Auto-ignition liquid propellant hybrid burn boundary condition testing apparatus and method

Abstract

The application discloses a kind of self-ignition liquid propellant mixed combustion boundary condition testing device and method, wherein testing device includes reaction main body, oxidant supply system, combustion agent supply system, delivery monitoring system and control unit.Reaction main body includes reaction box, gate and sensor, gate, sensor are installed on reaction box, gate is closed state and separates reaction box into oxidant chamber and combustion agent chamber, gate is open state and communicates oxidant chamber with combustion agent chamber, sensor is used to monitor the combustion phenomenon in reaction box.Oxidant supply system is used to deliver oxidant to oxidant chamber.Combustion agent supply system is used to deliver combustion agent to combustion agent chamber.Delivery monitoring system is used to monitor the content of oxidant in oxidant chamber and the content of combustion agent in combustion agent chamber.Compared with prior art, the testing device and method provided by the application can be used to explore the boundary condition of combustion and explosion under the condition of self-ignition liquid propellant leakage.

Description

Technical Field

[0001] This invention relates to the field of spontaneously combustible liquid propellant technology, and in particular to a test apparatus and method for testing the boundary conditions of mixed combustion and explosion of spontaneously combustible liquid propellants. Background Technology

[0002] Spontaneously igniting liquid propellants consist of an oxidizer and a propellant. When the oxidizer and propellant come into contact, they can ignite spontaneously without external ignition. During testing and storage, if both the oxidizer and propellant leak simultaneously, the contact between their gaseous and liquid phases can easily lead to combustion and explosion. Currently, there are no relevant testing equipment or methods for determining the boundary conditions for combustion and explosion under leakage conditions. Summary of the Invention

[0003] The purpose of this invention is to provide a test apparatus and method for the combustion and explosion boundary conditions of spontaneously combustible liquid propellants, so as to investigate the boundary conditions for combustion and explosion in the event of leakage of spontaneously combustible liquid propellants.

[0004] To achieve the above objectives, the present invention provides the following solution:

[0005] This invention discloses a test apparatus for the combustion and explosion boundary conditions of spontaneously combusting liquid propellants, comprising:

[0006] The reaction body includes a reaction chamber, a gate, and a sensor. The gate and the sensor are both installed on the reaction chamber. When the gate is in the closed state, it divides the reaction chamber into an oxidant chamber and a combustion agent chamber. When the gate is in the open state, it connects the oxidant chamber and the combustion agent chamber. The sensor is used to monitor combustion and explosion phenomena in the reaction chamber.

[0007] An oxidant supply system for supplying oxidant to the oxidant chamber;

[0008] A propellant supply system for supplying propellant to the propellant chamber;

[0009] A delivery monitoring system is used to monitor the content of oxidant in the oxidant chamber and the content of propellant in the propellant chamber;

[0010] The control unit controls the operation of the gate, the oxidizer supply system, and the propellant supply system, and receives monitoring signals from the delivery monitoring system and the sensors.

[0011] Preferably, the oxidant supply system includes an oxidant tank, which is connected to the oxidant chamber via an oxidant pipeline to supply oxidant to the oxidant chamber; the propellant supply system includes a propellant tank, which is connected to the propellant chamber via a propellant pipeline to supply propellant to the propellant chamber.

[0012] Preferably, the self-igniting liquid propellant mixed combustion and explosion boundary condition testing device further includes a pressurization system, which includes two nitrogen cylinders connected to the oxidizer tank and the propellant tank respectively, to increase the pressure of the oxidizer tank and the propellant tank.

[0013] Preferably, the self-igniting liquid propellant mixed combustion and explosion boundary condition testing device further includes an exhaust gas treatment system, which includes two collection tanks connected to the oxidant chamber and the combustion agent chamber respectively, to collect the exhaust gas in the reaction chamber after the combustion and explosion phenomenon occurs; and two nitrogen cylinders connected to the oxidant chamber and the combustion agent chamber respectively, to discharge the exhaust gas in the reaction chamber after the combustion and explosion phenomenon occurs.

[0014] Preferably, the self-igniting liquid propellant mixed combustion and explosion boundary condition testing device further includes a vacuum system, which includes two vacuum pumps connected to the oxidizer chamber and the propellant chamber respectively, to evacuate the oxidizer chamber and the propellant chamber.

[0015] Preferably, the conveying monitoring system includes two electronic scales, which are used to weigh the oxidant storage tank and the propellant storage tank, respectively.

[0016] Preferably, the delivery monitoring system further includes two flow meters, which are respectively installed on the oxidant pipeline and the propellant pipeline.

