CN109736971B - Electric pump pressure type liquid rocket engine - Google Patents
Electric pump pressure type liquid rocket engine Download PDFInfo
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- CN109736971B CN109736971B CN201811527024.7A CN201811527024A CN109736971B CN 109736971 B CN109736971 B CN 109736971B CN 201811527024 A CN201811527024 A CN 201811527024A CN 109736971 B CN109736971 B CN 109736971B
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Abstract
The invention discloses an electric pump pressure type liquid rocket engine, which comprises: an oxidizer main valve, an oxidizer pump, an oxygen pump motor, a multiple ignition device, a thrust chamber, a fuel main valve, a fuel pump motor, a fuel pump controller, an oxidizer pump controller, and a power supply; wherein the thrust chamber is connected with the oxidant main valve and the fuel main valve respectively; the oxidant main valve is connected with an outlet of the oxidant pump; the fuel main valve is connected with an outlet of the fuel pump; the oxidant pump is coaxially connected with the oxidant pump motor; the fuel pump motor is coaxially connected with the fuel pump; the oxygen pump motor is connected with the oxygen pump motor controller through a three-phase cable, and the fuel pump motor is connected with the fuel pump motor controller through a three-phase cable; and the power supply is respectively connected with the oxygen pump motor controller and the fuel pump motor controller through cables. The invention reduces the difficulty of production and manufacture and improves the reliability.
Description
Technical Field
The invention belongs to the field of liquid rocket engines, and particularly relates to an electric pump pressure type liquid rocket engine.
Background
The extrusion type rocket engine system is simple in structure, but the mass-to-thrust ratio is rapidly reduced along with the increase of the thrust, and the performance of the engine is lower; the pumping pressure open cycle engine is provided with a fuel gas generator to drive a turbine to do work and then discharge fuel gas, so that part of parts with harsh thermal environment are added; the pumping pressure type afterburning cycle engine supplies fuel gas to the thrust chamber for afterburning cycle after the fuel gas generator is arranged to drive the turbine to do work, and the system is complex in realization, high in technical difficulty and high in cost.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects of the prior art are overcome, and the electric pump pressure type liquid rocket engine is provided, wherein a motor is used for driving a pump to supply a thrust chamber for propellant pressurization, and a propellant supply system of a turbine gas generator is cancelled; the speed regulation of the motor is controlled by the controller to realize the thrust regulation and the mixing ratio regulation of the engine, the thrust regulation automatic machine and the mixing ratio regulation automatic machine are cancelled, and the engine system is simple.
The purpose of the invention is realized by the following technical scheme: an electrically pumped liquid rocket engine comprising: an oxidant main valve, an oxidant pump, an oxygen pump motor, a multiple ignition device, a thrust chamber, a fuel main valve, a fuel pump motor, an oxygen pump motor controller, a fuel pump motor controller and a power supply; wherein the thrust chamber is connected with the oxidant main valve and the fuel main valve respectively; the oxidant main valve is connected with an outlet of the oxidant pump; the fuel main valve is connected with an outlet of the fuel pump; the oxidant pump is coaxially connected with the oxidant pump motor, and the oxidant pump motor is cooled by using liquid oxygen leaked by the oxidant pump; the fuel pump motor is coaxially connected with the fuel pump, and is cooled by utilizing kerosene leaked from the fuel pump; the oxygen pump motor is connected with the oxygen pump motor controller through a three-phase cable, and the fuel pump motor is connected with the fuel pump motor controller through a three-phase cable; and the power supply is respectively connected with the oxygen pump motor controller and the fuel pump motor controller through cables.
In the electric pump type liquid rocket engine, the thrust chamber is connected to the main oxidizer valve through a first fuel supply line.
In the above electric pump type liquid rocket engine, the thrust chamber is connected to the main fuel valve through a first oxidizer supply line.
In the electric pump type liquid rocket engine, the main oxidizer valve is connected to an outlet of the oxidizer pump through a second oxidizer supply pipeline.
In the above electric pump type liquid rocket engine, the fuel main valve is connected to the outlet of the fuel pump through a second fuel supply line.
In the above electric pump type liquid rocket engine, the oxidizer pump is used for storing liquid oxygen.
In the above electric pump type liquid rocket engine, the fuel pump is used for storing kerosene.
In the electric pumping type liquid rocket engine, the voltage of the power supply is not more than DC 700V.
In the electric pumping type liquid rocket engine, the oxygen pump motor is a permanent magnet synchronous or direct current brushless motor.
In the electric pump pressure type liquid rocket engine, the fuel pump motor is a permanent magnet synchronous or direct current brushless motor.
