CN203616128U - Testing system of liquid rocket supercritical helium supercharging - Google Patents
Testing system of liquid rocket supercritical helium supercharging Download PDFInfo
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- CN203616128U CN203616128U CN201320739693.7U CN201320739693U CN203616128U CN 203616128 U CN203616128 U CN 203616128U CN 201320739693 U CN201320739693 U CN 201320739693U CN 203616128 U CN203616128 U CN 203616128U
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- orifice plate
- helium
- supercharging
- tank
- liquid helium
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- 239000001307 helium Substances 0.000 title claims abstract description 108
- 229910052734 helium Inorganic materials 0.000 title claims abstract description 108
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 title claims abstract description 108
- 239000007788 liquid Substances 0.000 title claims abstract description 75
- 238000010438 heat treatment Methods 0.000 claims abstract description 12
- 238000006073 displacement reaction Methods 0.000 claims abstract description 11
- 239000000945 filler Substances 0.000 claims description 3
- 239000003638 chemical reducing agent Substances 0.000 abstract 1
- 238000000034 method Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000005429 filling process Methods 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
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- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The utility model discloses a testing system of liquid rocket supercritical helium supercharging. The testing system comprises a helium tank (1), a normal temperature solenoid valve (2), a pressure reducer (3), an orifice plate front pressure gauge (41), an orifice plate rear pressure gauge (42), a normal temperature supercharging orifice plate (5), a liquid helium storage tank (6), a liquid helium storage tank pressure gauge (7), a liquid helium storage tank thermometer (8), an electronic scale (9), a heating heat exchanger (10), a stop valve (11), a supercharging solenoid valve (12), a displacement pipeline (13), a low temperature supercharging orifice plate (14), a flowmeter (15), a storage tank (16), a storage tank pressure gauge (17), a storage tank thermometer (18), an exhaust solenoid valve (19), and an exhaust orifice plate (20). The testing system of liquid rocket supercritical helium supercharging can check matching performance of a supercritical helium supercharging system, obtains a rule of a relation of the supercritical helium filling amount and the normal temperature supercharging air amount, and reveals difficulties of applying the testing system to a rocket in the future.
Description
Technical field
The utility model belongs to rocket ground experiment technical field, is specifically related to the pilot system of a kind of liquid rocket supercritical helium supercharging.
Background technology
The supercritical helium Pressurization scheme of heating utilizes normal temperature helium to carry out pre-supercharging to liquid helium, makes liquid helium be pressurized to supercriticality, after then heating to tank supercharging.The helium that the helium that this supercharging form is stored is stored more than other helium supercharging form is many, and for rocket structure weight limits, supercritical helium pressure charging system is optimum selection.For supercritical helium pressure charging system is applied to following rocket, need to study supercritical helium liquid rocket pressure charging system performance and matching.
Utility model content
Technical problem to be solved in the utility model is to provide the pilot system of a kind of liquid rocket supercritical helium supercharging, can examine the heat matching of pressure charging system of supercritical helium, obtain the rule that is related to of supercritical helium adding amount and normal temperature supercharging tolerance, expose and be applied to the existing difficult point of rocket future.
The utility model comprises following technical scheme:
A pilot system for liquid rocket supercritical helium supercharging, comprises tensimeter after tensimeter before helium tank, normal temperature solenoid valve, decompressor, orifice plate, orifice plate, normal temperature supercharging orifice plate, liquid helium basin, liquid helium sump pressure table, liquid helium basin thermometer, electronic scales, the heat interchanger of heating, stop valve, boost electromagnetic valve, displacement pipeline, low temperature supercharging orifice plate, flowmeter, tank, tank tensimeter, tank thermometer, exhaust solenoid valve and vent panel;
Liquid helium basin is used for storing liquid helium, and helium tank is connected with the filler of liquid helium basin with normal temperature supercharging orifice plate by normal temperature solenoid valve, decompressor successively, before normal temperature supercharging orifice plate, be provided with orifice plate before tensimeter, after normal temperature supercharging orifice plate, be provided with orifice plate after tensimeter; Liquid helium basin is placed on electronic scales, and liquid helium basin is provided with liquid helium sump pressure table and liquid helium basin thermometer; The boost port of liquid helium basin is connected with tank entrance by the heat interchanger of heating, boost electromagnetic valve, low temperature supercharging orifice plate, flowmeter successively, and tank is provided with tank tensimeter and tank thermometer; The outlet of tank connects exhaust solenoid valve and vent panel; Between pipeline after pipeline and boost electromagnetic valve after orifice plate after tensimeter, be provided with displacement pipeline, and be provided with stop valve at this displacement pipeline.
