CN111751115A - Ground test system for liquid rocket electric pump engine - Google Patents
Ground test system for liquid rocket electric pump engine Download PDFInfo
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- CN111751115A CN111751115A CN202010490737.1A CN202010490737A CN111751115A CN 111751115 A CN111751115 A CN 111751115A CN 202010490737 A CN202010490737 A CN 202010490737A CN 111751115 A CN111751115 A CN 111751115A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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Abstract
The invention provides a ground test system for a liquid rocket motor pump engine, which comprises a fuel supply system, an oxidant supply system, a motor pump pressure type engine system, a power supply and a control system. The fuel supply system and the oxidant supply system are respectively connected with the electric pump type engine system through a first pipeline and a second pipeline, and the fuel pump and the oxidant pump are used for realizing pressurization and supply of the fuel and the oxidant. The start-stop performance of the electric pump pressure type engine system is realized by controlling the start-stop of the fuel pump and the oxidant pump through a motor driver in the power supply and control system. The invention is suitable for the electric pump pressure type liquid rocket engine, and particularly has obvious application advantages in the aspects of variable thrust and multiple-start liquid rocket engine test.
Description
Technical Field
The invention relates to the technical field of pump pressure type liquid rocket engines, in particular to a ground test system for a liquid rocket electric pump engine. And more particularly, to an electric pump pressure type engine ground test system.
Background
The existing liquid rocket engine supercharging modes mainly comprise an extrusion type mode and a turbine pump pressure type mode. The concept of electric boosting, although it has been proposed for a long time, is limited to electric machines and high performance battery technology, and has not been rapidly developed until recently abroad. Compared with a conventional extrusion or turbine pump pressure type supply system, the electric pump pressurization system has the advantages of higher engine inlet pressure, realization of variable working condition operation through rotating speed control, and easiness in realization of multiple starting work of the engine. The ground test system of the liquid rocket electric pump engine comprises: 1) the working time sequence of the motor of the electric pump is convenient to adjust, and the working characteristics of the motor of the electric pump are explored; 2) the power supply and control of the electric pump are realized through the motor driver, so that the electric pump is convenient to start and stop for multiple times; 3) (ii) a The variable working condition performance examination of the electric pump pressure type engine is facilitated by combining the rotation speed regulation of the pump by the motor controller and the flow resistance regulation of the throttling orifice plate on the pipeline; 4) motor pump engine tests with different combinations of propellants can be performed.
At present, no description or report of similar technologies to the technology of the invention is found at home, and similar data at home and abroad is not collected.
The invention can obtain the start-stop time sequence, the working characteristics and the variable working condition performance of the liquid rocket motor pump system, and provides reference for the design optimization of the motor pump motor system.
Patent document CN 109736971a (application No. 201811527024.7) discloses an electric pump type liquid rocket engine comprising: 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.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a ground test system for a liquid rocket motor-driven pump engine.
The invention provides a ground test system for a liquid rocket motor pump engine, which comprises: the system comprises a fuel supply system, an oxidant supply system, an electric pump pressure type engine system, a power supply and a control system;
the fuel supply system is connected with the electric pump pressure type engine system through a first pipeline;
the oxidant supply system is connected with the electric pump pressure type engine system through a second pipeline;
the power supply and control system is respectively connected with the fuel pump and the oxidant pump through a first cable and a second cable, so that the electric energy supply and the real-time control of the pumps are realized.
Preferably, the fuel supply system includes:
a pressurized source of fuel, a fuel tank, a fuel filter, a fuel flow meter, a fuel pressure sensor, a fuel temperature sensor, and a fuel supply valve.
Preferably, the fuel pressurization air source is used for adjusting the pressure of working medium before the fuel pump.
Preferably, the oxidant supply system comprises:
the system comprises an oxidant pressurizing gas source, an oxidant storage tank, an oxidant filter, an oxidant flowmeter, an oxidant pressure sensor, an oxidant temperature sensor and an oxidant supply valve;
preferably, the oxidant pressurization gas source is used for adjusting the pressure of working medium before the oxidant pump.
