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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- 239000001307 helium Substances 0.000 title claims abstract description 107
- 229910052734 helium Inorganic materials 0.000 title claims abstract description 107
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 title claims abstract description 107
- 239000007788 liquid Substances 0.000 title claims abstract description 73
- 238000010438 heat treatment Methods 0.000 claims abstract description 13
- 239000003638 chemical reducing agent Substances 0.000 claims abstract description 10
- 238000006073 displacement reaction Methods 0.000 claims 2
- 235000015842 Hesperis Nutrition 0.000 abstract description 5
- 235000012633 Iberis amara Nutrition 0.000 abstract description 5
- 239000007789 gas Substances 0.000 abstract description 3
- 238000000034 method Methods 0.000 description 10
- 238000009833 condensation Methods 0.000 description 1
- 230000005494 condensation Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 238000005429 filling process Methods 0.000 description 1
- 230000008014 freezing Effects 0.000 description 1
- 238000007710 freezing Methods 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
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Abstract
本实用新型公开了一种液体火箭超临界氦增压的试验系统，包括氦气瓶（1）、常温电磁阀（2）、减压器（3）、孔板前压力表（41）、孔板后压力表（42）、常温增压孔板（5）、液氦贮罐（6）、液氦贮罐压力表（7）、液氦贮罐温度计（8）、电子秤（9）、加温换热器（10）、截止阀（11）、增压电磁阀（12）、置换管路（13）、低温增压孔板（14）、流量计（15）、贮箱（16）、贮箱压力表（17）、贮箱温度计（18）、排气电磁阀（19）、排气孔板（20）。本实用新型能够考核超临界氦加温增压系统的匹配性，得到超临界氦加注量与常温增压气量的关系规律，暴露未来应用于火箭所存在的难点。
The utility model discloses a test system for liquid rocket supercritical helium pressurization, which comprises a helium cylinder (1), a normal temperature electromagnetic valve (2), a pressure reducer (3), a pressure gauge in front of an orifice plate (41), an orifice plate Rear pressure gauge (42), normal temperature pressurized orifice plate (5), liquid helium storage tank (6), liquid helium storage tank pressure gauge (7), liquid helium storage tank thermometer (8), electronic scale (9), plus Temperature heat exchanger (10), cut-off valve (11), booster solenoid valve (12), replacement pipeline (13), low-temperature booster orifice plate (14), flow meter (15), storage tank (16), Storage tank pressure gauge (17), storage tank thermometer (18), exhaust solenoid valve (19), exhaust orifice plate (20). The utility model can examine the matching property of the supercritical helium heating and pressurizing system, obtain the relationship law between the supercritical helium filling amount and the normal temperature pressurizing gas volume, and expose the difficulties existing in the future application to rockets.
Description
技术领域technical field
本实用新型属于火箭地面试验技术领域，具体涉及一种液体火箭超临界氦增压的试验系统。The utility model belongs to the technical field of rocket ground tests, in particular to a test system for liquid rocket supercritical helium pressurization.
背景技术Background technique
超临界氦加温增压方案利用常温氦气对液氦进行预增压，使液氦增压至超临界状态，然后加温后对贮箱增压。这种增压形式贮存的氦气远比其它氦气增压形式贮存的氦气多，对于火箭结构重量限制而言，超临界氦增压系统是最优的选择。为了将超临界氦增压系统应用到未来火箭，需要对超临界氦液体火箭增压系统性能及匹配性进行研究。The supercritical helium heating and pressurization scheme uses normal temperature helium to pre-pressurize the liquid helium, pressurize the liquid helium to a supercritical state, and then pressurize the storage tank after heating. The helium stored in this pressurized form is far more than that stored in other helium pressurized forms. For the structural weight limit of the rocket, the supercritical helium pressurized system is the best choice. In order to apply the supercritical helium supercharging system to future rockets, it is necessary to study the performance and matching of the supercritical helium liquid rocket supercharging system.
