CN111963340A - Multi-starting system of pneumatic supercharging device of liquid rocket engine - Google Patents
Multi-starting system of pneumatic supercharging device of liquid rocket engine Download PDFInfo
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- CN111963340A CN111963340A CN202010773472.6A CN202010773472A CN111963340A CN 111963340 A CN111963340 A CN 111963340A CN 202010773472 A CN202010773472 A CN 202010773472A CN 111963340 A CN111963340 A CN 111963340A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/46—Feeding propellants using pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/50—Feeding propellants using pressurised fluid to pressurise the propellants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
Abstract
The invention relates to a multiple starting system of a pneumatic supercharging device of a liquid rocket engine, belonging to the field of pump pressure type liquid rocket engine starting system design; the system comprises 2 pneumatic supercharging devices, a supercharging air source, a fuel gas generator, 2 turbopumps, 2 control valves and 2 upward one-way valves; 2 pneumatic supercharging devices are respectively communicated with a supercharging air source; each pneumatic supercharging device is respectively communicated with one end of 1 control valve and one end of 1 upward one-way valve; the other ends of the 2 control valves are communicated with the fuel gas generator; the other end of each upward one-way valve is communicated with 1 turbine pump; the 2 turbopumps are all communicated with an exhaust pipeline of the gas generator; supplying an oxidant to 1 of the pneumatic booster devices and the corresponding turbopumps; respectively supplying fuel to the other 1 pneumatic supercharging device and the corresponding turbine pump; the multi-starting system of the pneumatic supercharging device has the advantages of simple system, light structural weight, high working efficiency, good consistency of starting working conditions of each time and low gas consumption.
Description
Technical Field
The invention belongs to the field of pump pressure type liquid rocket engine starting system design, and relates to a multiple starting system of a pneumatic supercharging device of a liquid rocket engine.
Background
In order to meet the requirements of space navigation launching tasks such as multi-satellite launching, deep space exploration and rail service technologies, the upper-level main engine needs to have the multiple-starting capability of more than 20 times. Meanwhile, in order to reduce the structural mass as much as possible and improve the carrying capacity of the upper stage, a multi-start system of the main engine needs to share a pressurized air source with the attitude control engine.
At present, domestic pump type liquid rocket engines are generally started by using powder starters and used for executing the task of one-time starting or two-time starting, more than 20 powder starters are required to be arranged if more than 20 times of starting are required, and the system is complex, the structural mass is large, and the reliability is poor.
In addition, in the development of a certain multi-start upper-level engine, in order to realize the multi-start working capacity of more than 20 times, a starting box type multi-start system is provided, the system can realize the multi-start of the engine through the repeated filling of a starting box, but in the starting mode, the repeated filling of the starting box is required, so that the starting acceleration of the engine is slow, and meanwhile, the pressure of the starting box is sensitive to the ambient temperature, so that the consistency of each start is poor.
Disclosure of Invention
The technical problem solved by the invention is as follows: the system overcomes the defects of the prior art, provides the multiple starting system of the pneumatic supercharging device of the liquid rocket engine, and has the advantages of simple system, light structure mass, high working efficiency, good consistency of each starting working condition and low gas consumption.
The technical scheme of the invention is as follows:
a liquid rocket engine pneumatic supercharging device multi-start system comprises 2 pneumatic supercharging devices, a supercharging gas source, a gas generator, 2 turbopumps, 2 control valves and 2 upward one-way valves; wherein, the pressurizing air source is arranged at the central position; the 2 pneumatic supercharging devices are symmetrically arranged at two sides of a supercharging air source; and 2 pneumatic supercharging devices are respectively communicated with a supercharging air source; each pneumatic supercharging device is respectively communicated with one end of 1 control valve and one end of 1 upward one-way valve; the other ends of the 2 control valves are communicated with the fuel gas generator; the other end of each upward one-way valve is communicated with 1 turbine pump; the 2 turbopumps are symmetrically arranged; and 2 turbopumps are all communicated with an exhaust pipeline of the gas generator; the external oxidant storage tank supplies oxidant to 1 pneumatic supercharging device and the corresponding turbopump; the external fuel tank supplies fuel to the other 1 pneumatic booster and the corresponding turbo pump, respectively.
