CN104075105A - Thermal pressurizing type xenon filling system of electric satellite propelling system - Google Patents
Thermal pressurizing type xenon filling system of electric satellite propelling system Download PDFInfo
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Abstract
The invention relates to a thermal pressurizing type xenon filling system of an electric satellite propelling system and belongs to the technical field of high-purity xenon filing experiments in the electric satellite propelling system system. Xenon flows into a satellite gas supply bottle through thermal pressurizing devices in the system; the thermal pressurizing type xenon filling system comprises a xenon storage tank, an electronic balance for weighing the storage tank, a gas source valve, a thermal pressurizing device A, a thermal pressurizing device B, a liquefied nitrogen valve A, a liquefied nitrogen valve B, a liquefied nitrogen valve C, a liquefied nitrogen tank, a helium bottle, a helium valve, a control and data collection module, a purity analyzer, a filling valve, the satellite gas supply bottle, a vacuum valve, a vacuum pump, a recycling valve, a recycling module, a gas discharge valve and a satellite gas supply bottle weighing device. According to the technical requirement of high-purity xenon filing in the electric satellite propelling system, a model experiment system is reasonably designed and established. The experiment system has the advantage of high cleanliness degree, accurate temperature control, high reliability, convenience in module replacement and comprehensive date measurement; the feasibility and the reasonability of thermal pressurizing type xenon filling can be effectively tested.
Description
Technical field
The present invention relates to the hot supercharging xenon of satellite electric propulsion system loading system, belong to high-purity xenon filling experimental technique field of satellite electric propulsion system, be applicable to the high-purity xenon of all employings as the filling test of the electric propulsion system of working medium.
Background technique
At present, the propulsion system type of flight is more in-orbit, wherein electric propulsion system developed rapidly in the last few years owing to having very high specific impulse, especially with Hall electric propulsion system and ion-conductance propulsion system, gain great popularity, be usually used in that satellite platform is carried out North-south Station-keeping, attitude is controlled (momenttum wheel unloading) and track control, even the task such as synchronous orbit transfer.In addition electric propulsion system can complete the task that conventional propulsion system cannot complete, and as survey of deep space, interplanetary travel etc. need the accurate attitude of the task of large △ y and satellite, microsatellite, controls and the task such as satellite constellation networking control.
The xenon of usining needs to carry out xenon filling as Hall electric propulsion system and the ion-conductance propulsion system of working medium before satellite launch, adopt xenon as the electric propulsion system of working medium, its performance is directly subject to the impact of xenon purity, xenon purity after filling is had to harsh requirement: require the xenon purity that is filled into propulsion system higher than 99.995%, the content of water and oxygen is no more than 2ppm, and the purity in xenon source is only 99.9995%.So how to guarantee in large capacity xenon filling process that xenon purity and system pressure, temperature, adding amount etc. meet the demands, guarantee that in filling process, xenon, in gaseous state or supercritical state, is a great problem that electric propulsion system, especially long lifetime electric propulsion system are realized through engineering approaches application.
Complete the xenon filling of electric propulsion system, can realize by falling to pressing to fill the hot supercharging loading system of loading system, compressor mechanical compress loading system and the present invention's design.It declines and presses filling filling to refer to that, under the effect of pressure reduction, the xenon in xenon storage tank is filled to the process of gas cylinder on star, after storage pressure equates on storage tank and star, cannot continue filling process, so the method is only applicable to the operating mode that adding amount is less; The filling of compressor mechanical compress adopts compressor that xenon is carried out to supercharging, make it constantly flow into the electric propulsion system on star, but the method exists defect at aspects such as fifth wheel control, temperature controls, and noise is larger, filling method is the same with falling to pressing, and is only applicable to the operating mode that adding amount is less; And hot supercharging xenon loading system has well solved the difficult problems such as fifth wheel control, temperature control, can by increasing the quantity of core component, improve the reliability of method simultaneously, become the most important technology that realizes the high-purity xenon filling of large capacity task.From 2012, started research and the investigation of hot supercharging xenon loading system, and finally completed the design work of this loading system.
