrode is discharged by using the synchronous trigger box 4 to ignite the internal premixed gas;

[0056] Step 4, the pressure change data collected by the pressure sensor and the combustion process images collected by the information acquisition system are analyzed and researched to obtain experimental results such as ignition delay time and laminar flame propagation speed.

[0057] When the device is used as the constant volume experimental system of the self-ignition propellant opposite jet combustion experiment, the experimental process comprises the following steps:

[0058] Step 1, open the vacuum pump 11 to start pumping, and then close the valve and the vacuum pump 11 after the pressure display value is negative, so as to ensure the vacuum condition in the combustion chamber 8 and the pipeline;

[0059] Step 2, after adjusting the information acquisition system, the high-speed camera 2 is started to prepare for recording; the electromagnetic valve connecting the fuel gas tank 12 and the oxidant gas tank 14 is opened by using the synchronous trigger box 4, the flowmeter data is observed and recorded, and the electromagnetic valve is closed in time after the combustion is completed to prevent backfire;

[0060] Step 3, the pressure change data collected by the pressure sensor and the combustion process images collected by the information acquisition system are analyzed and researched to obtain experimental results such as ignition delay time, flame propagation speed and the like.

[0061] The device expands the experimental range of the self-ignition propellant, and uses a constant volume bomb as the main body, which is more universal in device processing; and on this basis, the device uses replaceable flange interfaces, which can replace the impinging port for self-ignition propellant with an ignition electrode, not only can equip the stainless steel feed pipe required for self-ignition propellant impinging ignition, but also can replace the ignition electrode required for non-self-ignition propellant ignition, so as to obtain the laminar flame propagation speed of non-self-ignition propellant, and successfully expand the experimental range to almost all gas propellants, and use the constant volume bomb as the main body, which has universality in device processing.

[0062] The above examples are only used to illustrate the technical solutions of the present application, but not to limit them; although the present application has been described in detail with reference to the foregoing examples, those skilled in the art should understand that the technical solutions recorded in the foregoing examples can still be modified, or some technical features can be replaced by equivalents; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present application, and should be included in the protection scope of the present application.

Claims

1. A constant volume bomb experimental device universally applicable to liquid propellant ignition, characterized in that, The device can realize the switching of a constant volume bomb experimental system for the combustion experiment of self-ignition propellant and a constant volume bomb experimental system for the combustion experiment of non-self-ignition propellant; When the device is used as the constant volume bomb experimental system for the combustion experiment of non-self-ignition propellant, the device comprises: a combustion chamber (8); the upper and lower ends of the combustion chamber (8) are provided with transparent view windows; an ignition system; the ignition system comprises an ignition electrode which is detachably arranged on the inner wall of the combustion chamber (8); a triggering system; the triggering system comprises a synchronous triggering box (4), and the ignition electrode is controlled by the synchronous triggering box (4); a gas mixing tank (10); the gas mixing tank (10) stores premixed gas, and the premixed gas is filled into the combustion chamber (8) through a stainless steel pipeline; an exhaust system; the exhaust system comprises a vacuum gauge and a pressure gauge (9) and a vacuum pump (11), wherein the vacuum pump (11) is connected with the combustion chamber (8) through an exhaust pipe, is used for vacuumizing the combustion chamber (8), and a valve is arranged on the exhaust pipe; the vacuum gauge and the pressure gauge (9) are arranged on the combustion chamber (8) and are used for monitoring the pressure in the combustion chamber (8) in real time; an information acquisition system; the information acquisition system comprises a schlieren instrument light source (7), a plane mirror (6), a mercury mirror (5), a high-speed camera (2), an amplifier and an acquisition card (3), and an electronic computer (1); the schlieren instrument light source (7), the plane mirror (6) and the mercury mirror (5) cooperate with the view windows on the combustion chamber (8) to form an optical path for collecting the combustion condition in the combustion chamber (8), the combustion image is collected by the high-speed camera (2) and is sent to the electronic computer (1) for analysis and processing; the amplifier and the acquisition card (3) are used for collecting and amplifying the pressure signal detected by the pressure sensor arranged in the combustion chamber (8) and then uploading the signal to the electronic computer (1); when the device is used as the constant volume experimental system for the combustion experiment of self-ignition propellant, the ignition system is removed and a sampling system is added on the basis of the above structure; the sampling system comprises a fuel gas tank (12), an oxidant gas tank (14), an environmental gas tank (13) and a pair of counter-jet pipelines (15); the pair of counter-jet pipelines (15) are detachably and symmetrically arranged on the inner wall of the combustion chamber (8), the fuel gas tank (12) and the oxidant gas tank (14) are connected with the counter-jet pipelines (15) through pipelines, electromagnetic valves and flow meters are arranged on the pipelines, and the electromagnetic valves are controlled by the synchronous triggering box (4); when the synchronous triggering box (4) controls the electromagnetic valves to be opened, the fuel in the fuel gas tank (12) and the oxidant in the oxidant gas tank (14) are combusted in the combustion chamber (8) through the counter-jet pipelines (15), at this time, the gas mixing tank (10) is replaced by the environmental gas tank (13) to provide environmental gas into the combustion chamber (8) so that the combustion chamber simulates a real combustion environment.

