CN104535305A - Constant-flow low-temperature hydrogen mixing system for launch vehicle - Google Patents
Constant-flow low-temperature hydrogen mixing system for launch vehicle Download PDFInfo
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- CN104535305A CN104535305A CN201410723867.XA CN201410723867A CN104535305A CN 104535305 A CN104535305 A CN 104535305A CN 201410723867 A CN201410723867 A CN 201410723867A CN 104535305 A CN104535305 A CN 104535305A
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Abstract
Disclosed in the invention is a constant-flow low-temperature hydrogen mixing system for a launch vehicle. The mixing system is composed of an air inlet pneumatic main ball valve 1, a pressure reducer 2, a small-flow manually-operated valve 3, a small-flow current-limiting orifice plate 4, a room-temperature mixing manually-operated valve 5, a large-flow pneumatic ball valve 6, a large-flow current-limiting orifice plate 7, and a liquid nitrogen heat exchanger 8. With the pressure reducer and the current-limiting orifice plates, obtaining and stability of the test flow can be guaranteed; and with the room-temperature mixing manually-operated valve and the liquid nitrogen heat exchanger, precooling and shunting of the room-temperature hydrogen can be realized and obtaining and guaranteeing of the low-temperature hydrogen temperature can be realized based on mixing of the room-temperature hydrogen and precooled hydrogen. According to the invention, the system with the exquisite structure can be applied to various constant-current different-temperature tests of a launch vehicle valve assembling unit successfully at the flow of 2-500g/s and the temperature of 85-250K.
Description
Technical field
The present invention relates to a kind of low temperature hydrogen compound system, for hydrogen-oxygen carrier rocket subassembly flow test, belong to cryogenic engineering test application.
Background technology
Valve, the conduit of hydrogen-oxygen carrier rocket cryogenic propellant tank need the guaranteed performance test doing true medium before rocket assembling, under the low temperature hydrogen of different flow, different temperatures, carry out the tests such as opening pressure, impermeability, vibration examination.In order to meet the requirement of low temperature hydrogen medium, need to design the low temperature hydrogen that a set of compound system obtains test corresponding requirements.
Summary of the invention
The invention provides a kind of low temperature hydrogen compound system that may be used for providing different flow, different temperatures.
The present invention is achieved in that compound system is made up of air inlet pneumatic cue ball valve, decompressor, low discharge manually-operated gate, low discharge restriction orifice, the compounding manually-operated gate of normal temperature, large discharge pneumatic ball valve, large discharge restriction orifice, liquid nitrogen heat interchanger.Air inlet pneumatic ball valve mainly plays the cutting action between normal temperature sources of hydrogen and decompressor; Decompressor mainly plays the effect of steady pressure before orifice plate; Low discharge manually-operated gate plays the effect that low discharge switches; Low discharge restriction orifice plays the stable effect of low discharge; High flow manual valve plays the effect that large discharge switches; Large discharge restriction orifice plays the stable effect of large discharge; The compounding manually-operated gate of normal temperature plays the compounding hydrogen of shunting normal temperature, for compounding air lift is for the effect of normal temperature hydrogen; Liquid nitrogen heat interchanger plays precooling normal temperature hydrogen, for compounding air lift is for the effect of low temperature hydrogen.
Outstanding advantages of the present invention: the combination utilizing the compounding valve of decompressor, orifice plate, normal temperature, cryogenic heat exchanger etc. cleverly, the low temperature hydrogen determining different temperatures under different flow can be provided, meet the demand of the different tests such as constant flow fixed temperature, constant flow temperature, variable-flow temperature.
Effect of the present invention: native system is used on Subzero valve testing table, provides flow from 2g/s-500g/s to test, the low temperature hydrogen of temperature between 85K-250K, test findings is good.
Accompanying drawing explanation
Accompanying drawing 1 is schematic diagram of the present invention.1 is the pneumatic cue ball valve of air inlet, and 2 is decompressor, and 3 is low discharge manually-operated gate, and 4 is low discharge restriction orifice, and 5 is the compounding manually-operated gate of normal temperature, and 6 is large discharge pneumatic ball valve, and 7 is large discharge restriction orifice, and 8 is liquid nitrogen heat interchanger.A is normal temperature hydrogen, and B is low temperature hydrogen, and C is low discharge path, and D is large discharge path, and E is the compounding path of normal temperature, and F is the compounding path of low temperature.
Embodiment
Illustrate below in conjunction with accompanying drawing and with embodiment, the present invention to be elaborated.
Shown in accompanying drawing, the present invention is made up of air inlet pneumatic cue ball valve 1, decompressor 2, low discharge manually-operated gate 3, low discharge restriction orifice 4, the compounding manually-operated gate 5 of normal temperature, large discharge pneumatic ball valve 6, large discharge restriction orifice 7, liquid nitrogen heat interchanger 8.For the operating condition of test of a given flow and temperature, first give decompressor 2 air feed by the pneumatic cue ball valve 1 of air inlet; Then a steady pressure is supplied by decompressor to restriction orifice prerequisite, stablizing when pressure is certain value before restriction orifice plate with regard to energy guaranteed flow; Open the compounding manually-operated gate of normal temperature to certain aperture, carry out the shunting of constant flow hydrogen; A part of hydrogen enters the precooling of liquid nitrogen heat interchanger in addition becomes low temperature hydrogen; Become low temperature hydrogen after the precooling hydrogen mixing out of normal temperature hydrogen after shunting and liquid nitrogen heat interchanger, the temperature of low temperature hydrogen is regulated by the aperture of the compounding manually-operated gate of normal temperature.Low temperature hydrogen after compounding enters testpieces and tests.Like this by the compounding supply just achieving different flow different temperatures hydrogen.