Preferably, the electric pump engine system comprises:
a fuel pump, an oxidizer pump, a fuel path orifice plate, an oxygen path orifice plate, a fuel path pressure sensor, an oxygen path pressure sensor, a fuel path temperature sensor, an oxygen path temperature sensor, a fuel path discharge valve, an oxygen path discharge valve, a fuel path main valve, an oxygen path main valve, and a thrust chamber.
Preferably, the fuel pump and the oxidizer pump are: a variable frequency motor is used for driving the variable speed booster pump;
the booster pump comprises any one of the following components: vane type, positive displacement.
Preferably, the fuel path pore plate and the oxygen path pore plate are respectively used for adjusting the flow resistance of the fuel path and the oxygen path so as to meet the working condition parameters of the electric pump pressure type engine system.
Preferably, the power supply and control system includes:
a power supply, a fuel pump motor driver, an oxidant pump motor driver.
Preferably, the power supply has a voltage adjustable function, meets the power supply requirements of electric pump-type engine systems with different power levels, and realizes the electric energy supply of the motor in the test process;
the fuel pump motor driver and the oxidant pump motor driver are variable frequency drivers and are used for adjusting the rotating speed of the motors, and meanwhile, the motor drivers have the function of feeding back electrical performance parameters of the fuel pump motor and the oxidant pump motor in real time;
the electrical property parameters include: operating voltage, current, power factor, input power.
Compared with the prior art, the invention has the following beneficial effects:
the invention is suitable for the electric pump pressure type liquid rocket engine, and particularly has obvious application advantages in the aspects of variable thrust and multiple-start liquid rocket engine test.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
fig. 1 is a schematic structural diagram of a ground test system of a liquid rocket electric pump engine according to an embodiment of the present invention.
Reference numerals: 1-a fuel supply system; 11-a fuel pressurized air source; 12-a fuel tank; 13-a fuel filter; 14-a fuel flow meter; 15-fuel pressure sensor; 16-fuel temperature sensor; 17-a fuel supply valve; 2-an oxidant supply system; 21-oxidant pressurized gas source; 22-an oxidant reservoir; 23-an oxidant filter; 24-oxidant flow rate; 25-an oxidant pressure sensor; 26-an oxidant temperature sensor; 27-an oxidant supply valve; 3-an electric pump-pressure engine system; 31-a fuel pump; 32-an oxidant pump; 33-a combustion road hole plate; 34-an oxygen pathway orifice plate; 35-a fuel line pressure sensor; 36-oxygen path pressure sensor; 37-a fuel line temperature sensor; 38-oxygen path temperature sensor; 39-fuel line drain valve; 310-oxygen line vent valve; 311-a main fuel valve; 312-oxygen main valve; 313-a thrust chamber; 4-power and control system; 41-power supply; 42-fuel pump motor driver; 43-oxidant pump motor driver; 5, a first pipeline; 6-pipeline two; 7-cable one; 8-cable two.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
The invention provides a ground test system for a liquid rocket motor pump engine, which comprises: the system comprises a fuel supply system, an oxidant supply system, an electric pump pressure type engine system, a power supply and a control system;
the fuel supply system is connected with the electric pump pressure type engine system through a first pipeline;
the oxidant supply system is connected with the electric pump pressure type engine system through a second pipeline;
the power supply and control system is respectively connected with the fuel pump and the oxidant pump through a first cable and a second cable, so that the electric energy supply and the real-time control of the pumps are realized.
Specifically, the fuel supply system comprises:
a pressurized source of fuel, a fuel tank, a fuel filter, a fuel flow meter, a fuel pressure sensor, a fuel temperature sensor, and a fuel supply valve.
Specifically, the fuel pressurization air source is used for adjusting the pressure of a working medium before the fuel pump.