In the above multiple-start system of the pneumatic booster device of the liquid rocket engine, the pneumatic booster device comprises a booster pump and a downward check valve; the inlet end of the booster pump is communicated with a booster air source; the outlet end of the booster pump is communicated with the inlet end of the downward one-way valve; the outlet end of the downward check valve is respectively communicated with the corresponding control valve and the upward check valve.
In the above multiple starting system for the pneumatic supercharging device of the liquid rocket engine, the working process of the starting system is as follows:
starting the control valve to realize the communication of the passage between the pneumatic supercharging device and the gas generator; the booster gas source provides high-pressure gas for the 2 booster pumps; the external oxidant storage tank supplies low-pressure oxidant to 1 booster pump in the external oxidant storage tank; the low-pressure oxidant flows into the inlet of the corresponding downward one-way valve after the pressurization of the high-pressure gas and the booster pump, the corresponding downward one-way valve is opened through the high-pressure oxidant, and the high-pressure oxidant flows into the fuel gas generator through the outlet of the corresponding downward one-way valve; meanwhile, the external fuel storage tank supplies low-pressure fuel to the other 1 booster pump; the low-pressure fuel flows into the inlet of the corresponding downward one-way valve after the pressurization of the high-pressure gas and the booster pump, the corresponding downward one-way valve is opened through the high-pressure fuel, and the high-pressure fuel flows into the gas generator through the outlet of the corresponding downward one-way valve; igniting the gas generator, and enabling the rocket engine to enter an initial starting state; the gas generator generates high-temperature gas to drive 2 turbopumps to start;
2 turbo pumps continuously pressurize until the outlet end pressure of the turbo pump is greater than the outlet end pressure of the booster pump, and 2 downward check valves are closed; the external oxidant storage tank inputs oxidant to the corresponding turbine pump, and the oxidant enters the fuel gas generator through the corresponding upward one-way valve and the control valve in sequence after being pressurized by the turbine pump; meanwhile, the external fuel storage tank inputs fuel to the corresponding turbine pump, and the fuel enters the fuel gas generator through the corresponding upward one-way valve and the control valve in sequence after being pressurized by the turbine pump; the stable combustion in the fuel gas generator is realized, and the rocket engine enters a stable starting state.
In the multi-starting system of the pneumatic supercharging device of the liquid rocket engine, the initial pressure of the low-pressure oxidant is 0.3-0.4 Mpa; the pressure of the low-pressure oxidant is increased to 3-4MPa after the high-pressure gas and the booster pump are pressurized; the initial pressure of the low-pressure fuel is 0.3-0.4 Mpa; the pressure of the low-pressure fuel is increased to 3-4MPa after the high-pressure gas and the boosting action of the booster pump.
In the above-described multiple start system of the pneumatic booster device for a liquid rocket engine, the upward check valve realizes prevention of the oxidizer and the fuel outputted from the pneumatic booster device from entering the turbo pump.
In the above-described multiple start system of the pneumatic booster device for a liquid rocket engine, the downward check valve realizes a function of preventing the oxidizer and the fuel outputted from the turbo pump from returning to the pipe where the pneumatic booster device is located.
In the multiple-starting system of the pneumatic supercharging device of the liquid rocket engine, when high-pressure gas is left in a supercharging gas source, multiple stable combustion ignition of the multiple gas generator can be realized, and multiple starting of the rocket engine can be realized.
In the multiple-starting system of the pneumatic supercharging device of the liquid rocket engine, the stable starting times of the rocket engine are not less than 20 times for the high-pressure gas stored in the supercharging gas source.
Compared with the prior art, the invention has the beneficial effects that:
(1) the invention adopts a pneumatic supercharging device to supercharge the low-pressure propellant at the inlet of the engine under the action of supercharging starting, and supplies the low-pressure propellant to a fuel gas generator to provide the initial energy required by the starting of the engine; and a pneumatic pressurization mode is adopted, so that the structure is simple, the pressurization efficiency is high, and the air consumption is low.
