Multi-ignition system and ignition method for liquid carrier rocket engine

Abstract

The invention discloses a liquid carrier rocket engine multi-ignition system and method, and the liquid carrier rocket engine multi-ignition system comprises a diaphragm storage tank, a plurality of liquid carrier rocket engines and a plurality of ignition control valves; the diaphragm storage box comprises a gas cavity and a liquid cavity; the multiple liquid carrier rocket engines are arranged in parallel and can communicate with the liquid cavity. The number of the ignition control valves is the same as that of the liquid carrier rocket engines, and the ignition control valves are in one-to-one correspondence with the liquid carrier rocket engines; the ignition control valve is configured to control the ignition agent in the liquid cavity to enter the corresponding liquid carrier rocket engine through opening and closing of the ignition control valve, and multiple times of ignition of the corresponding liquid carrier rocket engine is achieved. The multi-engine parallel liquid carrier rocket engine can be ignited multiple times, the structure is simple, operation is safe and convenient, and the ignition stability is high.

Description

Technical Field

[0001] The invention relates to the technical field of liquid engine ignition, and in particular to a multiple ignition system and an ignition method for a liquid carrier rocket engine. Background Art

[0002] With the development of aerospace technology, liquid rockets need engines to be ignited multiple times to meet the needs of launch vehicles. With the development of liquid rocket recovery technology, higher requirements are placed on the number of multiple ignitions of the engine. At present, the multiple ignitions of liquid rocket engines at home and abroad mainly include spark ignition, gunpowder ignition and ignition agent ignition. Among them, spark ignition has low energy and is less used. The gunpowder ignition system is simple, but if multiple ignitions are achieved, multiple ignition noses need to be set up, the structural reliability is poor, and the fuel gas slag is easy to clog the ignition nozzle. The ignition agent has high ignition energy and reliable ignition.

[0003] However, in the existing ignition solution using ignition agent, the engine can only be ignited once. When igniting multiple times, multiple ignition tubes need to be set in parallel. The ignition system structure is complex, the number of ignitions is limited, and the reliability is low. In addition, the ignition tube is blocked by a diaphragm or cut by an air explosion valve, and the pipeline is easily blocked after the diaphragm is damaged.

[0004] In view of this, it is necessary to provide a new technical solution to solve the above problems. Summary of the invention

[0005] In order to solve the above technical problems, the present application provides a liquid carrier rocket engine multiple ignition system and ignition method, which can be used for multiple ignitions of multiple liquid carrier rocket engines connected in parallel and has high ignition stability.

[0006] A multiple ignition system for a liquid carrier rocket engine, comprising:

[0007] a diaphragm tank; the diaphragm tank comprising an air chamber capable of communicating with the gas storage device and a liquid chamber for storing an ignition agent;

[0008] A plurality of liquid carrier rocket engines; the plurality of liquid carrier rocket engines are all capable of communicating with the liquid cavity, and the plurality of liquid carrier rocket engines are arranged in parallel with each other;

[0009] A plurality of ignition control valves; the number of the ignition control valves is the same as the number of the liquid carrier rocket engines, and corresponds one to one with the liquid carrier rocket engines; the ignition control valve is arranged on a liquid connecting pipeline between the liquid carrier rocket engine and the liquid cavity; the ignition control valve is configured to control the ignition agent in the liquid cavity to enter the corresponding liquid carrier rocket engine through its opening and closing, so as to realize multiple ignitions of the corresponding liquid carrier rocket engine.

[0010] Preferably, it also includes a plurality of ignition check valves having the same number as the liquid carrier rocket engine; the ignition check valves are arranged on the liquid connecting pipeline between the liquid carrier rocket engine and the liquid chamber.

[0011] Preferably, the ignition check valve is arranged on the liquid connecting pipeline between the outlet end of the ignition control valve and the liquid carrier rocket engine.

[0012] Preferably, the gas storage device is a pressurized gas cylinder; the gas storage device is connected to the gas cavity via a gas connecting pipeline; the gas connecting pipeline is provided with a self-locking control valve for controlling the gas in the gas storage device to enter the gas cavity.

[0013] Preferably, it also includes a pressure reducing valve; the pressure reducing valve is arranged on the gas connecting pipeline between the gas outlet end of the self-locking control valve and the gas cavity inlet.