Specifically, the oxidant supply system includes:
the system comprises an oxidant pressurizing gas source, an oxidant storage tank, an oxidant filter, an oxidant flowmeter, an oxidant pressure sensor, an oxidant temperature sensor and an oxidant supply valve;
specifically, the oxidant pressurization gas source is used for adjusting the pressure of the working medium before the oxidant pump.
Specifically, the electric pump engine system includes:
a fuel pump, an oxidizer pump, a fuel path orifice plate, an oxygen path orifice plate, a fuel path pressure sensor, an oxygen path pressure sensor, a fuel path temperature sensor, an oxygen path temperature sensor, a fuel path discharge valve, an oxygen path discharge valve, a fuel path main valve, an oxygen path main valve, and a thrust chamber.
Specifically, the fuel pump and the oxidizer pump are: a variable frequency motor is used for driving the variable speed booster pump;
the booster pump comprises any one of the following components: vane type, positive displacement.
Specifically, the fuel path pore plate and the oxygen path pore plate are respectively used for adjusting the flow resistance of the fuel path and the oxygen path so as to meet the working condition parameters of the electric pump pressure type engine system.
Specifically, the power supply and control system comprises:
a power supply, a fuel pump motor driver, an oxidant pump motor driver.
Specifically, the power supply has a voltage adjustable function, meets the power supply requirements of electric pump-type engine systems with different power levels, and realizes the electric energy supply of the motor in the test process;
the fuel pump motor driver and the oxidant pump motor driver are variable frequency drivers and are used for adjusting the rotating speed of the motors, and meanwhile, the motor drivers have the function of feeding back electrical performance parameters of the fuel pump motor and the oxidant pump motor in real time;
the electrical property parameters include: operating voltage, current, power factor, input power.
The present invention will be described more specifically below with reference to preferred examples.
Preferred example 1:
the invention aims to provide a ground test system for a liquid rocket motor pump engine, which is used for exploring the working characteristics of a motor pump type engine system, examining the steady-state and variable working condition performance and the multiple start-stop capability of the motor pump type engine system. The ground test system of the liquid rocket electric pump engine comprises a fuel supply system, an oxidant supply system, an electric pump type engine system, a power supply and a control system. The fuel supply system is connected with the electric pumping type engine system through a first pipeline. And the oxidant supply system is connected with the electric pump type engine system through a second pipeline. The power supply and control system is respectively connected with the fuel pump and the oxidant pump through a first cable and a second cable, so that the electric energy supply and the real-time control of the pumps are realized.
The fuel supply system comprises a fuel pressurization air source, a fuel storage tank, a fuel filter, a fuel flow meter, a fuel pressure sensor, a fuel temperature sensor and a fuel supply valve. The fuel pressurizing air source is used for adjusting the pressure of the working medium in front of the fuel pump.
The oxidant supply system comprises an oxidant pressurization gas source, an oxidant storage tank, an oxidant filter, an oxidant flowmeter, an oxidant pressure sensor, an oxidant temperature sensor and an oxidant supply valve. And the oxidant pressurization gas source is used for adjusting the pressure of the working medium before the oxidant pump.
The electric pump type engine system comprises a fuel pump, an oxidant pump, a fuel path pore plate, an oxygen path pore plate, a fuel path pressure sensor, an oxygen path pressure sensor, a fuel path temperature sensor, an oxygen path temperature sensor, a fuel path discharge valve, an oxygen path discharge valve, a fuel path main valve, an oxygen path main valve and a thrust chamber. The fuel pump and the oxidant pump comprise vane type or positive displacement booster pumps driven by a variable frequency motor and with adjustable rotating speed, and the fuel path pore plate and the oxygen path pore plate are used for adjusting the flow resistance of a fuel path and an oxygen path so as to meet the working condition parameters of the electric pumping pressure type engine system.