[0017] Preferably, the sensor includes at least one of an optical fiber sensor, a temperature sensor, and a pressure sensor.

[0018] Preferably, the self-igniting liquid propellant mixed combustion and explosion boundary condition testing device further includes two high-speed cameras. Both the oxidizer chamber and the propellant chamber are provided with transparent windows, and the two high-speed cameras are respectively aimed at the transparent windows of the oxidizer chamber and the transparent windows of the propellant chamber.

[0019] This invention also discloses a method for testing the combustion and explosion boundary conditions of spontaneously combusting liquid propellants, using the aforementioned testing device for the combustion and explosion boundary conditions of spontaneously combusting liquid propellants, comprising the following steps:

[0020] 1) Load the same volume of propellant and oxidizer into the propellant tank and oxidizer tank respectively;

[0021] 2) Pressurize the propellant tank and oxidizer tank to the same pressure respectively;

[0022] 3) Control the temperatures of the propellant storage tank, oxidant storage tank, and reaction tank within the preset range;

[0023] 4) Evacuate the oxidizer chamber and the fuel chamber separately;

[0024] 5) Add the preset amounts of oxidizer and propellant to the oxidizer chamber and propellant chamber respectively;

[0025] 6) Open the gate and monitor for any signs of combustion or explosion;

[0026] 7) Discharge the exhaust gas from the oxidizer chamber and the combustion chamber.

[0027] The present invention achieves the following technical effects compared to the prior art:

[0028] In this invention, with the gate closed, a preset amount of oxidizer is supplied to the oxidizer chamber via the oxidizer supply system, and a preset amount of propellant is supplied to the propellant chamber via the propellant supply system. Then, the gate is opened, and sensors monitor whether a combustion explosion occurs. Through multiple experiments, using different dosages of oxidizer and propellant in each experiment, the minimum dosage of oxidizer and propellant required for a combustion explosion can be determined. Attached Figure Description

[0029] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0030] Figure 1 This is a schematic diagram of the structure of the test device for the combustion and explosion boundary conditions of self-igniting liquid propellant mixture according to an embodiment of the present invention.

[0031] Explanation of reference numerals in the attached diagram: 1. Nitrogen cylinder; 2. Pressure regulator; 3. Manual shut-off valve; 4. Pressure sensor; 5. Oxidant tank; 6. Propellant tank; 7. Bottom tube; 8. Tank temperature control jacket; 9. Electronic scale; 10. Flow meter; 11. Check valve; 12. Sample injection solenoid valve; 13. Fiber optic sensor; 14. Temperature sensor; 15. Reactor body; 16. Gate; 17. Reactor chamber; 18. Transparent window; 19. High-speed camera; 20. Drive motor; 21. Control unit; 22. Vacuum pump; 23. Vacuum extraction solenoid valve; 24. Safety valve; 25. Waste sample discharge solenoid valve; 26. Purge solenoid valve; 27. Collection tank. Detailed Implementation

[0032] 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, and 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] The purpose of this invention is to provide a test apparatus and method for the combustion and explosion boundary conditions of spontaneously combustible liquid propellants, so as to investigate the boundary conditions for combustion and explosion in the event of leakage of spontaneously combustible liquid propellants.

[0034] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0035] Reference Figure 1 This embodiment provides a test device for the combustion and explosion boundary conditions of self-igniting liquid propellant mixtures (hereinafter referred to as the test device), which includes a reaction body 15, an oxidizer supply system, a propellant supply system, a delivery monitoring system, and a control unit 21.

[0036] The reaction body 15 includes a reaction chamber 17, a gate 16, and sensors. Both the gate 16 and the sensors are mounted on the reaction chamber 17. When the gate 16 is closed, it divides the reaction chamber 17 into an oxidizer chamber and a propellant chamber. When the gate 16 is open, it connects the oxidizer chamber and the propellant chamber. The sensors are used to monitor combustion and explosion phenomena within the reaction chamber 17. An oxidizer supply system is used to supply oxidizer to the oxidizer chamber, and a propellant supply system is used to supply propellant to the propellant chamber. A delivery monitoring system is used to monitor the content of oxidizer in the oxidizer chamber and the content of propellant in the propellant chamber. A control unit 21 controls the operation of the gate 16, the oxidizer supply system, and the propellant supply system, and receives monitoring signals from the delivery monitoring system and the sensors.

[0037] The working principle of the testing device in this embodiment is as follows:

[0038] With gate 16 closed, a preset amount of oxidizer is supplied to the oxidizer chamber via the oxidizer supply system, and a preset amount of propellant is supplied to the propellant chamber via the propellant supply system. Then, gate 16 is opened, and sensors monitor whether a combustion explosion occurs. Through multiple experiments, using different dosages of oxidizer and propellant in each experiment, the boundary conditions for a combustion explosion can be explored, i.e., the minimum dosage of oxidizer and propellant required for a combustion explosion to occur.