[0014] Preferably, it also includes a gas filling valve connected to the gas cavity through a gas connecting pipeline and used to control the injection of gas into the gas storage device.

[0015] Preferably, it also includes an ignition agent filling valve which is connected to the liquid cavity through a liquid connecting pipeline and is used to control the injection of ignition agent into the liquid cavity.

[0016] Preferably, it also includes an exhaust port for evacuating the interior of the liquid carrier rocket engine multiple ignition system; the exhaust port includes a first exhaust port connected to the interior of the air cavity and a second exhaust port connected to the interior of the liquid cavity.

[0017] According to another aspect of the present application, a liquid carrier rocket engine ignition method is also provided, which utilizes the liquid carrier rocket engine multiple ignition system to ignite multiple liquid carrier rockets connected in parallel, comprising:

[0018] Vacuuming the system: Open the first and second air extraction ports, and evacuate the gas connection pipelines, liquid connection pipelines, and diaphragm tanks in the multiple ignition system of the liquid carrier rocket engine to ensure that the vacuum degree meets the requirements before the ignition agent is filled, and seal the first and second air extraction ports after the preset vacuum degree requirements are met;

[0019] Inflation of the gas storage device: Open the inflation valve connected to the inflation port, inflate the gas storage device through the gas source, and stop inflating after the pressure of the gas storage device meets the requirement, and seal the inflation port;

[0020] Ignition agent filling: open the ignition agent filling valve connected to the ignition agent filling port, fill the ignition agent into the liquid cavity of the diaphragm tank, stop filling after the ignition agent reaches a preset volume or weight, and seal the ignition agent filling port;

[0021] Ignition agent pressurized filling: The self-locking control valve is energized, and the pressurized gas in the gas storage device is reduced to the design pressure by the pressure reducing valve and then enters the gas cavity of the diaphragm tank and squeezes the ignition agent in the liquid cavity. The ignition agent is filled in front of the ignition control valve of each engine;

[0022] Engine ignition: Open the ignition control valve, and the ignition agent enters the engine's combustion device through the ignition control valve and the ignition check valve in turn, contacts with the oxidant and fuel, and realizes engine ignition. After successful ignition, close the ignition control valve.

[0023] Preferably, when the engines are ignited, the ignition of multiple engines is achieved by controlling the opening and closing of the ignition control valve corresponding to each engine arranged in parallel according to the ignition timing requirements of each extension.

[0024] Compared with the prior art, this application has at least the following beneficial effects:

[0025] 1. The present invention proposes a multiple ignition method for the first time in a multi-engine parallel liquid carrier rocket, which solves the problem that multiple engines cannot be ignited multiple times when multiple engines are connected in parallel. It can realize multiple ignitions of liquid carrier rocket engines in parallel, has a simple structure, is safe and convenient to operate, and has high ignition stability.

[0026] 2. The liquid carrier rocket engine multiple ignition system of the present invention adopts a unified constant pressure gas source to squeeze the ignition agent ignition scheme, which can ensure the consistency of ignition of multiple engines arranged in parallel.

[0027] 3. The liquid carrier rocket engine multiple ignition system of the present invention can be applied to the rocket recovery stage and can realize multiple ignitions of the recoverable carrier rocket engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Hereinafter, some specific embodiments of the present invention will be described in detail in an exemplary and non-limiting manner with reference to the accompanying drawings. The same reference numerals in the accompanying drawings indicate the same or similar components or parts. It should be understood by those skilled in the art that these drawings are not necessarily drawn to scale.

[0029] In the figure:

[0030] Figure 1 The system schematic diagram of the multiple ignition system of the liquid carrier rocket engine of the present invention.

[0031] The above drawings include the following reference numerals:

[0032] 1. Gas storage device; 2. Self-locking control valve; 3. Pressure reducing valve; 4. Diaphragm tank; 5. Ignition agent filling valve; 6. Inflating valve; 11. Ignition control valve; 12. Ignition non-return valve; 21. Liquid carrier rocket engine; 41. Air cavity; 42. Liquid cavity; 100. Inflating port; 200. Ignition agent filling port; 300. First air extraction port; 400. Second air extraction port. DETAILED DESCRIPTION

[0033] In order to make the purpose, technical solution and advantages of the present application clearer, the technical solution of the present application will be clearly and completely described below in combination with the specific embodiments of the present application and the corresponding drawings. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present application.