The power supply and control system comprises a power supply, a fuel pump motor driver and an oxidant pump motor driver. The power supply has a voltage adjustable function, meets the power supply requirements of electric pump pressure type engine systems with different power levels, and realizes the electric energy supply of the motor in the test process. The fuel pump motor driver and the oxidant pump motor driver are variable-frequency drivers and can be used for adjusting the rotating speed of the motors, and meanwhile, the motor drivers have the function of feeding back working voltage, current, power factors, input power and other electrical performance parameters of the fuel pump motor and the oxidant pump motor in real time.
Preferred example 2:
fig. 1 is a schematic structural diagram of a ground test system of a liquid rocket electric pump engine according to an embodiment of the present invention. As shown in FIG. 1, the liquid rocket motor-pump engine test system provided by the invention comprises a fuel supply system 1, an oxidant supply system 2, a motor-pump engine system 3 and a power supply and control system 4. The fuel supply system 1 is connected to the electric pump engine system 3 via a first conduit 5. The oxidant supply system 2 is connected to the electric pumped engine system 3 via conduit two 6. The power supply and control system 4 is connected with the fuel pump 31 and the oxidant pump 32 through the first cable 7 and the second cable 8 respectively, so that the power supply and the real-time control of the pumps are realized.
The fuel supply system 1 comprises a fuel pressurization air source 11, a fuel storage tank 12, a fuel filter 13, a fuel flow meter 14, a fuel pressure sensor 15, a fuel temperature sensor 16 and a fuel supply valve 17. The fuel pressurization air source 11 is used for adjusting the pressure of the working medium before the fuel pump 31.
The oxidant supply system 2 includes an oxidant pressurized gas source 21, an oxidant storage tank 22, an oxidant filter 23, an oxidant flow meter 24, an oxidant pressure sensor 25, an oxidant temperature sensor 26, and an oxidant supply valve 27. The oxidant pressurizing gas source 21 is used for adjusting the pressure of the working medium before the oxidant pump 32.
The electric pump engine system 3 includes a fuel pump 31, an oxidizer pump 32, a fuel passage orifice 33, an oxygen passage orifice 34, a fuel passage pressure sensor 35, an oxygen passage pressure sensor 36, a fuel passage temperature sensor 37, an oxygen passage temperature sensor 38, a fuel passage discharge valve 39, an oxygen passage discharge valve 310, a fuel passage main valve 311, an oxygen passage main valve 312, and a thrust chamber 313. The fuel pump 31 and the oxidant pump 32 comprise vane type or positive displacement booster pumps driven by a variable frequency motor and with adjustable rotating speed, and the fuel path orifice plate 33 and the oxygen path orifice plate 34 are used for adjusting the flow resistance of a fuel path and an oxygen path so as to meet the working condition parameters of the electric pumping type engine system 3.
The power supply and control system 4 includes a power supply 41, a fuel pump motor driver 42, and an oxidant pump motor driver 43. The power supply 41 has a voltage adjustable function, meets the power supply requirements of electric pump-type engine systems with different power levels, and realizes the electric energy supply of the motor in the test process. The fuel pump motor driver 42 and the oxidant pump motor driver 43 are variable frequency drivers, and can be used for adjusting the rotating speed of the motors, and meanwhile, the motor drivers have the function of feeding back the working voltage, current, power factors, input power and other electrical performance parameters of the motors of the fuel pump 31 and the oxidant pump 32 in real time.
The invention provides a ground test system for a liquid rocket electric pump engine, which mainly comprises the following working processes:
1) pump filling and exhausting: confirming that all valves are closed, opening the fuel supply valve 17 and the oxidizer supply valve 27, respectively, the fuel and the oxidizer are introduced into the fuel pump 31 and the oxidizer pump 32, opening the fuel path exhaust valve 39 and the oxygen path exhaust valve 310, respectively, the fuel and the oxidizer are discharged from the rear of the fuel pump 31 and the rear of the oxidizer pump 32, 5s later, closing the fuel path exhaust valve 39 and the oxygen path exhaust valve 310, and closing the fuel supply valve 17 and the oxidizer supply valve 27.
