CN112196702A - Liquid rocket engine starter and design method thereof - Google Patents
Liquid rocket engine starter and design method thereof Download PDFInfo
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- CN112196702A CN112196702A CN202011119645.9A CN202011119645A CN112196702A CN 112196702 A CN112196702 A CN 112196702A CN 202011119645 A CN202011119645 A CN 202011119645A CN 112196702 A CN112196702 A CN 112196702A
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- propellant
- gas generator
- pipeline
- storage tank
- starter
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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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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The invention relates to a liquid rocket engine starter and a design method thereof, wherein a propellant storage tank, an additional exhaust valve, an electromagnetic valve, a fuel gas generator and an igniter are arranged; the propellant storage tank stores nontoxic self-pressurization propellant, and the saturated vapor pressure of the medium is higher, so that the driving pressure can be provided for the propellant by utilizing the self pressure of the medium; the connecting pipeline of the storage tank and the electromagnetic valve is connected with a charging and discharging valve for charging and discharging non-toxic self-pressurizing medium, the electromagnetic valve is connected with the inlet of the fuel gas generator through a pipeline, the propellant is ignited to generate fuel gas, the fuel gas enters the downstream turbine shell at high speed and pushes the turbine to rotate, and the starting of the engine is realized. The invention adopts nitrous oxide based composite propellant, and has the advantages of green and non-toxic property, high saturated vapor pressure, high specific flushing, low use cost and easy maintenance. The starter has the advantages of simple structure, light weight, no toxicity or pollution, capability of being started for multiple times and repeated use.
Description
Technical Field
The invention relates to the technical field of liquid rockets, in particular to a liquid rocket engine starter and a design method thereof.
Background
With the rapid development of the aerospace industry, various technologies related to rockets also realize the rapid advance. The starter is an important component of the liquid rocket engine and provides initial power for starting the engine.
In the conventional liquid rocket engine starter, the solid starter cannot realize multiple starting, the gas starter has larger structural mass when used for multiple starting, and the liquid starter needs to provide a whole set of extrusion system and has a complex structure. And the solid starter and the liquid starter usually adopt toxic media, so that the requirements of green, environmental protection, no toxicity and no pollution of the rocket in the future are not met.
Existing starters typically require the introduction of pressurized gas, which necessarily requires the addition of fill interfaces, piping, corresponding valves, and pressure monitoring equipment. Resulting in a complex and bulky structure. How to provide a starter which has simple structure, can be started for a plurality of times, is nontoxic and pollution-free, meets the use requirements of the future liquid rocket engine, and is the problem to be solved at present.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides the liquid rocket engine starter and the design method thereof, which have the advantages of simple structure, light weight, no toxicity or pollution and capability of starting for multiple times, and can be widely applied to a liquid rocket engine system.
In order to achieve the above object, the present invention provides a liquid rocket engine starter, comprising a propellant storage tank, a gas generator, an igniter and a pipeline;
the propellant storage tank is used for storing nitrous oxide-based composite propellant; the inlet of the fuel gas generator is connected with the outlet of the propellant storage tank through the pipeline, and an igniter is arranged in the fuel gas generator;
when a pipeline valve is opened, the nitrous oxide based composite propellant enters the fuel gas generator through the pipeline under the action of the saturated vapor pressure of the nitrous oxide based composite propellant, and is ignited by the igniter to generate fuel gas; the combustion gases enter the downstream turbine housing from the outlet of the gas generator to effect starting of the engine.
Further, the propellant reservoir outlet is located at the bottom; the gasifier inlet is located at the top; and the propellant tank is located above the gas generator.
Furthermore, the pipeline is provided with an electromagnetic valve to control the nitrous oxide based composite propellant to enter the fuel gas generator, so as to control the startup and shutdown of the starter.
Further, the device also comprises a charging and discharging valve which is connected to the pipeline through a tee joint and is used for charging and discharging the nitrous oxide based composite propellant in the propellant storage tank.
Furthermore, the pipeline is made of stainless steel or titanium alloy.
In another aspect, the present invention provides a method for designing a starter for a liquid rocket engine, comprising the steps of:
(1) determining the sectional area of the pipeline according to the flow and the flow speed of the nitrous oxide based composite propellant;
(2) the propellant storage tank is provided with a unique outlet at the bottom, and is not provided with a separate inlet and a pressure sensor; the gas generator inlet is located at the top and the propellant tank is located above the gas generator; the distance between the propellant tank outlet and the gas generator inlet is equal to the conduit length;
(3) the igniter is arranged inside the fuel gas generator; the lower part of the gas generator is provided with an outlet which is connected to a downstream turbine shell;
(4) a tee joint connecting charge and discharge valve is arranged on the pipeline and is used for charging and discharging the nitrous oxide based composite propellant in the propellant storage tank; the pipeline is provided with an electromagnetic valve to control the nitrous oxide based composite propellant to enter the fuel gas generator, so as to control the start and stop of the starter.