实用新型内容Utility model content
本实用新型所要解决的技术问题是提供一种液体火箭超临界氦增压的试验系统，能够考核超临界氦加温增压系统的匹配性，得到超临界氦加注量与常温增压气量的关系规律，暴露未来应用于火箭所存在的难点。The technical problem to be solved by the utility model is to provide a liquid rocket supercritical helium pressurized test system, which can check the compatibility of the supercritical helium heating and pressurizing system, and obtain the relationship between the supercritical helium filling volume and the normal temperature pressurization gas volume. The law of relationship exposes the difficulties in applying it to rockets in the future.
本实用新型包括如下技术方案：The utility model comprises the following technical solutions:
一种液体火箭超临界氦增压的试验系统，包括氦气瓶、常温电磁阀、减压器、孔板前压力表、孔板后压力表、常温增压孔板、液氦贮罐、液氦贮罐压力表、液氦贮罐温度计、电子秤、加温换热器、截止阀、增压电磁阀、置换管路、低温增压孔板、流量计、贮箱、贮箱压力表、贮箱温度计、排气电磁阀和排气孔板；A test system for liquid rocket supercritical helium pressurization, including a helium cylinder, a normal temperature solenoid valve, a pressure reducer, a pressure gauge in front of the orifice plate, a pressure gauge behind the orifice plate, a normal temperature pressurized orifice plate, a liquid helium storage tank, a liquid helium Storage tank pressure gauge, liquid helium storage tank thermometer, electronic scale, heating heat exchanger, stop valve, booster solenoid valve, replacement pipeline, low temperature booster orifice plate, flow meter, storage tank, storage tank pressure gauge, storage tank Box thermometer, exhaust solenoid valve and exhaust orifice;
液氦贮罐用于储存液氦，氦气瓶依次通过常温电磁阀、减压器和常温增压孔板与液氦贮罐的加注口相连，在常温增压孔板前设有孔板前压力表，在常温增压孔板后设有孔板后压力表；液氦贮罐放置在电子秤上，液氦贮罐上设有液氦贮罐压力表和液氦贮罐温度计；液氦贮罐的增压口依次通过加温换热器、增压电磁阀、低温增压孔板、流量计与贮箱入口相连，贮箱设有贮箱压力表和贮箱温度计；贮箱的出口连接排气电磁阀和排气孔板；在孔板后压力表后的管路与增压电磁阀后的管路之间设有置换管路，并在该置换管路设有截止阀。The liquid helium storage tank is used to store liquid helium. The helium cylinder is connected to the filling port of the liquid helium storage tank through a normal temperature solenoid valve, a pressure reducer and a normal temperature pressurized orifice in sequence. A pressure gauge behind the orifice plate is provided behind the pressurized orifice plate at normal temperature; the liquid helium storage tank is placed on an electronic scale, and a liquid helium storage tank pressure gauge and a liquid helium storage tank thermometer are arranged on the liquid helium storage tank; The pressurization port of the tank is connected to the inlet of the storage tank through a heating heat exchanger, a booster solenoid valve, a low-temperature pressurized orifice, and a flowmeter in sequence. The storage tank is equipped with a tank pressure gauge and a tank thermometer; the outlet of the tank is connected to An exhaust solenoid valve and an exhaust orifice; a replacement pipeline is provided between the pipeline behind the pressure gauge behind the orifice plate and the pipeline behind the booster solenoid valve, and a shut-off valve is arranged on the replacement pipeline.
所述增压电磁阀至少为两个、低温增压孔板至少为两个，其中一个增压电磁阀和其中一个低温增压孔板串联后组成一套增压管路，并与另一套增压管路并联。There are at least two booster solenoid valves and at least two low-temperature booster orifice plates, and one booster solenoid valve and one of the low-temperature booster orifice plates are connected in series to form a set of booster pipelines, which are connected with the other set The booster lines are connected in parallel.