2) And (3) steady-state performance test: after completing the pump filling and the exhaust, the internal pressures of the fuel storage tank 12 and the oxidizer storage tank 22 are respectively increased to set values by the fuel pressurization air source 11 and the oxidizer pressurization air source 21, the fuel supply valve 17 and the oxidizer supply valve 27 are opened, the power supply and control system 4 is started, the power supply 41 supplies power to the fuel pump 31 and the oxidizer pump 32 through the fuel pump motor driver 42 and the oxidizer pump motor driver 43 respectively and drives the two pumps to work, when the rotating speeds of the fuel pump 31 and the oxidizer pump 32 fed back by the fuel pump motor driver 42 and the oxidizer pump motor driver 43 reach the set values or the pressures shown by the fuel circuit pressure sensor 35 and the oxygen circuit pressure sensor 36 reach the set values, the fuel circuit main valve 311 and the oxygen circuit main valve 312 are opened, the fuel and the propellant enter the thrust chamber 313, and the electric pump type engine system 3 starts. After a certain period of stable operation, the fuel main valve 311 and the oxygen main valve 312 are closed, the thrust chamber 313 is stopped, the fuel pump 31 and the oxidizer pump 32 are then closed, and finally the fuel supply valve 17 and the oxidizer supply valve 27 are closed.
3) And (3) variable working condition performance test: after completing the pump filling and the exhaust, the internal pressures of the fuel storage tank 12 and the oxidizer storage tank 22 are respectively increased to set values by the fuel pressurization air source 11 and the oxidizer pressurization air source 21, the fuel supply valve 17 and the oxidizer supply valve 27 are opened, the power supply and control system 4 is started, the power supply 41 supplies power to the fuel pump 31 and the oxidizer pump 32 through the fuel pump motor driver 42 and the oxidizer pump motor driver 43 respectively and drives the two pumps to work, when the rotating speeds of the fuel pump 31 and the oxidizer pump 32 fed back by the fuel pump motor driver 42 and the oxidizer pump motor driver 43 reach the set values or the pressures shown by the fuel circuit pressure sensor 35 and the oxygen circuit pressure sensor 36 reach the set values, the fuel circuit main valve 311 and the oxygen circuit main valve 312 are opened, the fuel and the propellant enter the thrust chamber 313, and the electric pump type engine system 3 starts. After the electric pump type engine system 3 starts to operate, the rotation speeds of the fuel pump 31 and the oxidant pump 32 are adjusted by the fuel pump motor driver 42 and the oxidant pump motor driver 43, the inlet pressures and the flow rates of the fuel path main valve 311 and the oxygen path main valve 312 in the electric pump type engine system 3 are changed to realize variable operation, after the variable operation test is completed, the fuel path main valve 311 and the oxygen path main valve 312 are closed, the thrust chamber 313 stops operating, then the fuel pump 31 and the oxidant pump 32 are closed, and finally the fuel supply valve 17 and the oxidant supply valve 27 are closed.
4) Adjusting the working condition points: in order to fully test the performance of the electric pump type engine system 3, in addition to changing the working curves of the fuel pump 31 and the oxidant pump 32 through the rotation speed adjustment as described in 3), the adjustment of the flow resistance of the pipeline can be realized by combining the adjustment of the fuel path adjusting orifice plate 33 and the oxygen path adjusting orifice plate 34 downstream of the fuel pump 31 and the oxidant pump 32.
5) And (3) starting and stopping for many times: and the motor pump engine is checked on starting and stopping performance for many times in a mode of multiple steady-state performance tests.
