CN109736971A - A kind of electronic turbopump-fed liquid rocket engine - Google Patents
A kind of electronic turbopump-fed liquid rocket engine Download PDFInfo
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- CN109736971A CN109736971A CN201811527024.7A CN201811527024A CN109736971A CN 109736971 A CN109736971 A CN 109736971A CN 201811527024 A CN201811527024 A CN 201811527024A CN 109736971 A CN109736971 A CN 109736971A
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- oxidant
- pump
- fuel
- main valve
- turbopump
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Abstract
The invention discloses a kind of electronic turbopump-fed liquid rocket engines, comprising: oxidant main valve, oxidant pump, oxygen pump motor, multiple igniter, thrust chamber, fuel main valve, petrolift, fuel pump motor, fuel pump controller, oxidant pump controller and power supply；Wherein, the thrust chamber is connect with the oxidant main valve, the fuel main valve respectively；The oxidant main valve is connect with the outlet of the oxidant pump；The fuel main valve is connect with the outlet of the petrolift；The oxidant pump is connect with the oxidant pump motor coaxle；The fuel pump motor and the petrolift are coaxially connected；The oxygen pump motor is connect with the oxygen pump electric machine controller by threephase cable, and fuel pump motor is connect with petrolift electric machine controller by threephase cable；The power supply respectively with oxygen pump electric machine controller and petrolift electric machine controller cable connection.The present invention is manufacturing difficulty reduction while mentioning high reliability.
Description
Technical field
The invention belongs to liquid-propellant rocket engine field more particularly to a kind of electronic turbopump-fed liquid rocket engines.
Background technique
Ullage rocket engine system structure is simple, but increases thrust-mass ratio with thrust and reduce rapidly, and engine performance
It is lower；It is pumped open-cycle engine, combustion gas is discharged after driving turbine acting by setting gas generator, increases part
Zero harsh parts of heating power environment；Pump pressure type afterburning cycle engine, after driving turbine acting by setting gas generator
Gas supply to thrust chamber is subjected to afterburning circulation, system realizes that complicated and technical difficulty is big, at high cost.
Summary of the invention
Technical problem solved by the present invention is having overcome the deficiencies of the prior art and provide a kind of electronic pump pressure type liquid fire
Arrow engine is propellant pressurization supply thrust chamber using Electric-motor driven pumps, eliminates turbine gas generator machine propellant
Supply system；Electric machine speed regulation is controlled by controller and realizes that motor power is adjusted and mixing ratio is adjusted, and eliminates thrust adjusting
Automation and mixing ratio adjust automation, and engine system is simple.
The object of the invention is achieved by the following technical programs: a kind of electronic turbopump-fed liquid rocket engine, comprising:
Oxidant main valve, oxidant pump, oxygen pump motor, multiple igniter, thrust chamber, fuel main valve, petrolift, fuel pump motor,
Fuel pump controller, oxidant pump controller and power supply；Wherein, the thrust chamber respectively with the oxidant main valve, the combustion
Expect main valve connection；The oxidant main valve is connect with the outlet of the oxidant pump；The fuel main valve and the petrolift
Outlet connection；The oxidant pump is connect with the oxidant pump motor coaxle, using oxidant pump leakage liquid oxygen to oxidant
Pump motor is cooled down；The fuel pump motor and the petrolift are coaxially connected, using fuel bump leakage kerosene to petrolift
Motor is cooled down；The oxygen pump motor is connect with the oxygen pump electric machine controller by threephase cable, fuel pump motor and combustion
Expect that pump motor controller is connected by threephase cable；The power supply respectively with oxygen pump electric machine controller and petrolift electric machine controller
Cable connection.
In above-mentioned electronic turbopump-fed liquid rocket engine, the thrust chamber passes through the first fuel supply conduit and the oxygen
Agent main valve is connected.
In above-mentioned electronic turbopump-fed liquid rocket engine, the thrust chamber by the first oxidant supply line with it is described
Fuel main valve is connected.
In above-mentioned electronic turbopump-fed liquid rocket engine, the oxidant main valve by the second oxidant supply line with
Oxidant pump outlet connection.
In above-mentioned electronic turbopump-fed liquid rocket engine, the fuel main valve by the second fuel supply conduit with it is described
Fuel pump outlet connection.
In above-mentioned electronic turbopump-fed liquid rocket engine, the oxidant pump is for storing liquid oxygen.