Described boost electromagnetic valve is at least two, low temperature supercharging orifice plate and is at least two, a set of pressure piping of composition after one of them boost electromagnetic valve and the series connection of one of them low temperature supercharging orifice plate, and in parallel with another set of pressure piping.
The utility model compared with prior art tool has the following advantages:
Pressurized test system of the present utility model comprises tensimeter after tensimeter before helium tank, normal temperature solenoid valve, decompressor, orifice plate, orifice plate, normal temperature supercharging orifice plate, liquid helium basin, liquid helium sump pressure table, liquid helium basin thermometer, electronic scales, the heat interchanger of heating, stop valve, boost electromagnetic valve, displacement pipeline, low temperature supercharging orifice plate, flowmeter, tank, tank tensimeter, tank thermometer, exhaust solenoid valve and vent panel; Thereby make system of the present utility model can examine the matching of supercritical helium pressure charging system; Can analyze the rule that is related to of supercritical helium adding amount and normal temperature extruding tolerance; Can analyze normal temperature supercharging road fluctuations in discharge; Temperature and pressure that the utility model can be analyzed the filling of liquid helium basin, pressurization change; The utility model can expose and be applied to the existing difficult point of rocket future.
Accompanying drawing explanation
Fig. 1 is supercritical helium liquid rocket pressurized test system diagram of the present utility model.
Embodiment
Just by reference to the accompanying drawings the utility model is described further below.
As shown in Figure 1, supercritical helium liquid rocket pressurized test system described in the utility model comprises tensimeter 42 after tensimeter 41 before helium tank 1, normal temperature solenoid valve 2, decompressor 3, orifice plate, orifice plate, normal temperature supercharging orifice plate 5, liquid helium basin 6, liquid helium sump pressure table 7, liquid helium basin thermometer 8, electronic scales 9, the heat interchanger 10 of heating, stop valve 11, boost electromagnetic valve 12, displacement pipeline 13, low temperature supercharging orifice plate 14, flowmeter 15, tank 16, tank tensimeter 17, tank thermometer 18, exhaust solenoid valve 19, vent panel 20.
Before test, liquid helium is filled in liquid helium basin 6, helium tank 1 is connected with the filler of liquid helium basin 6 with normal temperature supercharging orifice plate 5 by normal temperature solenoid valve 2, decompressor 3, normal temperature supercharging orifice plate 5 front and back are provided with before orifice plate tensimeter 42 after tensimeter 41 and orifice plate, liquid helium basin 6 is placed on electronic scales 9, and liquid helium basin 6 is provided with liquid helium sump pressure table 7 and liquid helium basin thermometer 8; The boost port of liquid helium basin 6 is connected with tank 16 entrances by the heat interchanger 10 of heating, boost electromagnetic valve 12, low temperature supercharging orifice plate 14, flowmeter 15, and tank 16 is provided with tank tensimeter 17 and tank thermometer 18; Tank 16 upper ends connect exhaust solenoid valve 19 and vent panel 20.For the pipeline after boost electromagnetic valve 12 is replaced, after orifice plate, after tensimeter 42, be provided with displacement pipeline 13 and be connected with the pipeline after boost electromagnetic valve 12, this section of pipeline is provided with stop valve 11.
The course of work of this pilot system is as follows:
A) the liquid helium filling process of liquid helium basin 6: guarantee that normal temperature solenoid valve 2, stop valve 11, boost electromagnetic valve 12 and exhaust solenoid valve 19 are in closed condition.To the liquid helium of annotating in liquid helium basin 6, record the weight of liquid helium in basin by liquid helium filling apparatus by electronic scale 9.
B) replacement process of pipeline: in system work process, the air setting in pipeline freezes, and causes boost electromagnetic valve 12 operation irregularities is replaced pipeline by displacement pipeline 13 before official test; Open stop valve 11, pipeline and tank 16 after boost electromagnetic valve 12 fill normal temperature helium, then close stop valve 11, open exhaust solenoid valve 19 and carry out exhaust, repeat to close stop valve 11 and exhaust solenoid valve 19 after this process 3 to 5 times.