The ground test system for the liquid rocket motor-driven pump engine provided by the embodiment I has the following advantages:
1) the system is suitable for a liquid rocket electric pump engine system adopting an electric supercharging mode;
2) the start-stop time sequence of the motor pump engine can be conveniently adjusted, and the start-stop and working characteristics of different motor pump engines can be conveniently researched;
3) the pressure and the flow of the propellant at the inlet of the engine can be conveniently adjusted by combining the rotation speed adjustment and the pipeline flow resistance adjustment, and the variable working condition performance test of the engine is carried out;
4) the performance test of the electric pump engine with different propellant combinations is convenient to realize.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
Those skilled in the art will appreciate that, in addition to implementing the systems, apparatus, and various modules thereof provided by the present invention in purely computer readable program code, the same procedures can be implemented entirely by logically programming method steps such that the systems, apparatus, and various modules thereof are provided in the form of logic gates, switches, application specific integrated circuits, programmable logic controllers, embedded microcontrollers and the like. Therefore, the system, the device and the modules thereof provided by the present invention can be considered as a hardware component, and the modules included in the system, the device and the modules thereof for implementing various programs can also be considered as structures in the hardware component; modules for performing various functions may also be considered to be both software programs for performing the methods and structures within hardware components.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. The utility model provides a liquid rocket motor pump engine ground test system which characterized in that includes: the system comprises a fuel supply system, an oxidant supply system, an electric pump pressure type engine system, a power supply and a control system;
the fuel supply system is connected with the electric pump pressure type engine system through a first pipeline;
the oxidant supply system is connected with the electric pump pressure type engine system through a second pipeline;
the power supply and control system is respectively connected with the fuel pump and the oxidant pump through a first cable and a second cable, so that the electric energy supply and the real-time control of the pumps are realized.
2. The ground test system for liquid rocket motor-pump engines as defined in claim 1, wherein said fuel supply system comprises:
a pressurized source of fuel, a fuel tank, a fuel filter, a fuel flow meter, a fuel pressure sensor, a fuel temperature sensor, and a fuel supply valve.
3. The ground test system for liquid rocket motor-pump engines as recited in claim 2, wherein said source of pressurized fuel gas is used to regulate the pressure of working fluid prior to fuel pumping.
4. The liquid rocket motor pump engine ground test system of claim 1, wherein said oxidizer supply system comprises:
the device comprises an oxidant pressurizing gas source, an oxidant storage tank, an oxidant filter, an oxidant flowmeter, an oxidant pressure sensor, an oxidant temperature sensor and an oxidant supply valve.
5. The ground test system for liquid rocket motor-pump engines as recited in claim 4, wherein said source of oxidizer pressurized gas is used to regulate the pressure of the working fluid before the oxidizer pump.
6. The ground test system for liquid rocket motor-pump engines as defined in claim 1, wherein said motor-pump engine system comprises:
a fuel pump, an oxidizer pump, a fuel path orifice plate, an oxygen path orifice plate, a fuel path pressure sensor, an oxygen path pressure sensor, a fuel path temperature sensor, an oxygen path temperature sensor, a fuel path discharge valve, an oxygen path discharge valve, a fuel path main valve, an oxygen path main valve, and a thrust chamber.
7. The liquid rocket motor pump engine ground test system of claim 6, wherein the fuel pump and oxidizer pump are: a variable frequency motor is used for driving the variable speed booster pump;
the booster pump comprises any one of the following components: vane type, positive displacement.
8. The ground test system for liquid rocket motor-pump engines according to claim 6, wherein the fuel path orifice plate and the oxygen path orifice plate are respectively used for adjusting the flow resistance of the fuel path and the oxygen path to meet the working condition parameters of the motor-pump engine system.
9. The ground test system for liquid rocket motor-pump engines as recited in claim 1, wherein said power and control system comprises:
a power supply, a fuel pump motor driver, an oxidant pump motor driver.