(2) The initial working medium adopted by the engine starting is the same as the working medium adopted by the steady-state work, and is both the oxidant and the fuel provided by the external storage tank, the system is simple, the structural mass is light, the working efficiency is high, and the consistency of the working conditions of each starting is good;
(3) the output characteristic consistency of the pneumatic supercharging device in the multi-starting process of the engine is good, and the working consistency of each starting of the engine is improved. The liquid rocket engine pneumatic supercharging device is adopted to carry out multiple starting by the multiple starting system, so that the reliability of the multiple starting of the engine can be improved, and the task adaptability of the engine is expanded;
(4) in the starting process of the engine, when the pressure after the pump is higher than the outlet pressure of the pneumatic supercharging device, the pneumatic supercharging device automatically stops working, a special valve is not required to be arranged for closing the pneumatic supercharging device, the mode that the pneumatic supercharging device supplies the gas generator to work is directly used for supplying the mode transition stage of the gas generator to the turbine pump when the engine is started, and the control is simple;
(5) according to the invention, when the pressure behind the turbo pump 4 is higher than the outlet pressure of the pneumatic supercharging device 1, the pneumatic supercharging device 1 automatically stops working, a special valve is not required to be arranged for closing the pneumatic supercharging device 1, the engine is started, the mode of supplying the gas generator 3 to the turbo pump 4 can be directly supplied with the working mode of the gas generator 3 by the pneumatic supercharging device 1, and the control is simple
Drawings
FIG. 1 is a schematic diagram of a multiple start system of the present invention.
Detailed Description
The invention is further illustrated by the following examples.
In order to realize the multiple starting capability of more than 20 times and ensure that the engine has better starting acceleration and multiple starting consistency, the invention provides a multiple starting system of a pneumatic supercharging device, and the multiple starting system has the characteristics of simple system, light structural mass, high working efficiency, good consistency of starting working conditions of each time, small air consumption and the like.
The technical solution of the invention is as follows: the pneumatic supercharging device 1 supercharges low-pressure propellant at the inlet of the engine under the action of the supercharged gas provided by the supercharged gas source 2, the low-pressure propellant is supplied to the gas generator 3 for ignition, high-temperature fuel gas generated by the gas generator 3 drives the turbine pump 4 to start, when the pressure behind the turbine pump 4 is higher than the pressure at the outlet of the pneumatic supercharging device 1, the pneumatic supercharging device 1 stops working, the turbine pump 4 supplies the gas generator 3 for working, and the working condition of the engine continues to rise until the working condition of a steady state.
The multiple starting system mainly comprises 2 pneumatic supercharging devices 1, a supercharging air source 2, a gas generator 3, 2 turbopumps 4, 2 control valves 5 and 2 upward check valves 6 as shown in figure 1; wherein, the pressurized gas source 2 is arranged at the center; the 2 pneumatic supercharging devices 1 are symmetrically arranged at two sides of the supercharging air source 2; and 2 pneumatic supercharging devices 1 are respectively communicated with a supercharging gas source 2; each pneumatic supercharging device 1 is respectively communicated with one end of 1 control valve 5 and one end of 1 upward one-way valve 6; the other ends of the 2 control valves 5 are communicated with the gas generator 3; the other end of each upward one-way valve 6 is communicated with 1 turbine pump 4; the 2 turbo pumps 4 are symmetrically arranged; and 2 turbopumps 4 are all communicated with an exhaust pipeline of the gas generator 3; the external oxidant storage tank respectively supplies oxidant to 1 pneumatic supercharging device 1 and the corresponding turbopump 4; the external fuel tank supplies fuel to the other 1 pneumatic booster devices 1 and the corresponding turbo pumps 4, respectively.
Wherein, the pneumatic booster device 1 comprises a booster pump 11 and a downward check valve 12; the inlet end of the booster pump 11 is communicated with a booster air source 2; the outlet end of the booster pump 11 is communicated with the inlet end of the downward check valve 12; the outlet ends of the downward check valves 12 are respectively communicated with the corresponding control valves 5 and the upward check valves 6.