Further, the cross-sectional area of the pipeline is flow rate; the flow rate is not more than 10 m/s.
The technical scheme of the invention has the following beneficial technical effects:
(1) the invention adopts nontoxic self-pressurization medium and nitrous oxide based composite propellant, has the advantages of green and innocuity, high saturated vapor pressure, high specific flushing, low use cost and easy maintenance, and can play the same role by adopting other nontoxic self-pressurization propellant.
(2) The storage tank and the propellant interface are arranged at the bottom of the storage tank, so that liquid propellant enters the fuel gas generator to be combusted to generate fuel gas, and the interface is arranged at the top of the fuel gas generator, so that gas propellant enters the fuel gas generator to be combusted to generate fuel gas, and the same fuel gas generating effect can be achieved.
(3) The filling valve is arranged on a connecting pipeline between the storage tank and the electromagnetic valve and can be connected through a tee joint, and the filling valve is arranged on the outer wall of the storage tank and can play the same filling and discharging role.
(4) The igniter adopts a spark plug structure for ignition, and adopts ignition devices such as a gunpowder igniter, a laser igniter, a plasma igniter and the like, so that the same ignition effect can be achieved.
(5) The liquid rocket engine starter has the advantages of simple structure, light weight, no toxicity or pollution, repeated starting and repeated use, is generally applied to a liquid rocket engine system, and is particularly suitable for the liquid rocket engine system which adopts green nontoxic propellant and is repeatedly started for multiple times.
(6) The propellant storage tank is only provided with a single outlet, and the propellant is injected through the discharge valve by utilizing the outlet; need not to set up other access & exit, need not to add pressurized gas, need not to set up pressure measurement, propellant storage tank simple structure. One outlet reduces the leakage link, and the method has high reliability and simple process.
Drawings
FIG. 1 is a schematic diagram of a liquid rocket engine starter according to an embodiment of the present invention:
in the figure: 1. a propellant storage tank; 2. a gaseous propellant; 3. a liquid propellant; 4. adding and discharging valves; 5. an electromagnetic valve; 6. an igniter; 7. a gas generator.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail with reference to the accompanying drawings in conjunction with the following detailed description. It should be understood that the description is intended to be exemplary only, and is not intended to limit the scope of the present invention. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not unnecessarily obscure the concepts of the present invention.
As shown in fig. 1, the present invention provides a liquid rocket engine starter comprising a propellant tank 1, a charge and discharge valve 4, a solenoid valve 5, a gas generator 7 and an igniter 6; the nontoxic nitrous oxide based composite propellant capable of self-pressurization is stored in the propellant storage tank 1, the gaseous propellant and the liquid propellant are simultaneously stored in the propellant storage tank 1, and the driving pressure can be provided for the propellant by utilizing the self pressure of the medium due to the high saturated vapor pressure of the medium. The liquid propellant 3 sinks below the storage tank 1, the gaseous propellant 2 floats above the storage tank 1, and due to the fact that the saturated vapor pressure of the propellant is high, the required driving pressure can be provided for the propellant by utilizing the self pressure of the medium, and a pressurizing device does not need to be carried additionally.
The outlet of the propellant storage tank 1 is connected with an electromagnetic valve 5 through a pipeline and is used for controlling the on-off control of a starter, and a charging and discharging valve 4 is arranged on a connecting pipeline of the propellant storage tank 1 and the electromagnetic valve 5 through a tee joint for charging and discharging the propellant. The electromagnetic valve 5 is connected with an inlet of a gas generator 7 through a pipeline, an igniter 6 is arranged on the gas generator 7 and used for igniting a medium when a starter is started, the gas generator 7 burns a propellant to generate gas, and the gas enters a downstream turbine shell from an outlet of the gas generator 7 at a high speed and pushes a turbine to rotate, so that the engine is started.
Furthermore, the pipeline is made of stainless steel or titanium alloy.
Furthermore, the propellant storage tank 1 is of a cylindrical surface structure or an ellipsoidal surface structure, and the inside of the propellant storage tank is a cavity without arranging parts such as an interlayer, a valve and the like.