10. The ground test system for the liquid rocket motor-driven pump engine according to claim 9, wherein the power supply has a voltage-adjustable function, meets the power supply requirements of the motor-driven pump motor systems with different power levels, and realizes the electric energy supply of the motor in the test process;
the fuel pump motor driver and the oxidant pump motor driver are variable frequency drivers and are used for adjusting the rotating speed of the motors, and meanwhile, the motor drivers have the function of feeding back electrical performance parameters of the fuel pump motor and the oxidant pump motor in real time;
the electrical property parameters include: operating voltage, current, power factor, input power.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN113250860A (en) * | 2021-06-19 | 2021-08-13 | 中国人民解放军国防科技大学 | Thrust control method for variable thrust rocket engine |
| CN114458478A (en) * | 2020-12-25 | 2022-05-10 | 北京天兵科技有限公司 | Double-station test bed and test method for extrusion pump pressure type rocket engine |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101126553A (en) * | 2006-06-19 | 2008-02-20 | 陈红专 | Solar boiler |
| CN104329187A (en) * | 2014-09-05 | 2015-02-04 | 西北工业大学 | Variable working condition type primary rocket system of rocket based combined cycle engine |
| CN109281774A (en) * | 2018-12-03 | 2019-01-29 | 上海空间推进研究所 | Electronic pump pressure type liquid oxygen methane space propulsion system |
| CN109630317A (en) * | 2018-12-06 | 2019-04-16 | 上海空间推进研究所 | Rail attitude control integration space propulsion system based on electrodynamic pump |
| CN109915280A (en) * | 2019-03-14 | 2019-06-21 | 北京星际荣耀空间科技有限公司 | A kind of electronic variable thrust rocket engine and the rocket with it |
| CN110749444A (en) * | 2019-09-27 | 2020-02-04 | 西安航天计量测试研究所 | Calibration system and method for aerospace liquid engine ground test testing system |
| CN210221499U (en) * | 2019-05-16 | 2020-03-31 | 南京林业大学 | Aeroengine ground test device |
-
2020
- 2020-06-02 CN CN202010490737.1A patent/CN111751115A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101126553A (en) * | 2006-06-19 | 2008-02-20 | 陈红专 | Solar boiler |
| CN104329187A (en) * | 2014-09-05 | 2015-02-04 | 西北工业大学 | Variable working condition type primary rocket system of rocket based combined cycle engine |
| CN109281774A (en) * | 2018-12-03 | 2019-01-29 | 上海空间推进研究所 | Electronic pump pressure type liquid oxygen methane space propulsion system |
| CN109630317A (en) * | 2018-12-06 | 2019-04-16 | 上海空间推进研究所 | Rail attitude control integration space propulsion system based on electrodynamic pump |
| CN109915280A (en) * | 2019-03-14 | 2019-06-21 | 北京星际荣耀空间科技有限公司 | A kind of electronic variable thrust rocket engine and the rocket with it |
| CN210221499U (en) * | 2019-05-16 | 2020-03-31 | 南京林业大学 | Aeroengine ground test device |
| CN110749444A (en) * | 2019-09-27 | 2020-02-04 | 西安航天计量测试研究所 | Calibration system and method for aerospace liquid engine ground test testing system |
Non-Patent Citations (2)
| Title |
|---|
| 王浩明: ""液体火箭发动机电动泵系统发展及性能研究"", 《火箭推进》 * |
| 魏祥庚: ""RBCC用变工况气氧/煤油引射火箭发动机设计和试验研究"", 《西北工业大学学报》 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN114458478A (en) * | 2020-12-25 | 2022-05-10 | 北京天兵科技有限公司 | Double-station test bed and test method for extrusion pump pressure type rocket engine |
| CN114458478B (en) * | 2020-12-25 | 2023-08-22 | 北京天兵科技有限公司 | Double-station test bed and test method for extrusion pump type rocket engine |
| CN113250860A (en) * | 2021-06-19 | 2021-08-13 | 中国人民解放军国防科技大学 | Thrust control method for variable thrust rocket engine |
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