Ignition agent processing device and processing method for liquid rocket engine

Abstract

The present invention discloses an ignition agent processing device for a liquid rocket engine and a processing method thereof, comprising an ignition agent tank, a high-pressure gas extrusion component, a control valve component, a gas cleaning component, a liquid cleaning component and a discharge component; the present invention inputs high-pressure gas into the ignition agent tank to extrude the remaining ignition agent, introduces kerosene multiple times through a kerosene interface to replace the remaining ignition agent in the ignition agent tank, and discharges the ignition agent and kerosene mixture; introduces nitrogen from a nitrogen interface to blow off the ignition agent tank outlet pipeline, and discharges the ignition agent and kerosene mixture attached to the pipeline wall; through multiple blowing, the ignition agent in the pipeline is completely blown out, so that the ignition agent in the engine is completely discharged, thereby improving safety. Compared with the existing technology, the present invention has the advantages of simple structure and easy operation.

Description

Technical Field

[0001] The present invention relates to the technical field of engine ignition agent treatment, and in particular to an ignition agent treatment device for a liquid rocket engine and a treatment method thereof. Background Art

[0002] The ignition forms of liquid rocket engines are: self-igniting liquid ignition, solid gunpowder ignition, and torch ignition. They have their own advantages. Among them, natural liquid ignition has the advantages of small usage, reliable starting and ignition, simple operation, and high controllability. Its disadvantage is that it reacts violently when encountering air or water, so it is extremely important to post-process it during use.

[0003] After a liquid rocket engine uses hypergolic liquid to ignite, a certain amount of ignition agent remains inside the tank, which needs to be processed to avoid danger. Summary of the Invention

[0004] In view of this, the main object of the present invention is to provide an ignition agent processing device and a processing method for a liquid rocket engine.

[0005] To achieve the above object, the technical solution of the present invention is achieved as follows:

[0006] Embodiment 1 of the present invention provides an ignition agent processing device for a liquid rocket engine, comprising an ignition agent tank, a high-pressure gas extrusion assembly, a control valve assembly, a gas cleaning assembly, a liquid cleaning assembly, and a drain assembly. The high-pressure gas extrusion assembly is disposed at the top of the ignition agent tank and is used to inject high-pressure gas to squeeze out the remaining ignition agent in the ignition agent tank. The other end of the ignition agent tank is connected to the gas cleaning assembly and the liquid cleaning assembly respectively through the control valve assembly, so as to clean the remaining ignition agent in the ignition agent tank by gas or liquid. The drain assembly is connected to the other end of the ignition agent tank and is used to remove the remaining ignition agent in the ignition agent tank.

[0007] Preferably, the high-pressure gas extrusion assembly of the present invention includes a high-pressure gas interface and a first valve, one end of the high-pressure gas interface is connected to one end of the first valve, and the other end of the first valve is connected to one end of the ignition agent tank.

[0008] Preferably, the control valve assembly of the present invention includes a solenoid valve and a one-way valve, the other end of the ignition agent tank is connected to one end of the solenoid valve, the other end of the solenoid valve is connected to one end of the one-way valve, and the other end of the one-way valve is respectively connected to the gas cleaning assembly and the liquid cleaning assembly.

[0009] Preferably, the gas cleaning component of the present invention includes a second valve and a nitrogen interface, one end of the second valve is connected to the other end of the one-way valve, and the other end of the second valve is connected to the nitrogen interface.

[0010] Preferably, the liquid cleaning assembly of the present invention includes a third valve and a kerosene interface, one end of the third valve is connected to the other end of the one-way valve, and the other end of the third valve is connected to the kerosene interface.

[0011] Preferably, the discharge assembly of the present invention includes a fourth valve and a discharge port, one end of the fourth valve is connected to the other end of the solenoid valve, and the other end of the fourth valve is connected to the discharge port.

[0012] A second embodiment of the present invention provides a method for treating the ignition agent of a liquid rocket engine, comprising the following steps:

[0013] S1: Open the first valve and input high-pressure gas into the ignition agent tank through the high-pressure gas interface to squeeze the remaining ignition agent in the ignition agent tank. At the same time, open the fourth valve and squeeze the ignition agent out of the discharge port.

[0014] S2: Close the first and fourth valves, introduce kerosene multiple times through the kerosene port, open the third valve to displace the remaining ignition agent in the ignition agent tank, and open the fourth valve to discharge the ignition agent and kerosene mixture. Through multiple replacements, the remaining ignition agent in the ignition agent tank is completely discharged;

[0015] S3: Close the first valve, the third valve and the fourth valve, introduce nitrogen from the nitrogen interface, open the second valve to blow out the ignition agent tank outlet pipeline, open the fourth valve to discharge the ignition agent and kerosene mixture attached to the pipe wall, and through multiple blows, all the ignition agent in the pipeline is blown out.