In above-mentioned electronic turbopump-fed liquid rocket engine, the petrolift is for storing kerosene.
In above-mentioned electronic turbopump-fed liquid rocket engine, the voltage of the power supply is not more than DC700V.
In above-mentioned electronic turbopump-fed liquid rocket engine, the oxygen pump motor is permanent-magnet synchronous or DC brushless motor.
In above-mentioned electronic turbopump-fed liquid rocket engine, the fuel pump motor is permanent-magnet synchronous or brush DC electricity
Machine.
Compared with prior art, the present invention has the following advantages:
The present invention by motor direct-drive pump be thrust chamber pressure compared with conventional pump pressure engine, eliminate turbine,
The big high temperature and pressure component of the difficulty of processing such as gas generator reduces engine processing and manufacturing cost.Motor control is utilized simultaneously
Device processed adjusts motor speed, simplifies flow regulator in conventional engines, throttle valve etc. and adjusts component, additionally by controlling respectively
Making two motor speeds makes the efficiency of pump when deviateing rated designs point better than traditional liquid rocket engine.With existing liquid rocket
Engine is compared, and the present invention can pump up rotation in multiple start by motor direct-drive, cooperates multiple igniter that can realize
Repeatedly start.Since engine system is succinct, eliminates the harsh turbine of working heat force environment and Gas generator engine is easy
In reuse.
Detailed description of the invention
By reading the following detailed description of the preferred embodiment, various other advantages and benefits are common for this field
Technical staff will become clear.The drawings are only for the purpose of illustrating a preferred embodiment, and is not considered as to the present invention
Limitation.And throughout the drawings, the same reference numbers will be used to refer to the same parts.In the accompanying drawings:
Fig. 1 is the structural schematic diagram of electronic turbopump-fed liquid rocket engine provided in an embodiment of the present invention.
Specific embodiment
Exemplary embodiments of the present disclosure are described in more detail below with reference to accompanying drawings.Although showing the disclosure in attached drawing
Exemplary embodiment, it being understood, however, that may be realized in various forms the disclosure without should be by embodiments set forth here
It is limited.On the contrary, these embodiments are provided to facilitate a more thoroughly understanding of the present invention, and can be by the scope of the present disclosure
It is fully disclosed to those skilled in the art.It should be noted that in the absence of conflict, embodiment in the present invention and
Feature in embodiment can be combined with each other.The present invention will be described in detail below with reference to the accompanying drawings and embodiments.
Fig. 1 is the structural schematic diagram of electronic turbopump-fed liquid rocket engine provided in an embodiment of the present invention.Such as Fig. 1 institute
Show, the electronic turbopump-fed liquid rocket engine is by thrust chamber 5, fuel main valve 6, oxidant main valve 1, oxidant pump 2, petrolift
7, oxygen pump motor 3, fuel pump motor 8, power supply 11, oxidant pump controller 10, fuel pump controller 9 and multiple igniter 4
Composition.
Thrust chamber 5 is connected by the first fuel supply conduit 51 with oxidant main valve 1；Thrust chamber 5 passes through the first oxidation
Agent supply line 52 is connected with the fuel main valve 6.Oxidant main valve 1 passes through the second oxidant supply line 53 and oxidant
3 outlet connection of pump, fuel main valve 6 are connected by the second fuel supply conduit 54 and the outlet of petrolift 7；Oxidant pump 2 and oxidation
Agent pump motor 3 is coaxially connected, leaks liquid oxygen using oxidant pump 2 and cools down to oxidant pump motor 3；Fuel pump motor 8 with
Petrolift 7 is coaxially connected, leaks kerosene using petrolift 7 and cools down to fuel pump motor 8.Oxygen pump motor 3 and oxygen pump motor
Controller 9 is connected by threephase cable, and fuel pump motor 8 is connect with petrolift electric machine controller 10 by threephase cable；Power supply
11 pass through cable to oxygen pump electric machine controller 9, and petrolift electric machine controller 10 provides electrical source of power, and 11 voltage of power supply is not more than
DC700V。
Start to start: starting engine by " itself start " scheme, rocket body opens oxidant tank lower valve, oxygen when starting
Agent flows through oxidant pump 2 under oxidant tank hydrostatic head and the effect of propellant constituent element boost pressure and is fills up to oxidant main valve
Before 1.Rocket body fuel tank lower valve is opened after 6 prepass of engine fuel main valve vacuumizes simultaneously, engine fuel is fills up to
Before fuel main valve 6.Oxidant pump electric machine controller 9 and petrolift electric machine controller 10 are respectively oxidant pump when engine start
Motor 3 and fuel pump motor 8 provide three alternating currents, and oxidant pump motor 3 and fuel pump motor 8 play rotation, open simultaneously
Thrust chamber igniter 4.Oxygen main valve 1 and combustion are successively opened when oxidant pump motor 3 and fuel pump motor 8 go to declared working condition
Expect main valve 6, engine start is completed in the igniting of thrust chamber 5 later.
