Liquid rocket engine ignition agent integrated control system adopting control gas extrusion

Abstract

The invention discloses a liquid rocket engine ignition agent integrated control system adopting control gas extrusion, and relates to the technical field of liquid rocket engines. The system comprises a control gas cylinder, an extrusion gas control valve, an ignition agent storage box, a diaphragm valve, an integrated control valve and a plurality of one-way valves. High-pressure gas is stored in the control gas cylinder and enters an extrusion opening of the ignition agent storage box through one path of shunting, and the ignition agent is extruded and conveyed. A diaphragm valve is arranged at an outlet of the ignition agent storage box, the extrusion pressure enables the diaphragm valve to be exploded and opened, and the ignition agent flows out to the integrated control valve. The integrated control valve is a multi-way valve and can perform centralized control on a generator ignition agent, a thrust chamber ignition agent and ignition agent leakage, so that the ignition agents accurately and timely enter the thrust chamber and the generator for ignition. According to the liquid rocket engine ignition agent integrated control system adopting control gas extrusion, the integrated control valve can be adopted for carrying out integrated control on the ignition agent, so that a liquid rocket engine system is simplified, the weight is reduced, and the reliability is improved.

Description

Technical Field

[0001] This invention relates to the field of liquid rocket engine technology, and in particular to an integrated control system for the ignition agent of a liquid rocket engine employing controlled gas compression. Background Technology

[0002] Liquid rocket engines generally use chemical ignition propellants for ignition. Typically, a separate extrusion cylinder provides high-pressure gas to extrude the ignition propellant tank. After the ignition propellant is extruded downstream, kerosene is introduced to continuously extrude and deliver the ignition propellant. A separate ignition propellant control valve then precisely and promptly directs the ignition propellant into the thrust chamber and generator to ignite the propellant. Furthermore, for system maintenance, a separate ignition propellant venting valve and related piping are required.

[0003] For liquid rocket engine ignition control systems, the separate ignition extrusion cylinders, ignition control valves, ignition discharge valves, and corresponding pipelines make system control complex, increase structural weight, limit reliability, and are not conducive to compact engine design. Summary of the Invention

[0004] The purpose of this invention is to overcome the shortcomings of the prior art and provide an integrated control system for liquid rocket engine ignition agents that is simple in structure, highly integrated, and reliable.

[0005] The technical solution adopted by this invention to solve its technical problem is as follows:

[0006] An integrated control system for liquid rocket engine igniter using control gas compression includes a control gas cylinder, a compression gas control valve, an igniter tank, a diaphragm valve, an integrated control valve, and multiple check valves.

[0007] The control gas cylinder stores high-pressure gas to provide valve control gas for the engine. The gas in the control gas cylinder is diverted through a branch line to the compression port of the ignition agent reservoir via the compression gas control valve, compressing and delivering the ignition agent. The compression gas control valve is used to control the on / off flow of the compression gas.

[0008] The ignition agent reservoir is used to store the ignition agent, and a diaphragm valve is installed at its outlet. When the engine is not running, the diaphragm valve isolates the ignition agent reservoir from the downstream pipeline to prevent ignition agent leakage. When the engine is igniting, the extrusion gas control valve opens, and the extrusion pressure causes the diaphragm valve to burst open, allowing the ignition agent to flow out to the integrated control valve.

[0009] The integrated control valve is used to precisely and timely control the entry of the ignition agent into the thrust chamber and generator for ignition. The integrated control valve has one inlet and three outlets. The inlet of the integrated control valve is connected to the outlet of the diaphragm valve. The three outlets of the integrated control valve are, respectively, the thrust chamber ignition agent supply port, the generator ignition agent supply port, and the ignition agent discharge port.

[0010] Preferably, the integrated control valve is a multi-way valve, including an integrated control valve body and an integrated control valve core disposed within the integrated control valve body. The integrated control valve inlet, the thrust chamber ignition agent supply port, the generator ignition agent supply port, and the ignition agent discharge port are all located on the valve body. The integrated control valve core is provided with a flow channel for connecting the integrated control valve inlet with the thrust chamber ignition agent supply port, the generator ignition agent supply port, and the ignition agent discharge port.