Compared with the prior art, the invention has the following beneficial effects:
compared with the traditional pumping pressure type engine, the invention directly drives the pump to be the thrust chamber pressure through the motor, cancels high-temperature and high-pressure components with high processing difficulty such as a turbine, a gas generator and the like, and reduces the processing and manufacturing cost of the engine. Meanwhile, the motor speed is regulated by the motor controller, so that regulating assemblies such as a flow regulator, a throttle valve and the like in the traditional engine are simplified, and in addition, the pump efficiency is superior to that of the traditional liquid rocket engine when the pump efficiency deviates from a rated design point by respectively controlling the rotating speeds of the two motors. Compared with the existing liquid rocket engine, the invention can directly drive the pump to start and rotate through the motor when being started for multiple times, and can realize multiple starting by matching with a multiple ignition device. Because the engine system is simple, a turbine with harsh working thermal environment is cancelled, and the gas generator engine is easy to reuse.
Drawings
Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention. Also, like reference numerals are used to refer to like parts throughout the drawings. In the drawings:
FIG. 1 is a schematic structural diagram of an electric pump liquid rocket engine according to an embodiment of the present invention.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art. It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
FIG. 1 is a schematic structural diagram of an electric pump liquid rocket engine according to an embodiment of the present invention. As shown in fig. 1, the electric pumping type liquid rocket engine is composed of a thrust chamber 5, a fuel main valve 6, an oxidizer main valve 1, an oxidizer pump 2, a fuel pump 7, an oxygen pump motor 3, a fuel pump motor 8, a power supply 11, a fuel pump motor controller 10, an oxygen pump motor controller 9, and a multiple ignition device 4.
The thrust chamber 5 is connected to the oxidizer main valve 1 through a first fuel supply line 51; the thrust chamber 5 is connected to said main fuel valve 6 by means of a first oxidant supply line 52. The oxidant main valve 1 is connected with the outlet of the oxidant pump 2 through a second oxidant supply pipeline 53, and the fuel main valve 6 is connected with the outlet of the fuel pump 7 through a second fuel supply pipeline 54; the oxidant pump 2 is coaxially connected with the oxidant pump motor 3, and the oxidant pump motor 3 is cooled by using liquid oxygen leaked from the oxidant pump 2; the fuel pump motor 8 is coaxially connected to the fuel pump 7, and the fuel pump motor 8 is cooled by kerosene leaking from the fuel pump 7. The oxygen pump motor 3 is connected with the oxygen pump motor controller 9 through a three-phase cable, and the fuel pump motor 8 is connected with the fuel pump motor controller 10 through a three-phase cable; the power supply 11 supplies power to the oxygen pump motor controller 9 and the fuel pump motor controller 10 through cables, and the voltage of the power supply 11 is not more than DC 700V.
Starting and starting: the engine is started according to the scheme of 'self-starting', when starting, the lower valve of the oxidant storage tank is opened by the arrow body, and the oxidant flows through the oxidant pump 2 to be filled in front of the oxidant main valve 1 under the action of the static pressure head of the oxidant storage tank and the boosting pressure of the propellant component. Meanwhile, the lower valve of the rocket fuel storage tank is opened after the front channel of the engine fuel main valve 6 is vacuumized, and the engine fuel is filled in front of the fuel main valve 6. When the engine is started, the oxygen pump motor controller 9 and the fuel pump motor controller 10 respectively provide three alternating currents for the oxidant pump motor 3 and the fuel pump motor 8, the oxidant pump motor 3 and the fuel pump motor 8 start rotating, and the thrust chamber ignition device 4 is turned on. When the oxidant pump motor 3 and the fuel pump motor 8 are switched to the rated working condition, the oxygen main valve 1 and the fuel main valve 6 are opened in sequence, and then the thrust chamber 5 is ignited to finish the engine starting.
The engine works: the oxidant pump motor 3 drives the oxidant pump 2 to rotate to supply oxidant to the thrust chamber 5; the fuel pump 7 is driven to rotate by the fuel pump motor 8 to supply fuel for the thrust chamber; after entering the thrust chamber 5, the propellant is combusted in the combustion chamber to generate high-temperature fuel gas, and the high-temperature fuel gas is expanded and discharged through a thrust chamber nozzle to generate thrust.
Adjusting the working condition of the engine: the rotating speed of the motor 3 is controlled by the oxygen pump motor controller 9, the lifts of the oxidant pump 2 and the fuel pump 8 are respectively controlled by the way that the rotating speed of the motor 8 is controlled by the fuel pump motor controller 10, and the fuel pump motor 8 of the oxidant pump motor 3 independently adjusts the rotating speed and simultaneously cooperates with other flow control elements of the engine to realize the optimal pump efficiency in the processes of adjusting the thrust of the engine and adjusting the mixing ratio.
The oxygen pump motor 3 is a permanent magnet synchronous or direct current brushless motor, and can continuously adjust the rotating speed according to the instruction of the controller to change the lift of the oxidant pump.
The fuel pump motor 8 is a permanent magnet synchronous or direct current brushless motor, and can continuously adjust the rotating speed according to the instruction of the controller to change the delivery head of the fuel pump.