The working process of the starting system is as follows:
starting the control valve 5 to realize the communication between the pneumatic supercharging device 1 and the gas generator 3; the booster gas source 2 provides high-pressure gas for 2 booster pumps 11; the external oxidant reservoir supplies low pressure oxidant to 1 of the booster pumps 11; the low-pressure oxidant flows into the inlet of the corresponding downward check valve 12 after the pressurization of the high-pressure gas and the booster pump 11, and the initial pressure of the low-pressure oxidant is 0.3-0.4 Mpa; the pressure of the low-pressure oxidant is increased to 3-4MPa after the pressurization of the high-pressure gas and the booster pump 11. The corresponding downward check valve 12 is opened by the high-pressure oxidant, and the high-pressure oxidant flows into the gas generator 3 through the outlet of the corresponding downward check valve 12; while the external fuel reservoir supplies low pressure fuel to the other 1 booster pump 11; the low-pressure fuel flows into the inlet of the corresponding downward check valve 12 after the pressurization of the high-pressure gas and the booster pump 11, and the initial pressure of the low-pressure fuel is 0.3-0.4 Mpa; the pressure of the low-pressure fuel is increased to 3-4MPa after the high-pressure gas and the pressurization effect of the booster pump 11. The corresponding downward check valve 12 is opened by the high-pressure fuel, and the high-pressure fuel flows into the gas generator 3 through the outlet of the corresponding downward check valve 12; the downward check valve 12 realizes a line that prevents the oxidant and the fuel output from the turbo pump 4 from returning to the pneumatic booster device 1. Igniting the gas generator 3, and enabling the rocket engine to enter an initial starting state; the gas generator 3 generates high-temperature gas to drive 2 turbopumps 4 to start;
2 turbo pumps 4 continuously pressurize until the pressure at the outlet end of the turbo pumps 4 is greater than the pressure at the outlet end of the booster pump 11, and 2 downward one-way valves 12 are closed; the external oxidant storage tank inputs oxidant to the corresponding turbopump 4, and the oxidant enters the fuel gas generator 3 through the corresponding upward one-way valve 6 and the control valve 5 in sequence after being pressurized by the turbopump 4; meanwhile, the external fuel storage tank inputs fuel to the corresponding turbine pump 4, and the fuel enters the fuel gas generator 3 through the corresponding upward one-way valve 6 and the control valve 5 in sequence after being pressurized by the turbine pump 4; the upward check valve 6 achieves prevention of the oxidizer and fuel output from the pneumatic booster device 1 from entering the turbo pump 4. Stable combustion inside the gas generator 3 is realized, and the rocket engine enters a stable starting state.
When high-pressure gas is left in the pressurized gas source 2, multiple stable combustion ignition of the multiple gas generator 3 can be realized, and multiple starting of the rocket engine can be realized. The number of times of stable starting of the rocket engine by the high-pressure gas stored in the pressurized gas source 2 is not less than 20.
After an engine starting signal is sent out, the pneumatic supercharging device 1 supercharges low-pressure propellant at the inlet of the engine under the action of supercharging starting, supplies the low-pressure propellant to the fuel gas generator 3 and provides initial energy required by the starting of the engine; the pressurized gas source 2 is used for storing and supplying pressurized gas required by the work of the pneumatic pressurizing device 1; the fuel gas generator 3 is used for burning the propellant and generating high-temperature fuel gas to provide a power source for the turbopump 4; the turbo pump 4 is used for converting the heat energy of the high-temperature gas generated by the gas generator 3 into mechanical energy, pressurizing the propellant at the inlet of the engine and supplying high-pressure propellant for the thrust chamber and the gas generator; the starting control valve is used for controlling the starting and the shutdown of the engine.
In the starting process of the engine, the initial working medium adopted for starting the engine is the same as the working adopted for steady-state working, and is the engine inlet propellant, and components for storing the starting working medium, such as a gunpowder starter or a storage tank specially used for starting the engine, and the like do not need to be arranged independently.
When the engine is started, the low-pressure propellant at the inlet of the engine is pressurized by the pneumatic pressurizing device 1 and then is converted into the high-pressure propellant to be supplied to the gas generator 3, so that the power of the gas generator 3 is improved, and the sufficient gas generated by the gas generator 3 can be ensured to drive the turbopump 4 to start. Meanwhile, the propellant pressure supplied by the pneumatic pressurization device 1 to the gas generator 3 is determined by the inlet propellant pressure and the pressurization gas pressure, and under the condition that the inlet propellant pressure and the pressurization gas pressure are stable, the propellant pressure supplied by the pneumatic pressurization device 1 to the gas generator 3 is also consistent, so that the consistency of starting of the engine at each time can be ensured.