The reduction of the pressure following temperature of xenon and reducing, rising with temperature raises, hot supercharging xenon charging method is this thermodynamic properties that utilizes xenon, first liquid nitrogen is passed into hot supercharging device, high-pressure bottle temperature in device is reduced, thereby make the reduction of the xenon pressure following temperature in container and reduce, lower than the pressure of xenon in xenon storage tank, under the effect of pressure reduction, the xenon in xenon storage tank can constantly flow into high-pressure bottle; When xenon intake reaches required value, stop logical liquid nitrogen, start the heating equipment in hot supercharging device, high-pressure bottle temperature is raise, thereby make the rising of the xenon pressure following temperature in container and raise, higher than the pressure of xenon in gas cylinder on star, under the effect of pressure reduction, xenon in high-pressure bottle can constantly flow into gas cylinder on star, thereby completes the filling process of xenon.Said process loops, until adding amount meets mission requirements.
For realizing the loading technique of high-purity xenon, overall plan and the function of filling pilot system that the present invention is clear and definite.And use the method, and completed the demonstration test of high-purity xenon filling, proved this loading system reasonable.
Abroad since the later stage nineties in last century just the research to high-purity xenon loading technique, dropped into huge man power and material, carry out a large amount of demonstration tests, by technological accumulation for many years, aspect high-purity xenon filling, possessed stronger technical capability.Wherein, Air Liquid Co adopts the loading technique that is similar to hot supercharging, successfully developed the high-purity xenon loading system of large capacity, its filling ability has reached 1200kg, article is " Patrick BRAVAIS; Roland SALOME, C é cile GELAS.IMPROVED XENON LOADING EQUIPMENT WITH LOADING CAPACITY UP TO1200KG FOR ALPHABUS.AIR LIQUIDE DTA.CNES Toulouse ".And although some article does not relate to concrete xenon loading technique, but its content has comprised recovery and the supply process of utilizing xenon physical property to carry out, can be used as the reference of hot supercharging xenon charging method, article is " Gani B.Ganapathi*and Jiunn Jenq Wu.Xenon Recovery System Concept Demonstration.AIAA2006-5256 ".Domestic because high-purity xenon loading technique is still located blank, do not have the document can reference.
Because the checking of high-purity xenon loading technique and correlation test relates to national security, the country that has grasped this technology often carries out blockade on new techniques, the data that abroad can provide is very not comprehensive, can only play certain reference function, in the related article of delivering just article the performance index that can reach, all not mentioned pilot system form, design and the verification experimental verification method of pilot system.So the loading technique research to high-purity xenon need to be built pilot system voluntarily, carries out a large amount of demonstration tests, sum up filling verification experimental verification method, obtain the sufficient firsthand information, these basic datas can not obtain from foreign literature.
In sum, the hot supercharging xenon of satellite electric propulsion system loading system is to realize the achievement of groping and summing up in the process that progressively realizes through engineering approaches application at electric propulsion system, whole system is brand-new, domestic do not have relevant document and data to use for reference, and seldom discloses the similar pilot system of careless mistake abroad yet.The present invention, in order to realize high-purity xenon loading technique, in conjunction with practice and the experience of scientific research production process, has proposed the pilot system of high-purity xenon filling first.
Summary of the invention
The object of the invention is in order to overcome the deficiencies in the prior art, the hot supercharging xenon of satellite electric propulsion system loading system is provided, can effectively complete the xenon filling task of satellite electric propulsion system.
The object of the invention is to be achieved through the following technical solutions.