Engine operation: driving oxidant pump 2 to play rotation by oxidant pump motor 3 is that thrust chamber 5 supplies oxidant；Pass through
It is that thrust chamber supplies fuel that fuel pump motor 8, which drives petrolift 7 to play rotation,；Propellant burns in the combustion chamber after entering thrust chamber 5
It generates high-temperature fuel gas and generation thrust is discharged through thrust chamber nozzle expansion.
Engine operating condition is adjusted: controlling 3 revolving speed of motor, petrolift electric machine controller by oxidant pump electric machine controller 9
The mode of 10 control 8 revolving speeds of motor controls the lift of oxidant pump 3 Yu petrolift 8,3 fuel pump motor of oxidant pump motor respectively
Simultaneously, the other flow control elements of cooperation engine realize motor power adjusting, mixing ratio adjustment process to 8 separately adjustable revolving speeds
The middle efficiency of pump is optimal.
Oxygen pump motor 3 is permanent-magnet synchronous or DC brushless motor, can be instructed according to controller and continuously adjust revolving speed change oxygen
Agent pump lift.
Fuel pump motor 8 is permanent-magnet synchronous or DC brushless motor, can be instructed according to controller and continuously adjust revolving speed change
Fuel pump lift.
The present embodiment is thrust chamber pressure compared with conventional pump pressure engine by motor direct-drive pump, eliminates whirlpool
The big high temperature and pressure component of the difficulty of processing such as wheel, gas generator reduces engine processing and manufacturing cost.Motor is utilized simultaneously
Controller adjusts motor speed, simplifies flow regulator in conventional engines, throttle valve etc. and adjusts component, additionally by respectively
Controlling two motor speeds makes the efficiency of pump when deviateing rated designs point better than traditional liquid rocket engine.With existing liquid fire
Arrow engine is compared, and the present embodiment can pump up rotation in multiple start by motor direct-drive, cooperates multiple igniter can
It realizes and repeatedly starts.Since engine system is succinct, eliminates the harsh turbine of working heat force environment and gas generator starts
Machine is easy to reuse.
Embodiment described above is the present invention more preferably specific embodiment, and those skilled in the art is in this hair
The usual variations and alternatives carried out in bright technical proposal scope should be all included within the scope of the present invention.
Claims (10)
1. a kind of electronic turbopump-fed liquid rocket engine, characterized by comprising: oxidant main valve (1), oxidant pump (2),
Oxygen pump motor (3), multiple igniter (4), thrust chamber (5), fuel main valve (6), petrolift (7), fuel pump motor (8), combustion
Expect pump controller (9), oxidant pump controller (10) and power supply (11)；Wherein,
The thrust chamber (5) connect with the oxidant main valve (1), the fuel main valve (6) respectively；
The oxidant main valve (1) connect with the outlet of the oxidant pump (3)；
The fuel main valve (6) connect with the outlet of the petrolift (7)；
The oxidant pump (2) and the oxidant pump motor (3) are coaxially connected, using oxidant pump (2) leakage liquid oxygen to oxygen
Agent pump motor (3) is cooled down；
The fuel pump motor (8) and the petrolift (7) are coaxially connected, using petrolift (7) leakage kerosene to petrolift electricity
Machine (8) is cooled down；
The oxygen pump motor (3) is connect with the oxygen pump electric machine controller (9) by threephase cable, fuel pump motor (8) and combustion
Expect that pump motor controller (10) are connected by threephase cable；
The power supply (11) respectively with oxygen pump electric machine controller (9) and petrolift electric machine controller (10) cable connection.