In the starting process of the engine, when the back pressure of the turbine pump 4 is higher than the outlet pressure of the pneumatic supercharging device 1, the pneumatic supercharging device 1 automatically stops working, a special valve is not required to be arranged for closing the pneumatic supercharging device 1, the mode of supplying the gas generator 3 to the turbine pump 4 in the mode of directly supplying the gas generator 3 to work by the pneumatic supercharging device 1 is changed, and the control is simple.
Compared with the prior art, the invention has the following advantages: the invention adopts a pneumatic pressurization mode, so the structure is simple, the pressurization efficiency is high, and the air consumption is low; the transition of the starting process of the engine can be automatically realized, and the control time sequence is simple; the output characteristic consistency of the pneumatic supercharging device in the process of starting the engine for multiple times is good, and the working consistency of starting the engine for each time is improved. The liquid rocket engine pneumatic supercharging device is adopted to carry out multiple starting by the multiple starting system, so that the reliability of the multiple starting of the engine can be improved, and the task adaptability of the engine can be expanded.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (8)
1. A liquid rocket engine pneumatic supercharging device system that starts many times which characterized in that: the device comprises 2 pneumatic supercharging devices (1), a supercharging air source (2), a fuel gas generator (3), 2 turbopumps (4), 2 control valves (5) and 2 upward one-way valves (6); wherein, the pressurizing air source (2) is arranged at the center; the 2 pneumatic supercharging devices (1) are symmetrically arranged at two sides of the supercharging air source (2); and the 2 pneumatic supercharging devices (1) are respectively communicated with a supercharging air source (2); each pneumatic supercharging device (1) is respectively communicated with one end of 1 control valve (5) and one end of 1 upward one-way valve (6); the other ends of the 2 control valves (5) are communicated with the gas generator (3); the other end of each upward one-way valve (6) is communicated with 1 turbine pump (4); the 2 turbine pumps (4) are symmetrically arranged; and the 2 turbopumps (4) are all communicated with an exhaust pipeline of the gas generator (3); the external oxidant storage tank supplies oxidant to 1 pneumatic supercharging device (1) and a corresponding turbopump (4) respectively; the external fuel storage tank supplies fuel to the other 1 pneumatic booster devices (1) and the corresponding turbo pumps (4) respectively.
2. The multiple start system for the pneumatic booster of a liquid rocket engine according to claim 1, wherein: the pneumatic supercharging device (1) comprises a booster pump (11) and a downward one-way valve (12); the inlet end of the booster pump (11) is communicated with a booster air source (2); the outlet end of the booster pump (11) is communicated with the inlet end of the downward one-way valve (12); the outlet end of the downward check valve (12) is respectively communicated with the corresponding control valve (5) and the upward check valve (6).
3. A multiple start system for a liquid rocket engine pneumatic booster device according to any one of claims 1-2, wherein: the working process of the starting system is as follows:
starting a control valve (5) to realize the communication of a passage between the pneumatic supercharging device (1) and the gas generator (3); the booster gas source (2) provides high-pressure gas for 2 booster pumps (11); an external oxidant storage tank supplies low-pressure oxidant to 1 booster pump (11) in the external oxidant storage tank; the low-pressure oxidant flows into the inlet of the corresponding downward one-way valve (12) after the high-pressure gas and the pressurization effect of the booster pump (11), the corresponding downward one-way valve (12) is opened through the high-pressure oxidant, and the high-pressure oxidant flows into the gas generator (3) through the outlet of the corresponding downward one-way valve (12); simultaneously, the external fuel storage tank supplies low-pressure fuel to the other 1 booster pump (11); the low-pressure fuel flows into the inlet of the corresponding downward one-way valve (12) after the high-pressure gas and the pressurization effect of the booster pump (11), the corresponding downward one-way valve (12) is opened by the high-pressure fuel, and the high-pressure fuel flows into the gas generator (3) through the outlet of the corresponding downward one-way valve (12); igniting the gas generator (3), and enabling the rocket engine to enter an initial starting state; the fuel gas generator (3) generates high-temperature fuel gas to drive 2 turbopumps (4) to start;
2 turbo pumps (4) are continuously pressurized until the pressure of the outlet end of the turbo pump (4) is greater than the pressure of the outlet end of the booster pump (11), and 2 downward one-way valves (12) are closed; an external oxidant storage tank inputs oxidant to a corresponding turbine pump (4), and the oxidant is pressurized by the turbine pump (4) and then sequentially enters a fuel gas generator (3) through a corresponding upward one-way valve (6) and a control valve (5); meanwhile, the external fuel storage tank inputs fuel to the corresponding turbine pump (4), and the fuel enters the fuel gas generator (3) through the corresponding upward one-way valve (6) and the control valve (5) in sequence after being pressurized by the turbine pump (4); the stable combustion in the fuel gas generator (3) is realized, and the rocket engine enters a stable starting state.