[0011] Preferably, the integrated control valve core can independently control the on / off state of the thrust chamber ignition agent supply port, the generator ignition agent supply port, and the ignition agent discharge port, thereby opening and closing one or more outlets.

[0012] Preferably, the integrated control valve is a pneumatic valve or a solenoid valve.

[0013] Preferably, a purging inlet is provided on the pipeline after the diaphragm valve, and the medium introduced is nitrogen or kerosene. Before engine ignition, nitrogen is introduced through the purging inlet to purge the pipeline between the diaphragm valve and the integrated control valve. After engine ignition, kerosene is introduced through the purging inlet to replace and clean the ignition agent delivery pipeline and the ignition agent tank with kerosene, followed by nitrogen purging and drying to ensure the safety of the pipeline and the ignition agent tank.

[0014] Preferably, the plurality of one-way valves include a purge one-way valve, a thrust chamber ignition circuit one-way valve, and a generator ignition circuit one-way valve, which are respectively installed on the rear end pipelines of the purge inlet, the thrust chamber ignition propellant supply port, and the generator ignition propellant supply port to prevent backflow of the pipeline medium when the engine is running.

[0015] Preferably, the high-pressure gas stored in the control cylinder is nitrogen or helium.

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

[0017] (1) In the liquid rocket engine ignition agent control system of the present invention, the ignition agent is centrally distributed and controlled by an integrated control valve, which simplifies the valve configuration, reduces the delivery pipeline, and simplifies the engine ignition system, reduces its weight, and improves its reliability.

[0018] (2) In the liquid rocket engine ignition agent control system of the present invention, the existing control gas cylinder of the engine is used as the ignition agent extrusion gas source. The system does not set up independent extrusion gas cylinders and related pipelines, and does not introduce other ignition agent extrusion media. The ignition agent extrusion method is simple, the number of system components is reduced, and the system complexity is reduced.

[0019] (3) This invention proposes a complete integrated control system for liquid rocket engine igniter. The igniter is delivered by controlling the gas cylinder as the igniter extrusion gas source. The thrust chamber and generator are ignited by the integrated control valve. The ignition control system is maintained by the blow-out port and the igniter discharge port. Attached Figure Description

[0020] To more clearly illustrate the technical solutions of the embodiments of this invention, the drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are some embodiments of this invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0021] Figure 1 This is a schematic diagram of an integrated control system for an igniter using controlled gas extrusion, as an example of the present invention.

[0022] Figure 2 This is a schematic diagram of the integrated control valve in the embodiment.

[0023] Explanation of the markings in the image:

[0024] 1-Control gas cylinder; 2-Compressed gas control valve; 3-Ignition agent storage tank; 4-Diaphragm valve; 5-Integrated control valve; 61-Purge check valve; 62-Thrust chamber ignition circuit check valve; 63-Generator ignition circuit check valve; 51-Integrated control valve body; 52-Integrated control valve core; 53-Integrated control valve inlet; 54-Thrust chamber ignition agent supply port; 55-Generator ignition agent supply port; 56-Ignition agent discharge port. Detailed Implementation

[0025] 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, not all, of the embodiments of the present invention. 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.

[0026] It should also be understood that the terminology used in this specification is for the purpose of describing particular embodiments only and is not intended to limit the invention. As used in this specification and the appended claims, the singular forms “a,” “an,” and “the” are intended to include the plural forms unless the context clearly indicates otherwise.

[0027] It should also be further understood that the term "and / or" as used in this specification and the appended claims refers to any combination of one or more of the associated listed items and all possible combinations, and includes such combinations.

[0028] Example

[0029] See Figure 1 The liquid rocket engine ignition agent integrated control system shown includes a control gas cylinder 1, a squeeze gas control valve 2, an ignition agent storage tank 3, a diaphragm valve 4, an integrated control valve 5, and multiple check valves.

[0030] The control gas cylinder 1 stores high-pressure gas to provide valve control gas for the engine. The gas in the control gas cylinder 1 is diverted through a branch line and enters the compression port of the ignition agent reservoir 3 via the compression gas control valve 2, compressing and delivering the ignition agent. The compression gas control valve 2 is used to control the on / off flow of the compression gas.