[0016] Compared with the prior art, the present invention has the following beneficial effects:

[0017] The present invention inputs high-pressure gas into the ignition agent tank to extrude the remaining ignition agent, introduces kerosene multiple times from the kerosene interface to replace the remaining ignition agent in the ignition agent tank, discharges the ignition agent and kerosene mixture, introduces nitrogen from the nitrogen interface, blows out the ignition agent tank outlet pipe, and discharges the ignition agent and kerosene mixture attached to the pipe wall. Through multiple blows, the ignition agent in the pipe is completely blown out, so that the ignition agent in the engine is completely discharged, thereby improving safety. Compared with the existing technology, the present invention has the advantages of simple structure and easy operation. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The accompanying drawings described herein are used to further understand the present invention and constitute a part of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the accompanying drawings:

[0019] Figure 1The present invention is a schematic structural diagram of an air supply mechanism for use in an ignition agent processing device for a liquid rocket engine according to an embodiment of the present invention. DETAILED DESCRIPTION

[0020] In order to make the purpose, technical solutions and advantages of the present invention more clearly understood, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention.

[0021] The same or similar numbers in the drawings of this embodiment correspond to the same or similar parts; in the description of the present invention, it should be understood that the terms "upper", "lower", "left", "right", "inner", "outer", etc. indicating the orientation or position relationship are based on the orientation or position relationship shown in the drawings, which is only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation. Therefore, the terms describing the position relationship in the drawings are only used for illustrative purposes and cannot be understood as limiting this patent. For ordinary technicians in this field, the specific meanings of the above terms can be understood according to specific circumstances.

[0022] It should be noted that, in this document, the terms "comprises," "includes," or any other variations thereof are intended to encompass non-exclusive inclusion, such that a process, article, or device comprising a series of elements includes not only those elements but also other elements not explicitly listed, or elements inherent to such process, article, or device. In the absence of further limitations, an element defined by the phrase "comprising a ..." does not exclude the presence of other identical elements in the process, article, or device comprising the element.

[0023] The first embodiment of the present invention provides an ignition agent processing device for a liquid rocket engine, such as Figure 1 As shown, it includes an ignition agent tank 1, a high-pressure gas extrusion assembly, a control valve assembly, a gas cleaning assembly, a liquid cleaning assembly and a drain assembly. The high-pressure gas extrusion assembly is arranged on the top of the ignition agent tank 1, and is used to inject high-pressure gas to squeeze out the remaining ignition agent in the ignition agent tank 1. The other end of the ignition agent tank 1 is connected to the gas cleaning assembly and the liquid cleaning assembly respectively through the control valve assembly, which is the same as cleaning the remaining ignition agent in the ignition agent tank 1 by gas or liquid. The drain assembly is connected to the other end of the ignition agent tank 1 for removing the remaining ignition agent in the ignition agent tank 1.

[0024] like Figure 1As shown, the high-pressure gas extrusion assembly includes a high-pressure gas interface 11 and a first valve 20 , one end of the high-pressure gas interface 11 is connected to one end of the first valve 20 , and the other end of the first valve 20 is connected to one end of the ignition agent tank 1 .

[0025] like Figure 1 As shown, the control valve assembly includes a solenoid valve 19 and a one-way valve 18. The other end of the ignition agent tank 1 is connected to one end of the solenoid valve 19, the other end of the solenoid valve 19 is connected to one end of the one-way valve 18, and the other end of the one-way valve 18 is connected to the gas cleaning assembly and the liquid cleaning assembly respectively.

[0026] like Figure 1 As shown, the gas cleaning component includes a second valve 15 and a nitrogen interface 12 , one end of the second valve 15 is connected to the other end of the one-way valve 18 , and the other end of the second valve 15 is connected to the nitrogen interface 12 .

[0027] like Figure 1 As shown, the liquid cleaning component includes a third valve 16 and a kerosene interface 13 , one end of the third valve 16 is connected to the other end of the one-way valve 18 , and the other end of the third valve 16 is connected to the kerosene interface 13 .

[0028] like Figure 1 As shown, the drainage component includes a fourth valve 17 and a drainage port 14 , one end of the fourth valve 17 is connected to the other end of the solenoid valve 19 , and the other end of the fourth valve 17 is connected to the drainage port 14 .

[0029] A second embodiment of the present invention provides a method for treating the ignition agent of a liquid rocket engine, comprising the following steps:

[0030] S1: Open the first valve 20 and input high-pressure gas into the ignition agent tank 1 through the high-pressure gas interface 11 to squeeze the remaining ignition agent in the ignition agent tank 1. At the same time, open the fourth valve 17 to squeeze the ignition agent out of the discharge port 14.