Compared with the traditional pumping pressure type engine, the direct drive pump of the motor is used as the thrust chamber pressure, high-temperature and high-pressure components with high processing difficulty such as a turbine and a fuel gas generator are eliminated, and the processing and manufacturing cost of the engine is reduced. Meanwhile, the motor speed is regulated by the motor controller, so that regulating assemblies such as a flow regulator, a throttle valve and the like in the traditional engine are simplified, and in addition, the pump efficiency is superior to that of the traditional liquid rocket engine when the pump efficiency deviates from a rated design point by respectively controlling the rotating speeds of the two motors. Compared with the existing liquid rocket engine, the liquid rocket engine can directly drive the pump to start and rotate through the motor when being started for multiple times, and can realize multiple starting by matching with a multiple ignition device. Because the engine system is simple, a turbine with harsh working thermal environment is cancelled, and the gas generator engine is easy to reuse.
The above-described embodiments are merely preferred embodiments of the present invention, and general changes and substitutions by those skilled in the art within the technical scope of the present invention are included in the protection scope of the present invention.
Claims (1)
1. An electric pump liquid rocket engine, comprising: the fuel pump comprises an oxidant main valve (1), an oxidant pump (2), an oxygen pump motor (3), a multi-ignition device (4), a thrust chamber (5), a fuel main valve (6), a fuel pump (7), a fuel pump motor (8), an oxygen pump motor controller (9), a fuel pump motor controller (10) and a power supply (11); wherein the content of the first and second substances,
the thrust chamber (5) is respectively connected with the oxidant main valve (1) and the fuel main valve (6);
the oxidant main valve (1) is connected with an outlet of the oxidant pump (2);
the fuel main valve (6) is connected with an outlet of the fuel pump (7);
the oxidant pump (2) is coaxially connected with the oxygen pump motor (3), and the oxygen pump motor (3) is cooled by using liquid oxygen leaked from the oxidant pump (2);
the fuel pump motor (8) is coaxially connected with the fuel pump (7), and the fuel pump motor (8) is cooled by utilizing kerosene leaked from the fuel pump (7);
the oxygen pump motor (3) is connected with the oxygen pump motor controller (9) through a three-phase cable, and the fuel pump motor (8) is connected with the fuel pump motor controller (10) through a three-phase cable;
the power supply (11) is respectively connected with the oxygen pump motor controller (9) and the fuel pump motor controller (10) through cables; wherein the content of the first and second substances,
the thrust chamber (5) is connected to the main oxidizer valve (1) via a first oxidizer supply line (51);
the thrust chamber (5) is connected to the main fuel valve (6) via a first fuel supply line (52);
the oxidant main valve (1) is connected with the outlet of the oxidant pump (2) through a second oxidant supply pipeline (53);
the fuel main valve (6) is connected with the outlet of the fuel pump (7) through a second fuel supply pipeline (54);
the oxidant pump (2) is used for storing liquid oxygen;
the fuel pump (7) is used for storing kerosene;
the voltage of the power supply (11) is not greater than DC 700V;
the oxygen pump motor (3) is a permanent magnet synchronous or direct current brushless motor;
the fuel pump motor (8) is a permanent magnet synchronous or direct current brushless motor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811527024.7A CN109736971B (en) | 2018-12-13 | 2018-12-13 | Electric pump pressure type liquid rocket engine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811527024.7A CN109736971B (en) | 2018-12-13 | 2018-12-13 | Electric pump pressure type liquid rocket engine |
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| CN109736971A CN109736971A (en) | 2019-05-10 |
| CN109736971B true CN109736971B (en) | 2021-05-04 |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111043042A (en) * | 2019-12-17 | 2020-04-21 | 北京深蓝航天科技有限公司 | Electric pump device of liquid rocket |
| CN111654227A (en) * | 2020-07-06 | 2020-09-11 | 江苏深蓝航天有限公司 | Electric drive control propellant supply system of variable-thrust liquid engine |
| CN112196694A (en) * | 2020-10-19 | 2021-01-08 | 北京天兵科技有限公司 | Premixed electric rocket engine and propelling method |
| CN112697439B (en) * | 2020-12-04 | 2022-05-17 | 江苏深蓝航天有限公司 | Complete machine liquid flow test system and method for electric pump circulation rocket engine |
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| WO2018051566A1 (en) * | 2016-09-14 | 2018-03-22 | 株式会社Ihi | Electric power-assisted liquid fuel rocket propulsion system |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| FR3000996B1 (en) * | 2013-01-11 | 2016-06-17 | Snecma | SYSTEM AND METHOD FOR FEEDING A ROCKER ENGINE |
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- 2018-12-13 CN CN201811527024.7A patent/CN109736971B/en active Active
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN204961314U (en) * | 2015-08-06 | 2016-01-13 | 刘延军 | Special canned motor pump of chemical industry |
| CN105909424A (en) * | 2016-04-12 | 2016-08-31 | 西北工业大学 | Propellant supply system for RBCC large regulating-ratio liquid-propellant rocket engine |
| CN105822459A (en) * | 2016-05-31 | 2016-08-03 | 河南海力特装备工程有限公司 | Novel rocket engine |
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