2. electronic turbopump-fed liquid rocket engine according to claim 1, it is characterised in that: the thrust chamber (5) is logical
The first fuel supply conduit (51) is crossed to be connected with the oxidant main valve (1).
3. electronic turbopump-fed liquid rocket engine according to claim 1, it is characterised in that: the thrust chamber (5) is logical
The first oxidant supply line (52) is crossed to be connected with the fuel main valve (6).
4. electronic turbopump-fed liquid rocket engine according to claim 1, it is characterised in that: the oxidant main valve
(1) it is connected by the second oxidant supply line (53) and the oxidant pump (3) outlet.
5. electronic turbopump-fed liquid rocket engine according to claim 1, it is characterised in that: the fuel main valve (6)
It is connected by the second fuel supply conduit (54) and the petrolift (7) outlet.
6. electronic turbopump-fed liquid rocket engine according to claim 1, it is characterised in that: the oxidant pump (2)
For storing liquid oxygen.
7. electronic turbopump-fed liquid rocket engine according to claim 1, it is characterised in that: the petrolift (7) is used
In storage kerosene.
8. electronic turbopump-fed liquid rocket engine according to claim 1, it is characterised in that: the electricity of the power supply (11)
Pressure is not more than DC700V.
9. electronic turbopump-fed liquid rocket engine according to claim 1, it is characterised in that: the oxygen pump motor (3)
For permanent-magnet synchronous or DC brushless motor.
10. electronic turbopump-fed liquid rocket engine according to claim 1, it is characterised in that: the fuel pump motor
It (8) is permanent-magnet synchronous or DC 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 |
Applications Claiming Priority (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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109736971A true CN109736971A (en) | 2019-05-10 |
| CN109736971B CN109736971B (en) | 2021-05-04 |
Family
ID=66358900
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811527024.7A Active CN109736971B (en) | 2018-12-13 | 2018-12-13 | Electric pump pressure type liquid rocket engine |
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Cited By (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 |
| CN112697439A (en) * | 2020-12-04 | 2021-04-23 | 江苏深蓝航天有限公司 | Complete machine liquid flow test system and method for electric pump circulation rocket engine |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20150354503A1 (en) * | 2013-01-11 | 2015-12-10 | Snecma | System and a method for feeding a rocket engine |
| CN204961314U (en) * | 2015-08-06 | 2016-01-13 | 刘延军 | Special canned motor pump of chemical industry |
| CN105822459A (en) * | 2016-05-31 | 2016-08-03 | 河南海力特装备工程有限公司 | Novel rocket engine |
| 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 |
| CN106555707A (en) * | 2016-11-30 | 2017-04-05 | 西北工业大学 | Electricity drives propellant-feed system liquid-propellant rocket engine |
| CN107237703A (en) * | 2017-07-26 | 2017-10-10 | 北京航空航天大学 | Solid-liquid rocket electrodynamic pump induction system |
| WO2018051566A1 (en) * | 2016-09-14 | 2018-03-22 | 株式会社Ihi | Electric power-assisted liquid fuel rocket propulsion system |
| CN108757182A (en) * | 2018-05-29 | 2018-11-06 | 中国人民解放军国防科技大学 | Air-breathing rocket engine and Hypersonic Aircraft |
-
2018
- 2018-12-13 CN CN201811527024.7A patent/CN109736971B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20150354503A1 (en) * | 2013-01-11 | 2015-12-10 | Snecma | System and a method for feeding a rocket engine |
| 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 |
| WO2018051566A1 (en) * | 2016-09-14 | 2018-03-22 | 株式会社Ihi | Electric power-assisted liquid fuel rocket propulsion system |
| CN106555707A (en) * | 2016-11-30 | 2017-04-05 | 西北工业大学 | Electricity drives propellant-feed system liquid-propellant rocket engine |
| CN107237703A (en) * | 2017-07-26 | 2017-10-10 | 北京航空航天大学 | Solid-liquid rocket electrodynamic pump induction system |
| CN108757182A (en) * | 2018-05-29 | 2018-11-06 | 中国人民解放军国防科技大学 | Air-breathing rocket engine and Hypersonic Aircraft |
Cited By (5)
| 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 |
| CN112697439A (en) * | 2020-12-04 | 2021-04-23 | 江苏深蓝航天有限公司 | Complete machine liquid flow test system and method for electric pump circulation rocket engine |
| 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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| CN109736971B (en) | 2021-05-04 |
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