[0031] S2: Close the first valve 20 and the fourth valve 17, and introduce kerosene multiple times through the kerosene interface 13. Open the third valve 16 to displace the remaining ignition agent in the ignition agent tank 1. Open the fourth valve 17 to discharge the ignition agent and kerosene mixture. Through multiple replacements, the remaining ignition agent in the ignition agent tank is completely discharged.

[0032] S3: Close the first valve 20, the third valve 16 and the fourth valve 17, introduce nitrogen from the nitrogen interface 12, open the second valve 15 to purge the outlet pipe of the ignition agent tank 1, and open the fourth valve 17 to discharge the ignition agent and kerosene mixture attached to the pipe wall. After multiple purges, all the ignition agent in the pipe is blown out.

[0033] In summary, the present invention inputs high-pressure gas into the ignition agent tank, squeezes out the remaining ignition agent, introduces kerosene multiple times from the kerosene interface, replaces the remaining ignition agent in the ignition agent tank, discharges the ignition agent and kerosene mixture, introduces nitrogen from the nitrogen interface, blows out the ignition agent tank outlet pipe, and discharges the ignition agent and kerosene mixture attached to the pipe wall. Through multiple blows, the ignition agent in the pipe is completely blown out, so that the ignition agent in the engine is completely discharged, thereby improving safety. Compared with the existing technology, the present invention has the advantages of simple structure and easy operation.

[0034] The above description is merely a preferred embodiment of the present invention and is not intended to limit the scope of protection of the present invention.

Claims

1. A liquid rocket engine ignition agent processing device, characterized in that: The ignition agent storage tank comprises an ignition agent storage tank, a high-pressure gas extrusion assembly, a control valve assembly, a gas cleaning assembly, a liquid cleaning assembly and a drain assembly. The high-pressure gas extrusion assembly is arranged on the top of the ignition agent storage tank and is used to inject high-pressure gas to squeeze out the remaining ignition agent in the ignition agent storage tank. The other end of the ignition agent storage tank is connected to the gas cleaning assembly and the liquid cleaning assembly respectively through the control valve assembly, so as to clean the remaining ignition agent in the ignition agent storage tank by gas or liquid. The drain assembly is connected to the other end of the ignition agent storage tank and is used to remove the remaining ignition agent in the ignition agent storage tank. The control valve assembly includes a solenoid valve and a one-way valve. The other end of the ignition agent tank is connected to one end of the solenoid valve, the other end of the solenoid valve is connected to one end of the one-way valve, and the other end of the one-way valve is respectively connected to the gas cleaning assembly and the liquid cleaning assembly.

2. The ignition agent processing device for liquid rocket engines according to claim 1, characterized in that: The high-pressure gas extrusion assembly includes a high-pressure gas interface and a first valve, one end of the high-pressure gas interface is connected to one end of the first valve, and the other end of the first valve is connected to one end of the ignition agent tank.

3. The ignition agent processing device for liquid rocket engines according to claim 1, characterized in that: The gas cleaning component includes a second valve and a nitrogen interface, one end of the second valve is connected to the other end of the one-way valve, and the other end of the second valve is connected to the nitrogen interface.

4. The ignition agent processing device for liquid rocket engines according to claim 3, characterized in that: The liquid cleaning component includes a third valve and a kerosene interface. One end of the third valve is connected to the other end of the one-way valve, and the other end of the third valve is connected to the kerosene interface.

5. The ignition agent processing device for liquid rocket engines according to claim 4, characterized in that: The drainage component includes a fourth valve and a drainage port. One end of the fourth valve is connected to the other end of the solenoid valve, and the other end of the fourth valve is connected to the drainage port.

6. A method for treating liquid rocket engine ignition agent according to any one of claims 1 to 5, characterized in that: The following steps are involved: S1: Open the first valve and input high-pressure gas into the ignition agent tank through the high-pressure gas interface to squeeze the remaining ignition agent in the ignition agent tank. At the same time, open the fourth valve and squeeze the ignition agent out of the discharge port. S2: Close the first and fourth valves, introduce kerosene multiple times through the kerosene port, open the third valve to displace the remaining ignition agent in the ignition agent tank, and open the fourth valve to discharge the ignition agent and kerosene mixture. Through multiple replacements, the remaining ignition agent in the ignition agent tank is completely discharged; S3: Close the first valve, the third valve and the fourth valve, introduce nitrogen from the nitrogen interface, open the second valve to blow out the ignition agent tank outlet pipeline, open the fourth valve to discharge the ignition agent and kerosene mixture attached to the pipe wall, and through multiple blows, all the ignition agent in the pipeline is blown out.

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