[0034] The present invention adopts a diaphragm tank to store ignition agent in the liquid cavity and supplies pressurized gas to the gas cavity of the diaphragm tank, so that the diaphragm tank supplies ignition agent to multiple liquid carrier rocket engines arranged in parallel, thereby realizing multiple ignitions of each liquid carrier rocket engine.

[0035] In addition, a self-locking control valve and a pressure reducing valve are used to control the pressurized gas entering the air cavity of the diaphragm tank, thereby ensuring the stability of the pressure supply to the air cavity of the diaphragm tank, ensuring that the pressure of the pressurized gas is constant, and the ignition agent flow is stable and controllable.

[0036] like Figure 1 As shown, a multiple ignition system of a liquid carrier rocket engine includes: a diaphragm tank 4, a plurality of liquid carrier rocket engines 21 and a plurality of ignition control valves 11.

[0037] The diaphragm tank 4 includes an air chamber 41 that can communicate with the gas storage device 1 and a liquid chamber 42 for storing ignition agent.

[0038] The plurality of liquid carrier rocket engines 21 can all be connected to the liquid chamber 42 , and the plurality of liquid carrier rocket engines 21 are arranged in parallel with each other.

[0039] The number of the ignition control valves 11 is the same as the number of the liquid carrier rocket engines 21, and they correspond one to one with the liquid carrier rocket engines 21. The ignition control valves 11 are arranged on the liquid connecting pipeline between the liquid carrier rocket engine 21 and the liquid cavity 42. The ignition control valves 11 are configured to control the ignition agent in the liquid cavity 42 to enter the corresponding liquid carrier rocket engine 21 through opening and closing thereof, so as to realize multiple ignitions of the corresponding liquid carrier rocket engine 21.

[0040] In this embodiment, the ignition agent is a mixture of triethylaluminum and triethylboron.

[0041] Preferably, the diaphragm tank 4 has an air cavity 41 at the top and a liquid cavity 42 at the bottom.

[0042] As another embodiment of the present invention, a multiple ignition system for a liquid carrier rocket engine further includes a plurality of ignition check valves 12 having the same number as the liquid carrier rocket engine 21; the ignition check valves 12 are arranged on the liquid connecting pipeline between the liquid carrier rocket engine 21 and the liquid chamber 42. Since the pressure in the combustion device in the liquid carrier rocket engine 21 is relatively high, the ignition check valves 12 can effectively prevent the gas in the combustion device from reversely entering the pipeline at the front end of the ignition control valve 11.

[0043] Preferably, the ignition check valve 12 is arranged on the liquid connecting pipeline between the outlet end of the ignition control valve 11 and the liquid carrier rocket engine 21.

[0044] Preferably, the gas storage device 1 is a pressurized gas cylinder, and the gas storage device 1 is connected to the gas cavity 41 through a gas connecting pipeline. The gas connecting pipeline is provided with a self-locking control valve 2 for controlling the gas in the gas storage device 1 to enter the gas cavity 41.

[0045] The self-locking control valve 2 is preferably a two-position, two-way solenoid valve whose on-off is controlled by electromagnetic force.

[0046] In addition, other gas storage devices capable of storing pressurized gas are also applicable to the present invention.

[0047] In an embodiment of the present invention, an inert gas is used as the pressurized gas, such as nitrogen or helium.

[0048] As another embodiment of the present invention, a multiple ignition system of a liquid carrier rocket engine further includes a pressure reducing valve 3 disposed on a gas connection pipeline between the gas outlet end of the self-locking control valve 2 and the inlet of the gas cavity 41. The pressure reducing valve 3 can reduce the pressure of the gas discharged from the gas storage device 1 to a preset constant pressure, so that the gas reduced to the preset pressure can enter the gas cavity 41, thereby achieving stable and effective squeezing of the ignition agent stored in the liquid cavity 42, thereby ensuring stable flow of the ignition agent.

[0049] As another embodiment of the present invention, a multiple ignition system for a liquid launch vehicle engine further includes a gas charging valve 6 connected to the gas cavity 41 through a gas connection pipeline and used to control the injection of gas into the gas storage device 1. The gas inlet end of the gas charging valve 6 is connected to the gas charging port 100, so that the gas in the gas source can enter the gas storage device 1 through the gas charging port 100 and the gas charging valve 6 in sequence.

