CN103278330A - Propellant flow comparison and measurement system for attitude and orbit control engine testing platform - Google Patents
Propellant flow comparison and measurement system for attitude and orbit control engine testing platform Download PDFInfo
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- CN103278330A CN103278330A CN2013101438659A CN201310143865A CN103278330A CN 103278330 A CN103278330 A CN 103278330A CN 2013101438659 A CN2013101438659 A CN 2013101438659A CN 201310143865 A CN201310143865 A CN 201310143865A CN 103278330 A CN103278330 A CN 103278330A
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Abstract
The invention discloses a propellant flow comparison and measurement system for an attitude and orbit control engine testing platform. The propellant flow comparison and measurement system comprises a test trolley storage tank, a liquid outlet manual valve, a turbine flowmeter 1, a turbine flowmeter 2, a mass flowmeter 1, a mass flowmeter 2, an electromagnetic valve, a pore plate, a weighing vessel, a high-precision electronic scale, a microcomputer acquisition system and a liquid return valve, wherein the stress conditions of pipelines and flowmeters during actual engine test are subjected to pressurized simulation, and the actual flow resistance is simulated by using the pore plate; a propellant flows into the weighing vessel from the test trolley storage tank through the liquid outlet manual valve, the turbine flowmeter 1, the turbine flowmeter 2, the mass flowmeter 1, the mass flowmeter 2, the electromagnetic valve and the pore plate; voltage signals measured by the microcomputer acquisition system are compared with data measured by the high-precision electronic scale so as to obtain formulae of all the flowmeters; and after the comparison is completed, the propellant returns to the test trolley storage tank from the weighing vessel through the liquid return valve and the liquid outlet manual valve.
Description
Technical field
The present invention relates to a kind of flow comparison system of weighing, relate in particular to a kind of spacecraft rail control engine test Flow Measuring System, belong to parameter measuring technical field.
Background technology
The rail control engine is as attitude and the track control engine of spacecrafts such as satellite, and the flow measurement precision can exert an influence to the specific impulse precision in its heat mark test, thereby the control accuracy that has influence on spacecraft reached in the rail life-span.Tradition flow comparison system makes water as medium, the inconsistent of medium may bring influence to measurement, therefore needs development one cover directly to use propellant as the throughput ratio of medium measuring system to be finished the comparison of rail control engine test flowmeter is demarcated.
Summary of the invention
Directly use propellant (oxygenant: dinitrogen tetroxide, fuel: MMH) as working medium.Oxygenant and fuel adopt two circuits systems, and the system of two circuits systems forms consistent, and its system schematic is seen accompanying drawing 1.Pipeline and flowmeter pressurized situation utilize orifice plate to simulate actual flow resistance during by the test of supercharging simulation real engine.N2O4 is volatile propellant, and adopting builds the pressure weighs, and with the folding of programmed control solenoid valve, builds with pressure transducer and to press and release judgement time constantly.Dinitrogen tetroxide and MMH have strong toxicity, require the sealing agent corrosion resistivity of pipe system good.Use propellant actual alignment flowmeter, overcome the deficiency of existing metrological service water calibration, provide a kind of throughput ratio to measuring system, this measuring system is formed simply, measuring accuracy is high.
Technical solution of the present invention is: pipeline tapping filling; Rated pressure when boost pressure is adjusted to the rail control engine run; Regulate the orifice plate aperture, with its simulated engine flow resistance; Mass flowmeter zero setting; High-precision electronic scale and mass flowmeter (accumulative total quality) initial value reading; The microcomputer acquisition system is gathered correlation parameter; The Controlled by Programmable Controller solenoid valve is opened time rating; The microcomputer acquisition system stops to gather; High-precision electronic scale and mass flowmeter (accumulative total quality) stop value reading; The release of propellant test run storage tank; The container propellant of weighing returns crowded.
The present invention's advantage compared with prior art is:
(1) propellant that directly uses engine test to use is calibrated, and does not need the formula conversion, and precision is higher;
Pipeline and flowmeter pressurized situation utilize orifice plate to simulate actual flow resistance during (2) by the test of supercharging simulation real engine;
(3) employing builds the pressure and weighs, and can prevent the propellant volatilization.
(4) turbo flow meter 1, turbo flow meter 2, mass flowmeter 1, mass flowmeter 2 online comparisons simultaneously increase their data consistency.