The invention also provides a design method of the liquid rocket engine starter, which comprises the following steps:
(1) determining the sectional area of the pipeline according to the flow and the flow speed of the nitrous oxide based composite propellant; cross-sectional area is flow/velocity; the flow velocity is not more than 10 m/s; (ii) a
(2) The propellant storage tank 1 is provided with a unique outlet at the bottom, and the propellant storage tank 1 is not provided with a separate inlet and a pressure sensor; the gas generator 7 inlet is located at the top and the propellant tank 1 is located above the gas generator 7; the distance between the outlet of the propellant tank 1 and the inlet of the gas generator 7 is equal to the length of the pipeline;
(3) the igniter 6 is arranged inside the fuel gas generator 7; the lower part of the gas generator 7 is an outlet which is connected to a downstream turbine shell;
(4) a tee joint is arranged on the pipeline and is connected with a charging and discharging valve 4 for charging and discharging the nitrous oxide based composite propellant in the propellant storage tank 1; the pipeline is provided with an electromagnetic valve 5 to control the nitrous oxide based composite propellant to enter the fuel gas generator 7, so as to control the startup and shutdown of the starter.
In summary, the invention relates to a liquid rocket engine starter and a design method thereof, which is provided with a propellant storage tank, an additional exhaust valve, an electromagnetic valve, a fuel gas generator and an igniter; the propellant storage tank stores nontoxic self-pressurization propellant, and the saturated vapor pressure of the medium is higher, so that the driving pressure can be provided for the propellant by utilizing the self pressure of the medium; the connecting pipeline of the storage tank and the electromagnetic valve is connected with a charging and discharging valve for charging and discharging non-toxic self-pressurizing medium, the electromagnetic valve is connected with the inlet of the fuel gas generator through a pipeline, the propellant is ignited to generate fuel gas, the fuel gas enters the downstream turbine shell at high speed and pushes the turbine to rotate, and the starting of the engine is realized. The invention adopts nitrous oxide based composite propellant, and has the advantages of green and non-toxic property, high saturated vapor pressure, high specific flushing, low use cost and easy maintenance. The starter has the advantages of simple structure, light weight, no toxicity or pollution, capability of being started for multiple times and repeated use.
It is to be understood that the above-described embodiments of the present invention are merely illustrative of or explaining the principles of the invention and are not to be construed as limiting the invention. Therefore, any modification, equivalent replacement, improvement and the like made without departing from the spirit and scope of the present invention should be included in the protection scope of the present invention. Further, it is intended that the appended claims cover all such variations and modifications as fall within the scope and boundaries of the appended claims or the equivalents of such scope and boundaries.
Claims (7)
1. A liquid rocket engine starter is characterized by comprising a propellant storage tank (1), a fuel gas generator (7), an igniter (6) and a pipeline;
the propellant storage tank (1) is used for storing nitrous oxide-based composite propellant; the inlet of the gas generator (7) is connected with the outlet of the propellant storage tank (1) through the pipeline, and an igniter (6) is arranged in the gas generator (7);
when a pipeline valve is opened, the nitrous oxide based composite propellant enters the gas generator (7) through the pipeline under the action of the self saturated vapor pressure, and is ignited by the igniter (6) to generate gas; the gas enters the downstream turbine housing from the outlet of the gas generator (7) to effect the starting of the engine.
2. The liquid rocket engine starter according to claim 1, wherein the propellant tank (1) outlet is located at the bottom; the gas generator (7) inlet is positioned at the top; and the propellant tank (1) is located above the gas generator (7).
3. The starter of a liquid rocket engine according to claim 1 or 2, wherein said circuit is provided with a solenoid valve (5) for controlling the introduction of nitrous oxide based composite propellant into said gas generator (7) and thus the start-up and shut-down of the starter.
4. The liquid rocket engine starter according to claim 1 or 2, further comprising a charge and discharge valve (4) connected to said piping by a tee for charging and discharging said propellant tank (1) with nitrous oxide based composite propellant.
5. The starter for a liquid rocket engine according to claim 1 or 2, wherein the material of said tube is stainless steel or titanium alloy.