[0031] The ignition agent reservoir 3 is used to store the ignition agent, and a diaphragm valve 4 is installed at its outlet. When the engine is not running, the diaphragm valve 4 is used to isolate the ignition agent reservoir from the downstream pipeline to prevent ignition agent leakage. When the engine is igniting, the extrusion gas control valve 2 opens, and the extrusion pressure causes the diaphragm valve 4 to burst open, allowing the ignition agent to flow out to the integrated control valve 5.

[0032] The integrated control valve 5 is used to control the precise and timely entry of the ignition agent into the thrust chamber and generator for ignition. The integrated control valve 5 has one inlet and three outlets. The integrated control valve inlet 53 is connected to the outlet of the diaphragm valve 4. The three outlets of the integrated control valve 5 are the thrust chamber ignition agent supply port 54, the generator ignition agent supply port 55, and the ignition agent discharge port 56.

[0033] The integrated control valve 5 is a multi-way valve, comprising an integrated control valve body 51 and an integrated control valve core 52 disposed within the integrated control valve body. The integrated control valve inlet 53, the thrust chamber ignition agent supply port 54, the generator ignition agent supply port 55, and the ignition agent discharge port 56 are all located on the valve body. The valve core 52 has a flow channel for connecting the integrated control valve inlet 53 with the thrust chamber ignition agent supply port 54, the generator ignition agent supply port 55, and the ignition agent discharge port 56.

[0034] The integrated control valve core 52 can independently control the on / off state of the thrust chamber ignition agent supply port 53, the generator ignition agent supply port 54, and the ignition agent discharge port 55, thereby enabling the opening and closing of one or more outlets.

[0035] The integrated control valve 5 is either a pneumatic valve or a solenoid valve.

[0036] A purge inlet is installed on the pipeline downstream of diaphragm valve 4, and the medium introduced is nitrogen or kerosene. Before engine ignition, nitrogen is introduced through the purge inlet to purge the pipeline between diaphragm valve 4 and integrated control valve 5. After engine ignition, kerosene is introduced through the purge inlet to replace and clean the ignition agent delivery pipeline and ignition agent tank 3 with kerosene, followed by nitrogen purging and drying to ensure the safety of the pipeline and ignition agent tank 3.

[0037] Multiple one-way valves, including a purge one-way valve 61, a thrust chamber ignition circuit one-way valve 62, and a generator ignition circuit one-way valve 63, are respectively installed on the rear pipelines of the purge inlet, the thrust chamber ignition propellant supply port, and the generator ignition propellant supply port to prevent backflow of the pipeline medium when the engine is running.

[0038] The high-pressure gas stored in cylinder 1 is controlled to be either nitrogen or helium.

[0039] The ignition control system of this liquid rocket engine operates as follows:

[0040] (1) Before engine ignition, the extrusion gas control valve 2 is closed, and the diaphragm valve 4 reliably isolates the ignition agent tank 3 from the downstream pipeline to prevent ignition agent leakage. Nitrogen gas is introduced into the purging inlet to purge impurities from the pipeline between the diaphragm valve 4 and the integrated control valve 5. The ignition agent outlet 56 of the integrated control valve 5 is open to discharge nitrogen gas. The thrust chamber ignition agent supply port 54 and the generator ignition agent supply port 55 of the integrated control valve 5 are closed.

[0041] (2) When the engine is ignited, the compression gas control valve 2 opens, allowing the high-pressure gas in the control gas cylinder 1 to enter the compression port of the ignition agent storage tank 3. The compression pressure causes the diaphragm valve 4 to burst and open, allowing the ignition agent to flow out to the inlet 53 of the integrated control valve. The valve core 52 of the integrated control valve actuates, closing the ignition agent outlet 56 and opening the thrust chamber ignition agent supply port 54 and the generator ignition agent supply port 55, accurately and timely delivering the ignition agent to the thrust chamber and the generator for ignition.

[0042] (3) After the engine ignition is completed, the extrusion gas control valve 2 is closed, the integrated control valve core 52 is activated, the thrust chamber ignition agent supply port 54 and the generator ignition agent supply port 55 are closed, and the ignition agent discharge port 56 is opened, allowing the ignition agent to discharge. Kerosene is introduced into the purging inlet to replace and clean the ignition agent delivery pipeline and the ignition agent storage tank 3 with kerosene. Nitrogen is then introduced for purging and drying to ensure the safety of the pipeline and the ignition agent storage tank 3.