Description of drawings
Accompanying drawing is that rail control engine test plateau propellant throughput ratio is to measuring system figure;
Among the figure:
1. test run storage tank 2. fluid hand valves 3. turbo flow meters 1
4. turbo flow meter 2 5. mass flowmeters 1 6. mass flowmeters 2
7. microcomputer acquisition system 8. solenoid valves 9. orifice plates
10. return the liquid valve 11. container 12. high-precision electronic scales of weighing
Embodiment
System of the present invention forms as shown in Figure 1: comprising: test run storage tank (1), fluid hand valve (2), turbo flow meter 1 (3), turbo flow meter 2 (4), mass flowmeter 1 (5), mass flowmeter 2 (6), microcomputer acquisition system (7), solenoid valve (8), orifice plate (9), time liquid valve (10), the container of weighing (11), high-precision electronic scale (12).
Pipeline and flowmeter (3,4,5,6) pressurized situation utilize orifice plate (9) to simulate actual flow resistance during by the test of supercharging simulation real engine.Propellant flows into the container (11) of weighing by test run storage tank (1) through fluid hand valve (2), turbo flow meter 1 (3), turbo flow meter 2 (4), mass flowmeter 1 (5), mass flowmeter 2 (6), solenoid valve (8), orifice plate (9).The voltage signal that microcomputer acquisition system (7) is measured is compared with the data that high-precision electronic scale (12) is measured, obtain the formula of each flowmeter.Comparison finishes the back propellant and gets back to test run storage tank (1) from the container of weighing (11) by returning liquid valve (10) and fluid hand valve (2).
During comparison, carry out successively: pipeline tapping filling; Rated pressure when boost pressure is adjusted to the rail control engine run; Regulate orifice plate aperture (9), with its simulated engine flow resistance; Mass flowmeter (5,6) zero setting; High-precision electronic scale (12) and mass flowmeter (5,6) accumulative total quality initial value reading; Microcomputer acquisition system (7) is gathered correlation parameter; Controlled by Programmable Controller solenoid valve (8) is opened time rating; Microcomputer acquisition system (7) stops to gather; Record high-precision electronic scale (12) and mass flowmeter (5,6) accumulative total quality stop value reading; Propellant test run storage tank release (1); Container (11) propellant of weighing returns crowded.
Institute's employing solenoid valve (8) response time is a few tens of milliseconds, is not more than 50ms; The response time difference of opening and closing should be not more than 10ms, and its error can be ignored for 500 (1000) s like this.High-precision electronic scale (12) precision that adopts: range 300kg, gauge outfit display resolution 1g.Weigh container (11) (dinitrogen tetroxide, methyl hydrazine volume all are not less than 1001, the deadweight 150kg in, the withstand voltage 3MPa that is not less than).
The present invention not detailed description is technology as well known to those skilled in the art.
Claims (4)
1. a rail control engine test plateau propellant throughput ratio is characterized in that measuring system: directly use propellant (oxygenant: dinitrogen tetroxide, fuel: MMH) as working medium; System comprises: test run storage tank, fluid hand valve, turbo flow meter 1, turbo flow meter 2, mass flowmeter 1, mass flowmeter 2, solenoid valve, orifice plate, the container of weighing, high-precision electronic scale, microcomputer acquisition system, time liquid valve; Propellant flows into the container of weighing by the test run storage tank through fluid hand valve, turbo flow meter 1, turbo flow meter 2, mass flowmeter 1, mass flowmeter 2, solenoid valve, orifice plate; The voltage signal that the microcomputer acquisition system is measured is compared with the data that the high-precision electronic scale is measured, obtain the formula of each flowmeter; Comparison finishes the back propellant and gets back to the test run storage tank from the container of weighing by returning liquid valve and fluid hand valve.
2. pipeline and flowmeter pressurized situation utilize orifice plate to simulate actual flow resistance during by the test of supercharging simulation real engine.
3. adopt to build the pressure and weigh, prevent the propellant volatilization.