6. Method of designing a starter for a liquid rocket engine according to one of claims 1 to 5, characterized in that it comprises the following steps:
(1) determining the sectional area of the pipeline according to the flow and the flow speed of the nitrous oxide based composite propellant;
(2) the propellant storage tank (1) is provided with a unique outlet at the bottom, and the propellant storage tank (1) is not provided with a separate inlet and a pressure sensor; the gas generator (7) inlet is located at the top and the propellant tank (1) is located above the gas generator (7); the distance between the outlet of the propellant tank (1) and the inlet of the gas generator (7) is equal to the length of the pipeline;
(3) the igniter (6) is arranged in the fuel gas generator (7); the lower part of the gas generator (7) is an outlet and is connected to a downstream turbine shell;
(4) a tee joint charging and discharging valve (4) is arranged on the pipeline and is used for charging and discharging the nitrous oxide based composite propellant in the propellant storage tank (1); the pipeline is provided with an electromagnetic valve (5) for controlling the nitrous oxide based composite propellant to enter the fuel gas generator (7) so as to control the startup and shutdown of the starter.
7. The design method according to claim 6, wherein the cross-sectional area of the pipeline is flow rate; the flow rate is not more than 10 m/s.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011119645.9A CN112196702B (en) | 2020-10-19 | 2020-10-19 | Liquid rocket engine starter and design method thereof |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011119645.9A CN112196702B (en) | 2020-10-19 | 2020-10-19 | Liquid rocket engine starter and design method thereof |
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| Publication Number | Publication Date |
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| CN112196702A true CN112196702A (en) | 2021-01-08 |
| CN112196702B CN112196702B (en) | 2022-01-04 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011119645.9A Active CN112196702B (en) | 2020-10-19 | 2020-10-19 | Liquid rocket engine starter and design method thereof |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2815981C2 (en) * | 2023-01-20 | 2024-03-25 | Валентин Павлович Рылов | Method of starting propulsion system with pump system for feeding powder metal into liquid-propellant engine combustion chamber |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6226980B1 (en) * | 1999-01-21 | 2001-05-08 | Otkrytoe Aktsionernoe Obschestvo Nauchno-Proizvodstvennoe Obiedinenie “Energomash” Imeni Akademika V.P. Glushko | Liquid-propellant rocket engine with turbine gas afterburning |
| US20160377028A1 (en) * | 2013-05-07 | 2016-12-29 | Reaction Systems, Llc | Catalytic n2o pilot ignition system for upper stage scramjets |
| CN106939850A (en) * | 2017-03-09 | 2017-07-11 | 上海空间推进研究所 | Monopropellant engine anti-backfire injection device |
| CN108019296A (en) * | 2017-12-07 | 2018-05-11 | 上海新力动力设备研究所 | A kind of nitrous oxide is from pressure charging system |
| CN109372655A (en) * | 2018-12-13 | 2019-02-22 | 西安航天动力研究所 | The pre- pressure charging system of gas-liquid parallel drive and method that high-altitude low entry pressure starts |
| CN111156101A (en) * | 2020-03-26 | 2020-05-15 | 北京宇航推进科技有限公司 | Nitrous oxide power system |
| CN111734554A (en) * | 2020-08-17 | 2020-10-02 | 北京航空航天大学 | Regeneration heat compensation system and method for realizing self-pressurization stable supply of nitrous oxide |
-
2020
- 2020-10-19 CN CN202011119645.9A patent/CN112196702B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6226980B1 (en) * | 1999-01-21 | 2001-05-08 | Otkrytoe Aktsionernoe Obschestvo Nauchno-Proizvodstvennoe Obiedinenie “Energomash” Imeni Akademika V.P. Glushko | Liquid-propellant rocket engine with turbine gas afterburning |
| US20160377028A1 (en) * | 2013-05-07 | 2016-12-29 | Reaction Systems, Llc | Catalytic n2o pilot ignition system for upper stage scramjets |
| CN106939850A (en) * | 2017-03-09 | 2017-07-11 | 上海空间推进研究所 | Monopropellant engine anti-backfire injection device |
| CN108019296A (en) * | 2017-12-07 | 2018-05-11 | 上海新力动力设备研究所 | A kind of nitrous oxide is from pressure charging system |
| CN109372655A (en) * | 2018-12-13 | 2019-02-22 | 西安航天动力研究所 | The pre- pressure charging system of gas-liquid parallel drive and method that high-altitude low entry pressure starts |
| CN111156101A (en) * | 2020-03-26 | 2020-05-15 | 北京宇航推进科技有限公司 | Nitrous oxide power system |
| CN111734554A (en) * | 2020-08-17 | 2020-10-02 | 北京航空航天大学 | Regeneration heat compensation system and method for realizing self-pressurization stable supply of nitrous oxide |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2815981C2 (en) * | 2023-01-20 | 2024-03-25 | Валентин Павлович Рылов | Method of starting propulsion system with pump system for feeding powder metal into liquid-propellant engine combustion chamber |
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| Publication number | Publication date |
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| CN112196702B (en) | 2022-01-04 |
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