The hot supercharging xenon of satellite electric propulsion system of the present invention loading system, this system makes the hot supercharging device of xenon in system flow into gas cylinder on star; This system comprises on xenon storage tank, storage tank weighing electronic scale, source of the gas valve, hot supercharging device A, hot supercharging device B, liquid nitrogen valve A, liquid nitrogen valve B, liquid nitrogen valve C, liquid nitrogen container, helium tank, helium valve, control and data acquisition module, purity analysis instrument, fill valve, star gas cylinder load cell on gas cylinder, vacuum valve, vacuum pump, recovery valve, recycling module, bleed valve and star; Wherein in hot supercharging device A, gas cylinder A and electric heater A are housed; Gas cylinder B and electric heater B are housed in hot supercharging device B;
Above-mentioned all valves are pneumatic valve, can control its switching by control system;
Wherein xenon storage tank is positioned on storage tank weighing electronic scale, and is connected with hot supercharging device A, hot supercharging device B by source of the gas valve; Liquid nitrogen container is connected with hot supercharging device A, hot supercharging device B, recycling module respectively by liquid nitrogen valve A, liquid nitrogen valve B, liquid nitrogen valve C, for three supplies with liquid nitrogen; Helium tank is connected with gas cylinder, recycling module on hot supercharging device A, hot supercharging device B, star respectively by helium valve, fill valve, recovery valve, for it provides helium; Purity analysis instrument is connected to the upstream of gas cylinder on star, for analyzing the purity of filling process xenon; Control with data acquisition module and be used for gathering this system weight, pressure, temperature, purity parameter, and according to the switching of each parameter situation control valve; On star, gas cylinder is connected with hot supercharging device A, hot supercharging device B by fill valve; Vacuum pump is connected with gas cylinder, hot supercharging device A, hot supercharging device B, recycling module on star by fill valve, vacuum valve, recovery valve, for it vacuumizes; Recycling module is connected with gas cylinder on hot supercharging device A, hot supercharging device B, star by recovery valve, fill valve, for the xenon of gas cylinder on hot supercharging device and star is reclaimed; Bleed valve is connected to the upstream of gas cylinder on star, for bleeding off the gas of system; On star, gas cylinder is weighed with gas cylinder load cell on star.
The hot supercharging xenon of satellite electric propulsion system charging method comprises the following steps:
A. connect xenon filling pilot system;
B. start vacuum pump, open fill valve, vacuum valve and recovery valve, gas cylinder and recycling module on hot supercharging device A, hot supercharging device B, star are vacuumized, when degree of vacuum reaches 10Pa, close above-mentioned valve (fill valve, vacuum valve and recovery valve), and stop vacuumizing;
C. open helium valve, fill valve, be filled with helium to gas cylinder on hot supercharging device A, hot supercharging device B, star, close helium valve; By purity analysis instrument, analyze helium purity and whether meet the demands, then open bleed valve, bleed off the helium in system, after venting finishes, close bleed valve, then close fill valve;
C ' repeating step c, until helium purity meets the demands;
D. open source of the gas valve, fill valve, be filled with xenon to gas cylinder on hot supercharging device A, hot supercharging device B, star, close source of the gas valve; Whether by purity analysis instrument, analyze xenon purity meets the demands; Open liquid nitrogen valve C and supply with liquid nitrogen to recycling module, close liquid nitrogen valve C; Then open recovery valve, the xenon in system is reclaimed, after recovery finishes, close recovery valve, then close fill valve;
D ' repeating step d, until xenon purity meets the demands;
E. open source of the gas valve, the xenon in xenon storage tank is filled to hot supercharging device A, hot supercharging device B; After filling process finishes, open liquid nitrogen valve A, liquid nitrogen valve B, supply with liquid nitrogen to hot supercharging device A, hot supercharging device B, the xenon in xenon storage tank is drawn in hot supercharging device A and hot supercharging device B; By storage tank weighing electronic scale, xenon intake is weighed, when intake reaches required value, close source of the gas valve, liquid nitrogen valve A and liquid nitrogen valve B;
F. starting electric heater A and electric heater B, is the gas cylinder A in hot supercharging device and gas cylinder B heating; When the temperature of xenon reaches ℃ in gas cylinder A and gas cylinder B, open fill valve, the xenon in gas cylinder A and gas cylinder B is annotated to gas cylinder on star; By gas cylinder load cell on star, xenon adding amount is weighed; On gas cylinder A, gas cylinder B and star, after storage pressure balance, close fill valve;
G. step e～f repeats, until adding amount meets the demands;
H. open recovery valve, the xenon in hot supercharging device A, hot supercharging device B and system pipeline is reclaimed; Off-test.