[0039] As a possible example, in this embodiment, the oxidant supply system includes an oxidant tank 5, which is connected to the oxidant chamber via an oxidant pipeline to supply oxidant to the oxidant chamber. The combustion agent supply system includes a combustion agent tank 6, which is connected to the combustion agent chamber via a combustion agent pipeline to supply combustion agent to the combustion agent chamber. Specifically, both the oxidant pipeline and the combustion agent pipeline are equipped with a one-way valve 11 and a sample injection solenoid valve 12. The one-way valve 11 is used to allow the oxidant or combustion agent to flow unidirectionally into the reaction chamber 17, and the sample injection solenoid valve 12 is used to control the start and end of the sample injection process. The two sample injection solenoid valves 12 are electrically connected to the control unit 21 to control the sample injection process. Depending on the actual needs, those skilled in the art can also connect the oxidant preparation system to the oxidant chamber and the combustion agent preparation system to the combustion agent chamber to supply oxidant to the oxidant chamber and combustion agent to the combustion agent chamber, respectively.

[0040] As a possible example, in this embodiment, the testing apparatus further includes a pressurization system comprising two nitrogen cylinders 1, which are respectively connected to the oxidant storage tank 5 and the propellant storage tank 6 to increase the pressure in the oxidant storage tank 5 and the propellant storage tank 6. Specifically, a nitrogen pipeline extending into the oxidant storage tank 5 is positioned above the oxidant liquid surface, with one end connected to a bottom insertion tube 7, which extends below the oxidant liquid surface in the oxidant storage tank 5, to pressurize the oxidant in the oxidant storage tank 5 into the oxidant chamber using nitrogen. Similarly, a nitrogen pipeline extending into the propellant storage tank 6 is positioned above the propellant liquid surface, with one end connected to a bottom insertion tube 7, which extends below the propellant liquid surface in the propellant storage tank 6, to pressurize the propellant in the propellant storage tank 6 into the propellant chamber using nitrogen. Manual shut-off valves 3 are installed on the nitrogen lines connecting to the oxidizer tank 5, the propellant tank 6, the oxidizer line, and the propellant line, so that the corresponding lines can be manually shut off in an emergency. Pressure sensors 4 are installed on the nitrogen lines connecting to the oxidizer tank 5 and the propellant tank 6. These pressure sensors 4 are electrically connected to the control unit 21 to monitor the nitrogen pressure.

[0041] As a possible example, in this embodiment, the testing apparatus further includes an exhaust gas treatment system. The exhaust gas treatment system includes two collection tanks 27, which are respectively connected to the oxidant chamber and the combustion chamber to collect exhaust gas from the reaction chamber 17 after a combustion explosion occurs. Both the pipeline connecting the oxidant chamber to the collection tank 27 and the pipeline connecting the combustion chamber to the collection tank 27 are equipped with exhaust sample discharge solenoid valves 25. These exhaust sample discharge solenoid valves 25 are electrically connected to a control unit 21 to control the exhaust sample discharge process. Two nitrogen cylinders 1 are respectively connected to the oxidant chamber and the combustion chamber to discharge exhaust gas from the reaction chamber 17 after a combustion explosion occurs. Both the pipeline connecting the oxidant chamber to the nitrogen cylinder 1 and the pipeline connecting the combustion chamber to the nitrogen cylinder 1 are equipped with purge solenoid valves 26. These purge solenoid valves 26 are electrically connected to the control unit 21 to control the purge of nitrogen into the oxidant chamber and the combustion chamber. A pressure regulator 2 is installed at the outlet of nitrogen cylinder 1. The nitrogen gas discharged from nitrogen cylinder 1 first passes through the pressure regulator 2, and then through the manual shut-off valve 3 or the purging solenoid valve 26.

[0042] As a possible example, in this embodiment, the testing apparatus further includes a vacuum system comprising two vacuum pumps 22, which are respectively connected to the oxidant chamber and the propellant chamber to evacuate the oxidant chamber and the propellant chamber. Vacuum solenoid valves 23 are installed on the pipelines between the oxidant chamber and the vacuum pumps 22, and on the pipelines between the propellant chamber and the vacuum pumps 22. The vacuum solenoid valves 23 are electrically connected to a control unit 21 to control the vacuuming process via the control unit 21.