2. The constant volume bomb experimental device universally applicable to ignition of liquid propellants according to claim 1, characterized in that, The combustion chamber (8) is a constant volume bomb with a hollow cylinder structure and open at both ends, and quartz glass windows are arranged on the open portions as view windows, wherein the view windows are used for cooperating with an optical system to collect data in the experiment.

3. The constant volume bomb test apparatus universally applicable for liquid propellant ignition according to claim 1, wherein, When the high-speed camera (2) in the optical system starts shooting, a trigger signal is generated and sent to the synchronous trigger box (4), which controls the ignition electrodes to start at the same time, generating an electric spark to complete ignition, or: The synchronous trigger box (4) controls the electromagnetic valves on the pipelines of the fuel gas tank (12) and the oxidant gas tank (14) to open at the same time, and synchronously sprays the opposite nozzles (15) in the combustion chamber (8).

4. The constant volume bomb test apparatus universally applicable for liquid propellant ignition according to claim 1, wherein, The mercury mirror (5) includes a first mercury mirror and a second mercury mirror, and the plane mirror (6) includes a first plane mirror and a second plane mirror; the first mercury mirror is arranged above the upper window of the combustion chamber (8), and the second mercury mirror is arranged below the lower window of the combustion chamber (8), and the distance between the second mercury mirror and the combustion chamber (8) is greater than that between the first mercury mirror and the combustion chamber (8); the first plane mirror and the schlieren light source (7) are respectively arranged obliquely above and laterally below the lower mercury mirror (5); the light generated by the schlieren light source (7) is reflected by the first plane mirror and the second mercury mirror, then enters the combustion chamber (8) through the lower window of the combustion chamber (8), and is emitted to the first mercury mirror through the upper window, and then is reflected by the second plane mirror to the viewfinder of the high-speed camera (2), so that the high-speed camera (2) can shoot the combustion process in the combustion chamber (8); In the experiment, the high-speed camera (2) is used to shoot the combustion process and upload the electronic computer (1) to analyze the flame propagation characteristics.

5. The constant volume bomb test apparatus universally applicable for liquid propellant ignition according to claim 1, wherein, A pair of the opposite nozzles (15) in the combustion chamber (8) should be arranged on the same straight line along the radial direction of the combustion chamber (8), and the outlet ends of the opposite nozzles (15) should be ensured to be within the visible range of the window of the combustion chamber (8).

6. The constant volume bomb experimental apparatus universally applicable to ignition of liquid propellants according to claim 1, wherein The mixing gas tank (10) is connected with the stainless steel pipeline through a connecting flange; when the system is switched, the mixing gas tank (10) can be removed from the connecting flange, and the ambient gas tank (13) can be installed.

7. The constant volume bomb experimental apparatus universally applicable to ignition of liquid propellants according to claim 1, wherein A pair of mounting interfaces are symmetrically arranged on the side wall of the combustion chamber (8), and a replaceable flange is detachably arranged on the mounting interface; the ignition electrodes of the ignition system are mounted on the combustion chamber (8) through the replaceable flange; correspondingly, a pair of the opposite nozzles (15) in the sampling system are also mounted on the combustion chamber (8) through the replaceable flange.

8. The constant volume bomb experimental apparatus universally applicable to ignition of liquid propellants according to claim 1, wherein When the device is used as a constant volume bomb experimental system for non-self-igniting propellant combustion experiment, the experimental process includes: Step 1, open the vacuum pump (11) to start pumping, and then close the valve and the vacuum pump (11) after the pressure display shows a negative value, to ensure the vacuum condition in the combustion chamber (8) and the pipeline; Step 2, the premixed gas is introduced from the mixing gas tank (10), and the internal pressure of the combustion chamber (8) is detected by the pressure sensor to reach the preset value of the experiment; Step 3, after adjusting the optical path, the high-speed camera (2) is turned on to prepare for recording; the ignition electrodes are discharged at the same time by using the synchronous trigger box (4) to ignite the internal premixed gas; Step 4, the experimental results are obtained by analyzing and researching the pressure change data collected by the pressure sensor and the combustion process images collected by the information collection system.

9. The constant volume bomb experimental apparatus universally applicable to ignition of liquid propellants according to claim 1, wherein When the device is used as a constant volume experimental system for self-igniting propellant opposite spraying combustion experiment, the experimental process includes: Step 1, open the vacuum pump (11) to start pumping, after the pressure display shows negative value, close the valve first and then close the vacuum pump (11), to ensure the vacuum condition in the combustion chamber (8) and pipeline; Step 2, under the condition of debugging the information collection system, open the high-speed camera (2) to prepare for recording; use the synchronous trigger box (4) to open the electromagnetic valve connected with the fuel gas tank (12) and the oxidant gas tank (14), observe and record the flowmeter data, and close the electromagnetic valve in time after the combustion to prevent backfire; Step 3, use the pressure change data collected by the pressure sensor and the combustion process image collected by the information collection system to analyze and study, and obtain the experimental results.

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