In whole process of the test, control with data acquisition module and complete the collection of each parameter, and control the switching of each pneumatic valve.System connects the stainless steel pressure duct that pipeline used is high polishing.
Described recycling module comprises and reclaims gas cylinder, sealing cover and liquid nitrogen container, wherein liquid nitrogen container be upper shed, with the cylindrical container of thermal insulation layer; Liquid nitrogen pipeline is housed, for liquid nitrogen being passed into liquid nitrogen container on sealing cover; First recovery gas cylinder is positioned in liquid nitrogen container, builds sealing cover, during recovery, liquid nitrogen is passed into liquid nitrogen container, to reclaiming gas cylinder cooling, open afterwards recovery valve and can complete the recovery to xenon in system.
The present invention's beneficial effect is compared with prior art:
(1) the present invention is according to the technical requirements of the high-purity xenon filling of satellite electric propulsion system, and appropriate design has also been built model test system.This pilot system have cleanliness high, can carry out that accurate temperature control, reliability are high, module displacement is convenient, the survey data advantage such as complete comprehensively, can effectively verify feasibility and the rationality of hot supercharging xenon filling.
(2) the present invention adopts pneumatic valve automatically to control, to coordinate matching strong with system pressure, temperature, realizing the control of pneumatic valve switch coordinates to carry out with filling process, can realize the automatic control of xenon suction process and filling process, also can prevent that on process of the test culminant star, the xenon in gas cylinder is back to pilot system, can ensure xenon filling experimental safe, reliably carry out.
(3) test method that the present invention adopts is reasonable, feasible, workable, can be for the filling test of larger xenon adding amount, also can, by increasing hot supercharging device quantity or increasing the volume of hot supercharging device mesohigh container, meet the filling mission requirements of larger adding amount; The realization of hot supercharging xenon loading technique, can promote the application of high-purity xenon in satellite electric propulsion system, thereby accelerates the process that electric propulsion system is realized through engineering approaches application.
Accompanying drawing explanation
Fig. 1 is the composition schematic diagram of system of the present invention;
Fig. 2 is the schematic flow sheet of method of the present invention;
Fig. 3 is the structural representation of recycling module.
Embodiment
Below in conjunction with drawings and Examples, the invention will be further described.
Embodiment
As shown in Figure 1, this system comprises on xenon storage tank 1, storage tank weighing electronic scale 2, source of the gas valve 3, hot supercharging device A4, hot supercharging device B5, liquid nitrogen valve A6, liquid nitrogen valve B7, liquid nitrogen valve C8, liquid nitrogen container 9, helium tank 10, helium valve 11, control and data acquisition module 12, purity analysis instrument 13, fill valve 14, star gas cylinder load cell 21 on gas cylinder 15, vacuum valve 16, vacuum pump 17, recovery valve 18, recycling module 19, bleed valve 20, star.
System connects the stainless steel pressure duct that pipeline used is high polishing, concrete Placement is as follows: wherein xenon storage tank 1 is positioned on storage tank weighing electronic scale 2, and adopts pressure duct that it is connected with hot supercharging device A4, hot supercharging device B5 with source of the gas valve 3; Adopt liquid nitrogen pipeline that liquid nitrogen container 9, liquid nitrogen valve A6, liquid nitrogen valve B7, liquid nitrogen valve C8, hot supercharging device A4, hot supercharging device B5, recycling module 19 are connected, liquid nitrogen pipeline outer wall need to be wrapped with thermal insulation layer; Adopt high-voltage tube that gas cylinder 15, recycling module 19 on helium tank 10 helium valves 11, fill valve 14, recovery valve 18, hot supercharging device A4, hot supercharging device B5, star are connected; Purity analysis instrument 13 accesses pilot system by high-voltage tube; Startup valve used all has control wiring to be connected with data acquisition module 12 with control, can receive at any time the control signal that it sends; Adopt high-voltage tube that vacuum pump 17, vacuum valve 16 are connected into pilot system, for whole pilot system vacuumizes; Adopt high-voltage tube by recycling module 19, recovery valve 18 access pilot systems, for the xenon of gas cylinder on hot supercharging device and star is reclaimed; Bleed valve 20 is for bleeding off the gas of system, and wherein bleed line need to be connected to outdoor; On star, gas cylinder is weighed with gas cylinder load cell 21 on star.