[0050] As another embodiment of the present invention, a multiple ignition system for a liquid launch vehicle engine further includes an ignition agent filling valve 5 which is connected to the liquid cavity 42 through a liquid connecting pipeline and is used to control the injection of ignition agent into the liquid cavity 42. The inlet end of the ignition agent filling valve 5 is connected to the ignition agent filling port 200, and the outlet end is connected to the liquid cavity 42.

[0051] As another embodiment of the present invention, a multiple ignition system for a liquid carrier rocket engine further includes an air extraction port for evacuating the interior of the multiple ignition system for a liquid carrier rocket engine. The air extraction port includes a first air extraction port 300 connected to the interior of the gas cavity 41 and a second air extraction port 400 connected to the interior of the liquid cavity 42. Before the ignition agent is filled, the gas inside the gas cavity 41, the liquid cavity 42, and the gas connecting pipelines and liquid connecting pipelines in the system need to be discharged and reach a preset negative pressure to facilitate the filling of the ignition agent.

[0052] As another embodiment of the present invention, a liquid carrier rocket engine ignition method is also provided, which uses the liquid carrier rocket engine multiple ignition system to ignite multiple liquid carrier rockets connected in parallel, comprising:

[0053] Vacuuming the system: Open the first and second air extraction ports, and evacuate the gas connection pipelines, liquid connection pipelines, and diaphragm tanks in the multiple ignition system of the liquid carrier rocket engine to ensure that the vacuum degree meets the requirements before the ignition agent is filled, and seal the first and second air extraction ports after the preset vacuum degree requirements are met;

[0054] Inflation of the gas storage device: Open the inflation valve connected to the inflation port, inflate the gas storage device through the gas source, and stop inflating after the pressure of the gas storage device meets the requirement, and seal the inflation port;

[0055] Ignition agent filling: open the ignition agent filling valve connected to the ignition agent filling port, fill the ignition agent into the liquid cavity of the diaphragm tank, stop filling after the ignition agent reaches a preset volume or weight, and seal the ignition agent filling port;

[0056] Ignition agent pressurized filling: The self-locking control valve is energized, and the pressurized gas in the gas storage device is reduced to the design pressure by the pressure reducing valve and then enters the gas cavity of the diaphragm tank and squeezes the ignition agent in the liquid cavity. The ignition agent is filled in front of the ignition control valve of each engine;

[0057] Engine ignition: Open the ignition control valve, and the ignition agent enters the engine's combustion device through the ignition control valve and the ignition check valve in turn, contacts with the oxidant and fuel, and realizes engine ignition. After successful ignition, close the ignition control valve.

[0058] Preferably, when the engines are ignited, the ignition of multiple engines is achieved by controlling the opening and closing of the ignition control valve corresponding to each engine arranged in parallel according to the ignition timing requirements of each extension.

[0059] The technical solution of this embodiment has been successfully applied to multiple ignition tests of a carrier rocket engine, and the ignition reliability has been greatly improved, with an ignition success rate of 100%.

[0060] For ease of description, spatially relative terms such as "above", "above", "on the upper surface of", "above", etc. may be used here to describe the spatial positional relationship between a device or feature and other devices or features as shown in the figure. It should be understood that spatially relative terms are intended to include different orientations of the device in use or operation in addition to the orientation described in the figure. For example, if the device in the accompanying drawings is inverted, the device described as "above other devices or structures" or "above other devices or structures" will be positioned as "below other devices or structures" or "below other devices or structures". Thus, the exemplary term "above" can include both "above" and "below". The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatially relative descriptions used here are interpreted accordingly.

[0061] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof.

[0062] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the numbers used in this way can be interchanged where appropriate, so that the embodiments of the present application described herein can be implemented in an order other than those illustrated or described herein.