Known operating mode 1: flow 400g/s, temperature 150 ± 15K.Air inlet pneumatic ball valve 1 is opened, and large discharge pneumatic ball valve 6 is opened, and before decompressor 2 ensures large discharge restriction orifice 7, pressure is 2.55MPa, and the compounding manually-operated gate 5 of normal temperature opens half, and acquisition low temperature hydrogen flow is 400g/s, temperature is 150 ± 5K.
Known operating mode 2: flow 300g/s, temperature 120K ± 15K.Air inlet pneumatic ball valve 1 is opened, and large discharge pneumatic ball valve 6 is opened, and before decompressor 2 ensures large discharge restriction orifice 7, pressure is 1.90MPa, and the compounding manually-operated gate 5 of normal temperature is opened, and acquisition low temperature hydrogen flow is 300g/s, temperature is 150 ± 5K.
Known operating mode 3: flow 4g/s, temperature 150 ± 15K.Air inlet pneumatic ball valve 1 is opened, and low discharge manually-operated gate 3 is opened, and before decompressor 2 ensures low discharge restriction orifice 4, pressure is 2.50MPa, and the compounding manually-operated gate 5 of normal temperature is opened, and acquisition low temperature hydrogen flow is 4g/s, temperature is 150 ± 5K.
Claims (3)
1. a carrier rocket constant flow low temperature hydrogen compound system, it is characterized in that, described compound system is made up of air inlet pneumatic cue ball valve, decompressor, low discharge manually-operated gate, low discharge restriction orifice, the compounding manually-operated gate of normal temperature, large discharge pneumatic ball valve, large discharge restriction orifice, liquid nitrogen heat interchanger.Normal temperature hydrogen enters decompressor after air inlet pneumatic ball valve, is then divided into two-way, and a road enters " low discharge manually-operated gate+low discharge restriction orifice ", and a road enters " high flow manual valve+large discharge restriction orifice ", realizes constant flow; Then enter the compounding manually-operated gate of normal temperature, liquid nitrogen heat interchanger respectively, realize compounding hydrogen flow and low temperature hydrogen is produced; Last normal temperature hydrogen and low temperature hydrogen pipeline converge, and realize compounding, obtain the low temperature hydrogen of necessary requirement.
2. compound system according to claim 1, is characterized in that, adopts decompressor and restriction orifice to guarantee the flow of hydrogen.
3. compound system according to claim 1, it is characterized in that, adopt the precooling that normal temperature compounding valve realizes the shunting of normal temperature hydrogen, liquid nitrogen heat interchanger realizes normal temperature hydrogen, the compounding temperature that ensure that low temperature hydrogen of adjustment of shunting normal temperature hydrogen and precooling hydrogen.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410723867.XA CN104535305A (en) | 2014-12-04 | 2014-12-04 | Constant-flow low-temperature hydrogen mixing system for launch vehicle |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410723867.XA CN104535305A (en) | 2014-12-04 | 2014-12-04 | Constant-flow low-temperature hydrogen mixing system for launch vehicle |
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| CN104535305A true CN104535305A (en) | 2015-04-22 |
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| CN201410723867.XA Pending CN104535305A (en) | 2014-12-04 | 2014-12-04 | Constant-flow low-temperature hydrogen mixing system for launch vehicle |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107192540A (en) * | 2016-03-15 | 2017-09-22 | 北京强度环境研究所 | Band net compensator pipe-line system stiffness characteristics experimental rig |
| CN107270270A (en) * | 2017-07-21 | 2017-10-20 | 中国核动力研究设计院 | Close-coupled steam generator secondary side thermal parameter stabilization control device |
| CN107843434A (en) * | 2017-10-18 | 2018-03-27 | 西安航天动力试验技术研究所 | Liquid propellant rocket engine test low temperature low discharge chilldown system and forecooling method |
| CN110821710A (en) * | 2019-10-28 | 2020-02-21 | 西安航天动力试验技术研究所 | Rocket engine test inlet pressure rapid pressurizing device and liquid oxygen supply system |
| CN112110060A (en) * | 2020-07-31 | 2020-12-22 | 北京航天试验技术研究所 | Low-temperature filling platform and automatic filling method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107192540A (en) * | 2016-03-15 | 2017-09-22 | 北京强度环境研究所 | Band net compensator pipe-line system stiffness characteristics experimental rig |
| CN107270270A (en) * | 2017-07-21 | 2017-10-20 | 中国核动力研究设计院 | Close-coupled steam generator secondary side thermal parameter stabilization control device |
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| CN107843434A (en) * | 2017-10-18 | 2018-03-27 | 西安航天动力试验技术研究所 | Liquid propellant rocket engine test low temperature low discharge chilldown system and forecooling method |
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| CN110821710A (en) * | 2019-10-28 | 2020-02-21 | 西安航天动力试验技术研究所 | Rocket engine test inlet pressure rapid pressurizing device and liquid oxygen supply system |
| CN110821710B (en) * | 2019-10-28 | 2020-08-21 | 西安航天动力试验技术研究所 | Rocket engine test inlet pressure rapid pressurizing device and liquid oxygen supply system |
| CN112110060A (en) * | 2020-07-31 | 2020-12-22 | 北京航天试验技术研究所 | Low-temperature filling platform and automatic filling method thereof |
| CN112110060B (en) * | 2020-07-31 | 2022-05-27 | 北京航天试验技术研究所 | Low-temperature filling platform and automatic filling method thereof |
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Application publication date: 20150422 |