[0043] The ignition propellant integrated control system of the present invention, which adopts control gas extrusion, can use an integrated control valve to control the ignition propellant and use existing control gas cylinders as the ignition propellant extrusion gas source, which simplifies the liquid rocket engine system, reduces weight, and improves reliability, and has a wide range of applications in the field of rocket engines.

[0044] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any person skilled in the art can easily conceive of various equivalent modifications or substitutions within the technical scope disclosed in the present invention, and these modifications or substitutions should all be covered within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

[0045] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. An integrated control system for the ignition agent of a liquid rocket engine employing controlled gas compression, characterized in that, It includes a control gas cylinder, a squeeze gas control valve, an ignition agent tank, a diaphragm valve, an integrated control valve, and multiple check valves; The control gas cylinder stores high-pressure gas to provide valve control gas for the engine; the gas in the control gas cylinder is diverted through the extrusion gas control valve to the extrusion port of the ignition agent storage tank to extrude and deliver the ignition agent; the extrusion gas control valve is used to control the on / off of the extrusion gas. The ignition agent reservoir is used to store ignition agent, and the diaphragm valve is installed at the outlet. When the engine is not running, the diaphragm valve is used to isolate the ignition agent reservoir from the downstream pipeline to prevent ignition agent leakage. When the engine is igniting, the extrusion gas control valve is opened, and the extrusion pressure causes the diaphragm valve to burst open, and the ignition agent flows out to the integrated control valve. The integrated control valve is used to control the precise and timely entry of the ignition agent into the thrust chamber and generator for ignition; the integrated control valve has one inlet and three outlets, the inlet of the integrated control valve is connected to the outlet of the diaphragm valve; the three outlets of the integrated control valve are the thrust chamber ignition agent supply port, the generator ignition agent supply port, and the ignition agent discharge port, respectively.

2. The integrated control system for liquid rocket engine igniter using controlled gas compression as described in claim 1, characterized in that, The integrated control valve is a multi-way valve, comprising an integrated control valve body and an integrated control valve core disposed within the integrated control valve body. The integrated control valve inlet, the thrust chamber ignition agent supply port, the generator ignition agent supply port, and the ignition agent discharge port are all located on the valve body. The integrated control valve core is provided with a flow channel for connecting the integrated control valve inlet with the thrust chamber ignition agent supply port, the generator ignition agent supply port, and the ignition agent discharge port.

3. The integrated control system for liquid rocket engine igniter using controlled gas compression as described in claim 2, characterized in that, The integrated control valve core can independently control the on / off state of the thrust chamber ignition agent supply port, the generator ignition agent supply port, and the ignition agent discharge port, thereby opening and closing one or more outlets.

4. The integrated control system for liquid rocket engine igniter using controlled gas compression as described in claim 1, characterized in that, The integrated control valve is either a pneumatic valve or a solenoid valve.

5. The integrated control system for liquid rocket engine igniter using controlled gas compression as described in claim 1, characterized in that, A purge inlet is provided on the pipeline downstream of the diaphragm valve, and the medium introduced is nitrogen or kerosene. Before engine ignition, nitrogen is introduced through the purge inlet to purge the pipeline between the diaphragm valve and the integrated control valve. After engine ignition, kerosene is introduced through the purge inlet to replace and clean the ignition agent delivery pipeline and the ignition agent tank with kerosene, followed by nitrogen purging and drying to ensure the safety of the pipeline and the ignition agent tank.

6. The integrated control system for liquid rocket engine igniter using controlled gas compression as described in claim 1, characterized in that, The plurality of one-way valves include a purge one-way valve, a thrust chamber ignition circuit one-way valve, and a generator ignition circuit one-way valve, which are respectively installed on the rear end pipelines of the purge inlet, the thrust chamber ignition propellant supply port, and the generator ignition propellant supply port to prevent backflow of the pipeline medium when the engine is running.

7. The integrated control system for liquid rocket engine igniter using controlled gas compression as described in claim 1, characterized in that, The high-pressure gas stored in the control cylinder is nitrogen or helium.

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