4. turbo flow meter 1, turbo flow meter 2, mass flowmeter 1, mass flowmeter 2 online comparisons simultaneously increase their data consistency.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN2013101438659A CN103278330A (en) | 2013-04-24 | 2013-04-24 | Propellant flow comparison and measurement system for attitude and orbit control engine testing platform |
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| Application Number | Priority Date | Filing Date | Title |
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| CN2013101438659A CN103278330A (en) | 2013-04-24 | 2013-04-24 | Propellant flow comparison and measurement system for attitude and orbit control engine testing platform |
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| CN103278330A true CN103278330A (en) | 2013-09-04 |
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| CN2013101438659A Pending CN103278330A (en) | 2013-04-24 | 2013-04-24 | Propellant flow comparison and measurement system for attitude and orbit control engine testing platform |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106568484A (en) * | 2016-11-02 | 2017-04-19 | 北京控制工程研究所 | Self-controlled flow test device |
| CN107131931A (en) * | 2017-06-06 | 2017-09-05 | 西安航天动力试验技术研究所 | Attitude control engine high-temperature propellant steady state flow calibrated in situ device and calibration method |
| CN107607325A (en) * | 2017-09-04 | 2018-01-19 | 西安航天动力研究所 | Pin fastens formula ejector filler Variable Thrust Engine System Operating condition adjustment method |
| CN107843330A (en) * | 2017-12-08 | 2018-03-27 | 上海悟道机电设备有限公司 | The measuring apparatus that a kind of flow is weighed |
| CN107941307A (en) * | 2017-11-10 | 2018-04-20 | 西安航天动力试验技术研究所 | A kind of large-scale liquid engine propellant flow rate field calibration system and method for routine |
| CN110260931A (en) * | 2019-06-18 | 2019-09-20 | 西安航天动力试验技术研究所 | A kind of liquid propellant pipeline flow field quality evaluation system and evaluation method |
| CN110895200A (en) * | 2018-09-12 | 2020-03-20 | 北京振兴计量测试研究所 | On-site calibration system for test bed of aerospace engine and calibration method for measurement and control unit of on-site calibration system |
| CN114087525A (en) * | 2021-11-09 | 2022-02-25 | 浙江浙能技术研究院有限公司 | Air pressure driven differential mass method liquid hydrogen accumulated flow standard device |
| CN114383851A (en) * | 2021-12-31 | 2022-04-22 | 西安航天动力研究所 | Multi-hole synchronous collecting and weighing device and method for attitude and orbit control engine product |
| CN114383852A (en) * | 2021-12-31 | 2022-04-22 | 西安航天动力研究所 | Testing device for automatic synchronous collection and clamping of attitude and orbit control engine product |
| CN114414252A (en) * | 2021-12-31 | 2022-04-29 | 西安航天动力研究所 | Automatic multi-hole jet flow synchronous collecting device for attitude and orbit control engine product |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106568484B (en) * | 2016-11-02 | 2019-09-06 | 北京控制工程研究所 | A kind of control flow testing device certainly |
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| CN107607325A (en) * | 2017-09-04 | 2018-01-19 | 西安航天动力研究所 | Pin fastens formula ejector filler Variable Thrust Engine System Operating condition adjustment method |
| CN107941307B (en) * | 2017-11-10 | 2021-02-26 | 西安航天动力试验技术研究所 | Propellant flow field calibration system and method for conventional large-scale liquid engine |
| CN107941307A (en) * | 2017-11-10 | 2018-04-20 | 西安航天动力试验技术研究所 | A kind of large-scale liquid engine propellant flow rate field calibration system and method for routine |
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| CN110895200A (en) * | 2018-09-12 | 2020-03-20 | 北京振兴计量测试研究所 | On-site calibration system for test bed of aerospace engine and calibration method for measurement and control unit of on-site calibration system |
| CN110895200B (en) * | 2018-09-12 | 2021-08-27 | 北京振兴计量测试研究所 | On-site calibration system for test bed of aerospace engine and calibration method for measurement and control unit of on-site calibration system |
| CN110260931A (en) * | 2019-06-18 | 2019-09-20 | 西安航天动力试验技术研究所 | A kind of liquid propellant pipeline flow field quality evaluation system and evaluation method |
| CN114087525A (en) * | 2021-11-09 | 2022-02-25 | 浙江浙能技术研究院有限公司 | Air pressure driven differential mass method liquid hydrogen accumulated flow standard device |
| CN114383851A (en) * | 2021-12-31 | 2022-04-22 | 西安航天动力研究所 | Multi-hole synchronous collecting and weighing device and method for attitude and orbit control engine product |
| CN114383852A (en) * | 2021-12-31 | 2022-04-22 | 西安航天动力研究所 | Testing device for automatic synchronous collection and clamping of attitude and orbit control engine product |
| CN114414252A (en) * | 2021-12-31 | 2022-04-29 | 西安航天动力研究所 | Automatic multi-hole jet flow synchronous collecting device for attitude and orbit control engine product |
| CN114383851B (en) * | 2021-12-31 | 2023-08-25 | 西安航天动力研究所 | Multi-hole synchronous collecting and weighing device and method for attitude and orbit control engine product |
| CN114383852B (en) * | 2021-12-31 | 2023-08-25 | 西安航天动力研究所 | Test device for automatically and synchronously collecting and clamping attitude and orbit control engine product |
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Application publication date: 20130904 |