[0043] As a possible example, in this embodiment, the delivery monitoring system includes two electronic scales 9, which are used to weigh the oxidizer tank 5 and the propellant tank 6, respectively. The two electronic scales 9 are electrically connected to the control unit 21 to transmit weighing data to the control unit 21. Ignoring the nitrogen gas flow rate, the weight reduction of the oxidizer tank 5 represents the amount of oxidizer discharged, and the weight reduction of the propellant tank 6 represents the amount of propellant discharged.

[0044] As a possible example, in this embodiment, the delivery monitoring system also includes two flow meters 10, which are respectively installed on the oxidant pipeline and the propellant pipeline to monitor the flow rate of the oxidant and the flow rate of the propellant.

[0045] As a possible example, in this embodiment, the sensor includes at least one of an optical fiber sensor 13, a temperature sensor 14, and a pressure sensor 4, so that the control unit 21 can determine whether a combustion explosion has occurred by monitoring the flash, temperature, and pressure, respectively. Multiple optical fiber sensors 13, temperature sensors 14, and pressure sensors 4 can be uniformly arranged along the length of the reaction chamber 17 to monitor different locations within the reaction chamber 17.

[0046] As a possible example, in this embodiment, the testing device further includes two high-speed cameras 19. Both the oxidizer chamber and the propellant chamber are equipped with transparent windows 18. The two high-speed cameras 19 are respectively aimed at the transparent windows 18 of the oxidizer chamber and the propellant chamber to capture images of the combustion and explosion process. The high-speed cameras 19 are electrically connected to the control unit 21 to transmit the captured data to the control unit 21.

[0047] As a possible example, in this embodiment, a temperature control jacket is provided outside the reaction chamber 17, and temperature control jackets 8 are provided outside the oxidizer tank 5 and the propellant tank 6, respectively, to control the temperature of the reaction chamber 17, the oxidizer tank 5, and the propellant tank 6. By controlling the temperature, on the one hand, the state of the oxidizer and propellant can be switched, such as gaseous phase or liquid phase, and on the other hand, the temperature boundary conditions for combustion and explosion can be explored.

[0048] As a possible example, in this embodiment, the gate 16 switches between an open state and a closed state by rotation. The gate 16 is connected to the drive motor 20, which is located outside the reaction chamber 17.

[0049] As a possible example, in this embodiment, both the oxidant chamber and the propellant chamber are provided with exhaust ports, and safety valves 24 are installed on the exhaust ports to automatically open when the gas pressure in the oxidant chamber and the propellant chamber reaches a certain level, so as to prevent the reaction chamber 17 from cracking due to excessive internal pressure.

[0050] This embodiment also provides a test method for the combustion and explosion boundary conditions of a self-igniting liquid propellant mixture (hereinafter referred to as the test method), which uses the above-mentioned test device for the combustion and explosion boundary conditions of a self-igniting liquid propellant mixture and includes the following steps:

[0051] 1) Fill the fuel tank 6 and the oxidizer tank 5 with the same volume of fuel and oxidizer respectively, for example, fill 1L of fuel and 1L of oxidizer respectively.

[0052] 2) Pressurize the propellant tank 6 and the oxidizer tank 5 to the same pressure, for example, by introducing nitrogen gas to pressurize the gas pressure in the propellant tank 6 and the oxidizer tank 5 to 0.05MPa.

[0053] 3) The temperatures of the propellant storage tank 6, oxidant storage tank 5, and reaction tank 17 are controlled within a preset range. Specifically, temperature control can be achieved through the temperature control jacket of reaction tank 17 and the temperature control jacket of storage tank 8.

[0054] 4) Evacuate the oxidizer chamber and the fuel chamber separately, for example, by using vacuum pump 22.

[0055] 5) Add the preset amounts of oxidizer and propellant to the oxidizer chamber and propellant chamber respectively.

[0056] 6) Open the gate 16 and monitor whether a combustion or explosion occurs.

[0057] 7) Discharge the exhaust gas from the oxidizer chamber and the combustion chamber. For example, discharge the exhaust gas into the collection tank 27 by introducing nitrogen into the oxidizer chamber and the combustion chamber.

[0058] This specification uses specific examples to illustrate the principles and implementation methods of the present invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of the present invention. Furthermore, those skilled in the art will recognize that, based on the ideas of the present invention, there will be changes in the specific implementation methods and application scope. Therefore, the content of this specification should not be construed as a limitation of the present invention.