4. A multiple start system for a pneumatic booster device of a liquid rocket engine as defined in claim 3, wherein: the initial pressure of the low-pressure oxidant is 0.3-0.4 Mpa; the pressure of the low-pressure oxidant is increased to 3-4MPa after the high-pressure gas and the booster pump (11) are pressurized; the initial pressure of the low-pressure fuel is 0.3-0.4 Mpa; the pressure of the low-pressure fuel is increased to 3-4MPa after the high-pressure gas and the boosting action of the booster pump (11).
5. The multiple start system for the pneumatic booster of a liquid rocket engine according to claim 4, wherein: the upward check valve (6) achieves prevention of the oxidizer and fuel output from the pneumatic booster device (1) from entering the turbo pump (4).
6. The multiple start system for the pneumatic booster of a liquid rocket engine according to claim 5, wherein: the downward check valve (12) realizes a pipeline for preventing the oxidant and the fuel output from the turbine pump (4) from returning to the pneumatic booster device (1).
7. The multiple start system for the pneumatic booster of a liquid rocket engine according to claim 6, wherein: when high-pressure gas is left in the pressurized gas source (2), multiple stable combustion ignition of the multiple gas generator (3) can be realized, and multiple starting of the rocket engine can be realized.
8. The multiple start system for the pneumatic booster of a liquid rocket engine according to claim 7, wherein: the number of times of stable starting of the rocket engine by the high-pressure gas stored in the pressurized gas source (2) is not less than 20.
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| CN112901373A (en) * | 2021-03-17 | 2021-06-04 | 唐虎 | Novel liquid rocket engine multi-machine system |
| CN114408222A (en) * | 2021-12-20 | 2022-04-29 | 上海空间推进研究所 | Pneumatic supercharged engine system |
| GB2605586A (en) * | 2021-04-01 | 2022-10-12 | Thistle Rocketry Ltd | A pumping apparatus |
| CN115265273A (en) * | 2022-08-17 | 2022-11-01 | 成都众怡光电科技有限公司 | Remote automatic blasting ultrahigh-pressure pulse generation system |
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| CN204344305U (en) * | 2014-12-16 | 2015-05-20 | 中国航天科技集团公司第六研究院第十一研究所 | Shutdown pilot system before a kind of one push start turbopump-fed liquid rocket engine pump |
| CN110748437A (en) * | 2019-09-20 | 2020-02-04 | 上海宇航系统工程研究所 | Propellant conveying system |
| CN110761902A (en) * | 2019-11-05 | 2020-02-07 | 西安中科宇航动力技术有限公司 | Self-pressurization power system of electric pump |
| CN211082076U (en) * | 2020-06-09 | 2020-07-24 | 西安空天引擎科技有限公司 | Pump pressure type engine started by blowing |
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| CN112901373A (en) * | 2021-03-17 | 2021-06-04 | 唐虎 | Novel liquid rocket engine multi-machine system |
| GB2605586A (en) * | 2021-04-01 | 2022-10-12 | Thistle Rocketry Ltd | A pumping apparatus |
| CN114408222A (en) * | 2021-12-20 | 2022-04-29 | 上海空间推进研究所 | Pneumatic supercharged engine system |
| CN115265273A (en) * | 2022-08-17 | 2022-11-01 | 成都众怡光电科技有限公司 | Remote automatic blasting ultrahigh-pressure pulse generation system |
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