本实用新型与现有技术相比具有如下优点：Compared with the prior art, the utility model has the following advantages:
本实用新型的增压试验系统包括氦气瓶、常温电磁阀、减压器、孔板前压力表、孔板后压力表、常温增压孔板、液氦贮罐、液氦贮罐压力表、液氦贮罐温度计、电子秤、加温换热器、截止阀、增压电磁阀、置换管路、低温增压孔板、流量计、贮箱、贮箱压力表、贮箱温度计、排气电磁阀和排气孔板；从而使得本实用新型的系统可以考核超临界氦增压系统的匹配性；可以分析超临界氦加注量与常温挤压气量的关系规律；可以分析常温增压路流量变化；本实用新型可以分析液氦贮罐加注、增压过程的温度及压力变化；本实用新型可以暴露未来应用于火箭所存在的难点。The pressurized test system of the utility model includes a helium cylinder, a normal temperature solenoid valve, a pressure reducer, a pressure gauge in front of the orifice plate, a pressure gauge behind the orifice plate, a normal temperature pressurized orifice plate, a liquid helium storage tank, a liquid helium storage tank pressure gauge, Liquid helium storage tank thermometer, electronic scale, heating heat exchanger, stop valve, booster solenoid valve, replacement pipeline, low temperature booster orifice plate, flow meter, storage tank, storage tank pressure gauge, storage tank thermometer, exhaust Solenoid valve and exhaust orifice; so that the system of the present invention can assess the matching of supercritical helium supercharging system; can analyze the relationship between supercritical helium filling amount and normal temperature extrusion gas volume; can analyze the normal temperature supercharging path The flow rate changes; the utility model can analyze the temperature and pressure changes in the liquid helium storage tank filling and pressurization process; the utility model can expose the difficulties existing in the future application to rockets.
附图说明Description of drawings
图1为本实用新型的超临界氦液体火箭增压试验系统图。Fig. 1 is the supercritical helium liquid rocket pressurization test system diagram of the utility model.
具体实施方式Detailed ways
下面就结合附图对本实用新型做进一步介绍。Below just in conjunction with accompanying drawing, the utility model is further introduced.
如图1所示，本实用新型所述超临界氦液体火箭增压试验系统包括氦气瓶1、常温电磁阀2、减压器3、孔板前压力表41、孔板后压力表42、常温增压孔板5、液氦贮罐6、液氦贮罐压力表7、液氦贮罐温度计8、电子秤9、加温换热器10、截止阀11、增压电磁阀12、置换管路13、低温增压孔板14、流量计15、贮箱16、贮箱压力表17、贮箱温度计18、排气电磁阀19、排气孔板20。As shown in Figure 1, the supercritical helium liquid rocket pressurization test system described in the utility model includes a helium cylinder 1, a normal temperature solenoid valve 2, a pressure reducer 3, a pressure gauge 41 before the orifice plate, a pressure gauge 42 behind the orifice plate, a normal temperature Booster orifice plate 5, liquid helium storage tank 6, liquid helium storage tank pressure gauge 7, liquid helium storage tank thermometer 8, electronic scale 9, heating heat exchanger 10, stop valve 11,
试验前，将液氦加注到液氦贮罐6内，氦气瓶1通过常温电磁阀2、减压器3和常温增压孔板5与液氦贮罐6的加注口相连，常温增压孔板5前后设有孔板前压力表41和孔板后压力表42，液氦贮罐6放置在电子秤9上，液氦贮罐6上设有液氦贮罐压力表7和液氦贮罐温度计8；液氦贮罐6的增压口通过加温换热器10、增压电磁阀12、低温增压孔板14、流量计15与贮箱16入口相连，贮箱16设有贮箱压力表17和贮箱温度计18；贮箱16上端连接排气电磁阀19和排气孔板20。为了对增压电磁阀12后的管路进行置换，在孔板后压力表42后设有置换管路13与增压电磁阀12后的管路相连，该段管路设有截止阀11。