Claims

1. A test device for the combustion and explosion boundary conditions of a mixture of self-igniting liquid propellants, characterized in that, include: The reaction body includes a reaction chamber, a gate, and a sensor. The gate and the sensor are both mounted on the reaction chamber. When the gate is closed, it divides the reaction chamber into an oxidant chamber and a propellant chamber. When the gate is open, it connects the oxidant chamber and the propellant chamber. The sensor is used to monitor combustion and explosion phenomena within the reaction chamber. The oxidant chamber and the propellant chamber are located on the left and right sides of the gate, respectively. An oxidant supply system for supplying oxidant to the oxidant chamber; A propellant supply system for supplying propellant to the propellant chamber; A delivery monitoring system is used to monitor the content of oxidant in the oxidant chamber and the content of propellant in the propellant chamber; The control unit controls the operation of the gate, the oxidizer supply system, and the propellant supply system, and receives monitoring signals from the delivery monitoring system and the sensors. The self-igniting liquid propellant mixed combustion and explosion boundary condition test device also includes a vacuum system, which includes two vacuum pumps. The two vacuum pumps are respectively connected to the oxidizer chamber and the propellant chamber to evacuate the oxidizer chamber and the propellant chamber. The oxidant supply system includes an oxidant tank, which is connected to the oxidant chamber via an oxidant pipeline to supply oxidant to the oxidant chamber; the combustion agent supply system includes a combustion agent tank, which is connected to the combustion agent chamber via a combustion agent pipeline to supply combustion agent to the combustion agent chamber. The conveying monitoring system includes two electronic scales, which are used to weigh the oxidant storage tank and the propellant storage tank, respectively. Through multiple experiments, different dosages of oxidizer and propellant were used in each experiment to explore the boundary conditions for the occurrence of combustion explosion, that is, the minimum dosage of oxidizer and propellant when combustion explosion occurs. The conveying monitoring system includes two electronic scales, which are used to weigh the oxidant storage tank and the propellant storage tank, respectively. The delivery monitoring system also includes two flow meters, which are respectively installed on the oxidant pipeline and the propellant pipeline; The outer wall of the reaction chamber is equipped with a reaction chamber temperature control jacket, and the outer walls of the oxidant storage tank and the propellant storage tank are also equipped with storage tank temperature control jackets, which are used to control the temperature of the reaction chamber, oxidant storage tank and propellant storage tank in order to explore the temperature boundary conditions of combustion and explosion.

2. The test apparatus for the combustion and explosion boundary conditions of spontaneously combusting liquid propellants according to claim 1, characterized in that, It also includes a pressurization system comprising two nitrogen cylinders, which are respectively connected to the oxidant tank and the propellant tank to increase the pressure of the oxidant tank and the propellant tank.

3. The test device for the combustion and explosion boundary conditions of spontaneously combusting liquid propellants according to claim 2, characterized in that, It also includes an exhaust gas treatment system, which includes two collection tanks connected to the oxidant chamber and the combustion agent chamber respectively, to collect the exhaust gas in the reaction chamber after a combustion explosion occurs; and two nitrogen cylinders connected to the oxidant chamber and the combustion agent chamber respectively, to discharge the exhaust gas in the reaction chamber after a combustion explosion occurs.

4. The test apparatus for the combustion and explosion boundary conditions of spontaneously combusting liquid propellants according to claim 1, characterized in that, It also includes a vacuum system, which includes two vacuum pumps connected to the oxidant chamber and the propellant chamber respectively, to evacuate the oxidant chamber and the propellant chamber.

5. The test apparatus for the combustion and explosion boundary conditions of spontaneously combusting liquid propellants according to claim 1, characterized in that, The sensor includes at least one of an optical fiber sensor, a temperature sensor, and a pressure sensor.

6. The test apparatus for the combustion and explosion boundary conditions of spontaneously combusting liquid propellants according to claim 1, characterized in that, It also includes two high-speed cameras, and both the oxidant chamber and the propellant chamber are provided with transparent windows. The two high-speed cameras are respectively aimed at the transparent windows of the oxidant chamber and the transparent windows of the propellant chamber.

7. A method for testing the boundary conditions of spontaneous combustion liquid propellant mixtures, characterized in that, The test apparatus for testing the combustion and explosion boundary conditions of spontaneously combusting liquid propellants as described in any one of claims 1 to 6 includes the following steps: 1) Load the same volume of propellant and oxidizer into the propellant tank and oxidizer tank respectively; 2) Pressurize the propellant tank and oxidizer tank to the same pressure respectively; 3) Control the temperatures of the propellant storage tank, oxidant storage tank, and reaction tank within the preset range; 4) Evacuate the oxidizer chamber and the fuel chamber separately; 5) Add the preset amounts of oxidizer and propellant to the oxidizer chamber and propellant chamber respectively; 6) Open the gate and monitor for any signs of combustion or explosion; 7) Discharge the exhaust gas from the oxidizer chamber and the combustion chamber.

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