Adopt hot supercharging xenon filling pilot system, and adopt high-purity xenon and helium as test working medium, can verify whole xenon filling process, comprise vacuumize, the process such as helium replacement, xenon displacement, xenon suction, xenon filling, xenon recovery, thereby verify feasibility and the rationality of hot supercharging xenon charging method.
As shown in Figure 2, concrete steps are as follows: before on-test, so should be ready to the parts in pilot system, adopt respectively high pressure air pipeline with liquid nitrogen pipeline, individual parts to be connected, concrete connecting means as mentioned before, thereby complete building of whole pilot system; By controlling with data acquisition module, start vacuum pump, and open vacuum valve 16, fill valve 14, recovery valve 18, gas cylinder on star and ground loading system are vacuumized, degree of vacuum is evacuated to 10Pa; Helium valve 11 is opened, open fill valve 14, recovery valve 18 simultaneously, on star, gas cylinder and ground loading system carry out helium replacement, helium replacement pressure is 1MPa, the helium being filled with in system is carried out to purity analysis, require water content≤2ppm, oxygen content≤2ppm, then open bleed valve 20, bleed off the helium in system; Open source of the gas valve 3, fill valve 14, to gas cylinder, ground loading system on star, fill xenon to 0.5MPa, the xenon being filled with in system is carried out to purity analysis, require water content≤2ppm, oxygen content≤2ppm, then opens liquid nitrogen valve C8, is filled with liquid nitrogen in recycling module, open recovery valve 18, remaining xenon in system after purity analysis is reclaimed; Open liquid nitrogen valve A6, liquid nitrogen valve B7, be filled with liquid nitrogen to hot supercharging device, gas cylinder A41, gas cylinder B51 temperature in device are reduced, open source of the gas valve 3, xenon is sucked into high-pressure bottle, and suction process is weighed by storage tank weighing electronic scale 2, when weight reaches mission requirements, by controlling and data acquisition module 12 automatic closing gas source valves 3, cut off xenon suction process; Start electric heater A42, electric heater B52, gas cylinder A41, gas cylinder B51 in hot supercharging device are heated up, in container, the pressure of xenon is higher than on star during gas cylinder 15, control with data acquisition module 12 and automatically open fill valve 14, start to carry out xenon filling, in filling process, by gas cylinder load cell on star 21, carry out the measurement of adding amount; Xenon sucks and filling process will loop, until adding amount reaches mission requirements; Open liquid nitrogen valve C8, give recycling module 19 logical liquid nitrogen cooling, open recovery valve 18, remaining xenon in system is recycled to recycling module 19.Hot supercharging xenon filling process finishes.
As shown in Figure 3, described recycling module 19 comprises and reclaims gas cylinder 191, sealing cover 192 and liquid nitrogen container 193, and wherein liquid nitrogen container 193 is for upper shed, with the cylindrical container of thermal insulation layer; Liquid nitrogen pipeline is housed, for liquid nitrogen being passed into liquid nitrogen container 193 on sealing cover 192; First recovery gas cylinder 191 is positioned in liquid nitrogen container 193, builds sealing cover 192, during recovery, liquid nitrogen is passed into liquid nitrogen container 193, to reclaiming gas cylinder 191 coolings, open afterwards recovery valve 18 and can complete the recovery to xenon in system.
The unspecified part of the present invention belongs to general knowledge as well known to those skilled in the art.