C) pressurization of normal temperature helium to liquid helium basin 6: when on-test, guarantee that boost electromagnetic valve 12 is in closed condition, open normal temperature solenoid valve 2, regulate decompressor 3, by normal temperature supercharging orifice plate 5 by the normal temperature helium in helium tank 1 with certain pressure to the liquid helium supercharging in liquid helium basin 6, make the 4.2K normal pressure helium in liquid helium basin 6 reach supercriticality by supercharging, by recording the manometric reading of normal temperature supercharging orifice plate 5 front and back, calculate normal temperature supercharging amount of helium in liquid helium basin 6 pressurizations;
D) pressurization of tank 16: when the liquid helium in liquid helium basin 6 reaches supercriticality, open boost electromagnetic valve 12, supercritical helium is extruded from liquid helium basin 6, by heating, heat interchanger 10 is heated into low temperature helium, pass through again low temperature supercharging orifice plate 14 and flowmeter 15 to tank 16 superchargings, open the outside exhaust of exhaust solenoid valve 19 simultaneously, the case that maintains tank 16 is pressed stable, measure the helium gas flow to tank 16 superchargings by flowmeter 15, calculate the discharge of liquid helium in liquid helium basin 6 by the data variation of observation electronic scales 9, monitor the case of tank presses and case temperature value by the tank tensimeter 17 on tank 16 and tank thermometer 18.
E) the supercharging terminal procedure of tank; Close normal temperature solenoid valve 2 and boost electromagnetic valve 12, keep exhaust solenoid valve 19 to open;
F) data handling procedure; Can obtain normal temperature supercharging amount of helium by step c; By steps d can draw the discharge of liquid helium basin 6 interior liquid heliums, to the helium boosted flow of tank 16 and the Pressure Variation of tank 16.Regulate according to demand the rear pressure of decompressor 3, change normal temperature supercharging road flow, draw the rule that affects on normal temperature boost performance; Change liquid helium adding amount, draw the Changing Pattern of the interior liquid helium amount of liquid helium basin 6 and normal temperature supercharging amount of helium, investigate the supercritical helium pressure charging system matching of heating, exposure will be applied to the existing difficult point of rocket future.
The unspecified part of the utility model belongs to general knowledge as well known to those skilled in the art.
Claims (2)
1. the pilot system of liquid rocket supercritical helium supercharging, it is characterized in that, comprise helium tank (1), normal temperature solenoid valve (2), decompressor (3), tensimeter (41) before orifice plate, tensimeter after orifice plate (42), normal temperature supercharging orifice plate (5), liquid helium basin (6), liquid helium sump pressure table (7), liquid helium basin thermometer (8), electronic scales (9), the heat interchanger (10) of heating, stop valve (11), boost electromagnetic valve (12), displacement pipeline (13), low temperature supercharging orifice plate (14), flowmeter (15), tank (16), tank tensimeter (17), tank thermometer (18), exhaust solenoid valve (19) and vent panel (20),
Liquid helium basin (6) is for storing liquid helium, helium tank (1) is connected with the filler of liquid helium basin (6) with normal temperature supercharging orifice plate (5) by normal temperature solenoid valve (2), decompressor (3) successively, normal temperature supercharging orifice plate (5) is front be provided with orifice plate before tensimeter (41), after normal temperature supercharging orifice plate (5), be provided with orifice plate after tensimeter (42); It is upper that liquid helium basin (6) is placed on electronic scales (9), and liquid helium basin (6) is provided with liquid helium sump pressure table (7) and liquid helium basin thermometer (8); The boost port of liquid helium basin (6) is connected with tank (16) entrance by the heat interchanger of heating (10), boost electromagnetic valve (12), low temperature supercharging orifice plate (14), flowmeter (15) successively, and tank (16) is provided with tank tensimeter (17) and tank thermometer (18); The outlet of tank (16) connects exhaust solenoid valve (19) and vent panel (20); Between pipeline after pipeline after tensimeter after orifice plate (42) and boost electromagnetic valve (12), be provided with displacement pipeline (13), and be provided with stop valve (11) at this displacement pipeline (13).