[0063] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A multiple ignition system for a liquid launch vehicle engine, characterized in that: include: a diaphragm storage tank; The diaphragm tank includes an air cavity that can communicate with the air storage device and a liquid cavity for storing ignition agent; multiple liquid launch vehicle engines; A plurality of the liquid carrier rocket engines are all capable of communicating with the liquid chamber, and a plurality of the liquid carrier rocket engines are arranged in parallel with each other; A plurality of ignition control valves; the number of the ignition control valves is the same as the number of the liquid carrier rocket engines, and corresponds one-to-one to the liquid carrier rocket engines; the ignition control valves are arranged on the liquid connecting pipeline between the liquid carrier rocket engine and the liquid cavity; The ignition control valve is configured to control the ignition agent in the liquid chamber to enter the corresponding liquid carrier rocket engine through its opening and closing, thereby achieving multiple ignitions of the corresponding liquid carrier rocket engine.

2. The liquid launch vehicle engine multiple ignition system according to claim 1, characterized in that: It also includes a plurality of ignition check valves, the number of which is the same as that of the liquid carrier rocket engine; the ignition check valves are arranged on the liquid connecting pipeline between the liquid carrier rocket engine and the liquid cavity.

3. The liquid launch vehicle engine multiple ignition system as claimed in claim 2, characterized in that: The ignition check valve is arranged on the liquid connecting pipeline between the outlet end of the ignition control valve and the liquid carrier rocket engine.

4. The liquid launch vehicle engine multiple ignition system as claimed in claim 3, characterized in that: The gas storage device is a pressurized gas cylinder; the gas storage device is connected to the gas cavity through a gas connecting pipeline; the gas connecting pipeline is provided with a self-locking control valve for controlling the gas in the gas storage device to enter the gas cavity.

5. The liquid launch vehicle engine multiple ignition system according to claim 4, characterized in that: It also includes a pressure reducing valve; the pressure reducing valve is arranged on the gas connecting pipeline between the gas outlet end of the self-locking control valve and the gas cavity inlet.

6. The liquid launch vehicle engine multiple ignition system according to claim 5, characterized in that: It also includes a gas filling valve which is connected to the gas cavity through a gas connecting pipeline and is used to control the injection of gas into the gas storage device.

7. The liquid launch vehicle engine multiple ignition system according to claim 6, characterized in that: It also includes an ignition agent filling valve which is connected to the liquid cavity through a liquid connecting pipeline and is used to control the injection of ignition agent into the liquid cavity.

8. The liquid launch vehicle engine multiple ignition system according to claim 7, characterized in that: It also includes an exhaust port for evacuating the interior of the liquid carrier rocket engine multiple ignition system; the exhaust port includes a first exhaust port connected to the interior of the air cavity and a second exhaust port connected to the interior of the liquid cavity.

9. A method for igniting a liquid launch vehicle engine, characterized in that: The liquid carrier rocket engine multiple ignition system of claim 8 is used to ignite multiple liquid carrier rockets connected in parallel, comprising: Vacuuming the system: Open the first and second air extraction ports, and evacuate the gas connection pipelines, liquid connection pipelines, and diaphragm tanks in the multiple ignition system of the liquid carrier rocket engine to ensure that the vacuum degree meets the requirements before the ignition agent is filled, and seal the first and second air extraction ports after the preset vacuum degree requirements are met; Inflation of the gas storage device: Open the inflation valve connected to the inflation port, inflate the gas storage device through the gas source, and stop inflating after the pressure of the gas storage device meets the requirement, and seal the inflation port; Ignition agent filling: open the ignition agent filling valve connected to the ignition agent filling port, fill the ignition agent into the liquid cavity of the diaphragm tank, stop filling after the ignition agent reaches a preset volume or weight, and seal the ignition agent filling port; Ignition agent pressurized filling: The self-locking control valve is energized, and the pressurized gas in the gas storage device is reduced to the design pressure by the pressure reducing valve and then enters the gas cavity of the diaphragm tank and squeezes the ignition agent in the liquid cavity. The ignition agent is filled in front of the ignition control valve of each engine; Engine ignition: Open the ignition control valve, and the ignition agent enters the engine's combustion device through the ignition control valve and the ignition check valve in turn, contacts with the oxidant and fuel, and realizes engine ignition. After successful ignition, close the ignition control valve.

10. The liquid launch vehicle engine ignition method according to claim 9, characterized in that: When the engine is ignited, according to the ignition timing requirements of each extension, the opening and closing of the ignition control valve corresponding to each engine arranged in parallel is controlled to realize the ignition of multiple engines.

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