Claims (4)
1. for the hot supercharging xenon loading system of satellite electric propulsion system, it is characterized in that: this system comprises xenon storage tank (1), storage tank weighing electronic scale (2), source of the gas valve (3), hot supercharging device A (4), hot supercharging device B (5), liquid nitrogen valve A (6), liquid nitrogen valve B (7), liquid nitrogen valve C (8), liquid nitrogen container (9), helium tank (10), helium valve (11), control and data acquisition module (12), purity analysis instrument (13), fill valve (14), gas cylinder on star (15), vacuum valve (16), vacuum pump (17), recovery valve (18), recycling module (19), gas cylinder load cell (21) on bleed valve (20) and star,
Gas cylinder A (41) and electric heater A (42) are wherein housed in hot supercharging device A (4); Gas cylinder B (51) and electric heater B (52) are housed in hot supercharging device B (5);
Xenon storage tank (1) is positioned on storage tank weighing electronic scale (2), and is connected with hot supercharging device A (4), hot supercharging device B (5) by source of the gas valve (3);
Liquid nitrogen container (9) is connected with hot supercharging device A (4) by liquid nitrogen valve A (6);
Liquid nitrogen container (9) is connected with hot supercharging device B (5) by liquid nitrogen valve B (7);
Liquid nitrogen container (9) is connected with recycling module (19) by liquid nitrogen valve C (8);
Helium tank (10) is connected with hot supercharging device A (4), hot supercharging device B (5) by helium valve (11);
Helium tank (10) is connected with gas cylinder on star (15) with fill valve (14) by helium valve (11);
Helium tank (10) is connected with recycling module (19) with recovery valve (18) by helium valve (11);
Purity analysis instrument (13) is connected to the upstream of gas cylinder on star (15);
Control the upstream that is connected to gas cylinder on star (15) with data acquisition module (12);
Gas cylinder on star (15) is connected with hot supercharging device A (4), hot supercharging device B (5) by fill valve (14);
Vacuum pump (17) is connected with gas cylinder on star (15) with vacuum valve (16) by fill valve (14);
Vacuum pump (17) is connected with hot supercharging device A (4), hot supercharging device B (5) by vacuum valve (16);
Vacuum pump (17) is connected with recycling module (19) with recovery valve (18) by vacuum valve (16);
Recycling module (19) is connected with hot supercharging device A (4), hot supercharging device B (5) by recovery valve (18);
Recycling module (19) is connected with gas cylinder on star (15) with fill valve (14) by recovery valve (18);
Bleed valve (20) is connected to the upstream of gas cylinder on star (15);
On star gas cylinder load cell (21) be placed on gas cylinder on star (15) below.
2. the hot supercharging xenon of satellite electric propulsion system according to claim 1 loading system, is characterized in that: all valves are pneumatic valve, by control system, controls its switching.
3. the hot supercharging xenon of satellite electric propulsion system according to claim 1 loading system, is characterized in that: system connects the stainless steel pressure duct that pipeline used is high polishing.
4. the hot supercharging xenon of satellite electric propulsion system according to claim 1 loading system, it is characterized in that: described recycling module (19) comprises and reclaim gas cylinder (191), sealing cover (192) and liquid nitrogen container (193), wherein liquid nitrogen container (193) be upper shed, with the cylindrical container of thermal insulation layer; Sealing cover (192) covers on liquid nitrogen container (193); Sealing cover is equipped with liquid nitrogen pipeline on (192); Reclaim gas cylinder (191) and be arranged in liquid nitrogen container (193).
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| CN104456079B (en) * | 2014-11-06 | 2017-11-07 | 北京控制工程研究所 | A kind of electronics depressurized system |
| CN108204521A (en) * | 2018-01-30 | 2018-06-26 | 邯郸钢铁集团有限责任公司 | High-purity rare gas gas cylinder pretreatment system and preprocess method |
| CN109026580A (en) * | 2018-08-07 | 2018-12-18 | 柳盼 | A kind of delivery method of Hall thruster gaseous propellant |
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