2. the pilot system of a kind of liquid rocket supercritical helium according to claim 1 supercharging, it is characterized in that, described boost electromagnetic valve (12) is at least two, low temperature supercharging orifice plate (14) and is at least two, the a set of pressure piping of composition after one of them boost electromagnetic valve (12) and the series connection of one of them low temperature supercharging orifice plate (14), and in parallel with another set of pressure piping.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320739693.7U CN203616128U (en) | 2013-11-20 | 2013-11-20 | Testing system of liquid rocket supercritical helium supercharging |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320739693.7U CN203616128U (en) | 2013-11-20 | 2013-11-20 | Testing system of liquid rocket supercritical helium supercharging |
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| CN203616128U true CN203616128U (en) | 2014-05-28 |
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| CN201320739693.7U Expired - Lifetime CN203616128U (en) | 2013-11-20 | 2013-11-20 | Testing system of liquid rocket supercritical helium supercharging |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104215467A (en) * | 2014-09-19 | 2014-12-17 | 北京宇航系统工程研究所 | Ground testing system for verifying function of pressurizing system |
| CN104215520A (en) * | 2014-08-22 | 2014-12-17 | 北京宇航系统工程研究所 | Low-temperature inner pressure test checking method for low-temperature storage box under heat insulation structure-free state |
| CN104792233A (en) * | 2015-04-29 | 2015-07-22 | 北京航天发射技术研究所 | Supercharging device and supercharging method for low-temperature rocket ground redundancy |
| CN105444973A (en) * | 2015-11-17 | 2016-03-30 | 上海航天精密机械研究所 | Low-temperature-pressure automatic pressure-increasing balance device |
| CN105650461A (en) * | 2016-01-06 | 2016-06-08 | 北京航天发射技术研究所 | Inflation system for rocket low-temperature gas cylinder |
| CN105806443A (en) * | 2014-12-30 | 2016-07-27 | 北京强度环境研究所 | Waggle test storage tank liquid level measuring system |
| CN110470365A (en) * | 2019-08-16 | 2019-11-19 | 北京航天计量测试技术研究所 | The determination method, apparatus and computer storage medium of orifice flow constant characteristic |
| CN116006358A (en) * | 2022-12-30 | 2023-04-25 | 北京天兵科技有限公司 | Cold helium pressurization ground test system and method |
| CN116046377A (en) * | 2022-12-30 | 2023-05-02 | 北京天兵科技有限公司 | Rocket oxygen safety valve opening and closing performance test system and test method |
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2013
- 2013-11-20 CN CN201320739693.7U patent/CN203616128U/en not_active Expired - Lifetime
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104215520B (en) * | 2014-08-22 | 2016-08-24 | 北京宇航系统工程研究所 | Cryogenic tank is without the low temperature inner pressure test wire examination method under heat insulating construction state |
| CN104215520A (en) * | 2014-08-22 | 2014-12-17 | 北京宇航系统工程研究所 | Low-temperature inner pressure test checking method for low-temperature storage box under heat insulation structure-free state |
| CN104215467A (en) * | 2014-09-19 | 2014-12-17 | 北京宇航系统工程研究所 | Ground testing system for verifying function of pressurizing system |
| CN104215467B (en) * | 2014-09-19 | 2016-08-17 | 北京宇航系统工程研究所 | A kind of ground system test for verifying pressure charging system function |
| CN105806443B (en) * | 2014-12-30 | 2022-04-19 | 北京强度环境研究所 | Liquid level measuring system of shaking test storage tank |
| CN105806443A (en) * | 2014-12-30 | 2016-07-27 | 北京强度环境研究所 | Waggle test storage tank liquid level measuring system |
| CN104792233A (en) * | 2015-04-29 | 2015-07-22 | 北京航天发射技术研究所 | Supercharging device and supercharging method for low-temperature rocket ground redundancy |
| CN105444973A (en) * | 2015-11-17 | 2016-03-30 | 上海航天精密机械研究所 | Low-temperature-pressure automatic pressure-increasing balance device |
| CN105444973B (en) * | 2015-11-17 | 2018-06-26 | 上海航天精密机械研究所 | Low-temperature pressure Automatic-boosting balancing device |
| CN105650461B (en) * | 2016-01-06 | 2019-01-25 | 北京航天发射技术研究所 | System for the inflation of rocket low temperature cylinder |
| CN105650461A (en) * | 2016-01-06 | 2016-06-08 | 北京航天发射技术研究所 | Inflation system for rocket low-temperature gas cylinder |
| CN110470365A (en) * | 2019-08-16 | 2019-11-19 | 北京航天计量测试技术研究所 | The determination method, apparatus and computer storage medium of orifice flow constant characteristic |
| CN116006358A (en) * | 2022-12-30 | 2023-04-25 | 北京天兵科技有限公司 | Cold helium pressurization ground test system and method |
| CN116046377A (en) * | 2022-12-30 | 2023-05-02 | 北京天兵科技有限公司 | Rocket oxygen safety valve opening and closing performance test system and test method |
| CN116006358B (en) * | 2022-12-30 | 2024-06-11 | 北京天兵科技有限公司 | Cold helium pressurization ground test system and method |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
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Granted publication date: 20140528 |