Before the test, liquid helium was filled into the liquid helium storage tank 6, and the helium cylinder 1 was connected to the filling port of the liquid helium storage tank 6 through the normal temperature solenoid valve 2, the pressure reducer 3 and the normal temperature booster orifice 5, and the normal temperature Pressure gauge 41 before orifice and pressure gauge 42 after orifice are arranged before and after pressurized orifice 5, and liquid helium storage tank 6 is placed on electronic scale 9, and liquid helium storage tank 6 is provided with liquid helium storage tank pressure gauge 7 and liquid helium storage tank 6. Helium storage tank thermometer 8; the boost port of liquid helium storage tank 6 is connected to the inlet of
本试验系统的工作过程如下：The working process of the test system is as follows:
a)液氦贮罐6的液氦加注过程：保证常温电磁阀2、截止阀11、增压电磁阀12和排气电磁阀19处在关闭状态。通过液氦加注装置向液氦贮罐6中加注液氦，通过电子称9记录贮罐内液氦的重量。a) Liquid helium filling process of the liquid helium storage tank 6: ensure that the normal temperature solenoid valve 2, the stop valve 11, the pressure
b)管路的置换过程：为了避免系统工作过程中，管路中的空气冷凝结冰，导致增压电磁阀12工作异常，在正式试验前通过置换管路13对管路进行置换；打开截止阀11，向增压电磁阀12后的管路及贮箱16充常温氦气，然后关闭截止阀11，打开排气电磁阀19进行排气，重复该过程3至5次后关闭截止阀11和排气电磁阀19。b) Pipeline replacement process: In order to avoid the condensation and freezing of the air in the pipeline during the working process of the system, causing the
c)常温氦气对液氦贮罐6的增压过程：试验开始时，保证增压电磁阀12处在关闭状态，打开常温电磁阀2，调节减压器3，通过常温增压孔板5将氦气瓶1中的常温氦气以一定的压力向液氦贮罐6中的液氦增压，通过增压使液氦贮罐6中的4.2K常压氦气达到超临界状态，通过记录常温增压孔板5前后的压力表的读数，计算出液氦贮罐6增压过程中常温增压氦气量；c) The pressurization process of normal temperature helium to the liquid helium storage tank 6: when the test starts, ensure that the
d)贮箱16的增压过程：当液氦贮罐6中的液氦达到超临界状态，打开增压电磁阀12，超临界氦被从液氦贮罐6中挤出，通过加温换热器10加热成低温氦气，再通过低温增压孔板14和流量计15向贮箱16增压，同时开启排气电磁阀19向外排气，维持贮箱16的箱压稳定，通过流量计15测量给贮箱16增压的氦气流量，通过观测电子秤9的数据变化计算出液氦贮罐6中液氦的流出量，通过贮箱16上的贮箱压力表17和贮箱温度计18来监测贮箱的箱压和箱温值。d) The pressurization process of the storage tank 16: when the liquid helium in the liquid helium storage tank 6 reaches the supercritical state, the
e)贮箱的增压结束过程；关闭常温电磁阀2和增压电磁阀12，保持排气电磁阀19开启；e) The pressurization of the storage tank ends; close the normal temperature solenoid valve 2 and the
f)数据处理过程；通过步骤c可以得到常温增压氦气量；通过步骤d可以得出液氦贮罐6内液氦的流出量、向贮箱16的氦气增压流量及贮箱16的压力变化规律。根据需求调节减压器3后压力，改变常温增压路流量，得出对常温增压性能的影响规律；改变液氦加注量，得出液氦贮罐6内液氦量与常温增压氦气量的变化规律，考察超临界氦加温增压系统匹配性，暴露未来应用于火箭所存在的难点。f) data processing process; normal temperature pressurized helium volume can be obtained by step c; the outflow of liquid helium in the liquid helium storage tank 6, the helium pressurized flow rate to the
本实用新型未详细说明部分属本领域技术人员公知常识。Parts not described in detail in the utility model belong to the common knowledge of those skilled in the art.
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| 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 |
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| 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 |
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| CN105650461B (en) * | 2016-01-06 | 2019-01-25 | 北京航天发射技术研究所 | System for inflation of rocket cryogenic cylinders |
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| 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 |
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