CN105173124A - Service life ground test method for ion thruster - Google Patents
Service life ground test method for ion thruster Download PDFInfo
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- CN105173124A CN105173124A CN201510419025.XA CN201510419025A CN105173124A CN 105173124 A CN105173124 A CN 105173124A CN 201510419025 A CN201510419025 A CN 201510419025A CN 105173124 A CN105173124 A CN 105173124A
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Abstract
The invention discloses a service life ground test method for an ion thruster. By using the ground test method, a ground service life test for the iron thruster can be performed for a long time. According to the ground test method, service life ground test equipment is built first of all, the performance of the ion thruster after working for a long time is tested on the basis of the simulation space condition of the test equipment, and accordingly actual results of the service life of the ion thruster can be obtained, and real and reliable test data are provided for evaluation of the service life and the reliability of the thruster. Main performance parameters of the ion thruster in the whole service life can be obtained through substantive tests in the test process, and the change rule of the performance parameters of the thruster along with accumulative working time is further obtained; the basis for long-service-life working and application of the ion thruster is provided, and essential data can be obtained for more effective acceleration tests of the iron thruster in future. The test method is effective and reliable, and the economic cost and the time cost of the service life test are greatly lowered.
Description
Technical field
The present invention relates to ion thruster technical field, be specifically related to a kind of ion thruster life-span ground experiment method.
Background technology
Ion thruster is one of space propulsion system of advanced person the most at present, and external space technology developed country has been widely used in spacecraft flight task.Be characterized in that thrust is little, than leaping high, the life-span is long, in October, 2012, China puts into practice No. nine satellite launch lift-offs, good authentication is carried out to the compatibility of the correctness of multiple electric propulsion technology scheme, operation on orbit performance and spacecraft and long-term operation on orbit ability, has meaned that the full electric propulsion system of China tentatively possesses application power in-orbit.But it wants its ripe application on spacecraft, generally also needs, at its life test of ground validation, to examine its reliability.The 30cm xenon thruster that the U.S. " Deep Space 1 " (DS-1) sounding satellite adopts had carried out the ground life-span certification testing up to more than 30000 hours before aviation applications, same China also needs to build ion thruster life-span certification testing equipment, does the ground life-span assessment mode in life-span.Such test facility both domestic and external at present, large discharge gas load is bled by traditional conventional vacuum pump merely, pumping efficiency is lower, test facility and ion thruster experiment control system relatively independent, integrated level is low, and test operation is complicated, the performance of ion thruster and state, such as the means of testing such as the angle of divergence, gate surface situation when the test of above ion thruster (especially 2 and) is simple, the problems such as equipment sputtering deposition thing is large.
Summary of the invention
In view of this, the invention provides a kind of ion thruster life-span ground experiment method, can meet ion thruster life test strong to test facility exhaust capacity, return the particular/special requirements such as sputtering deposition thing is little, reliability is high, device integration is high.
Ion thruster life-span ground-testing plant of the present invention comprises: main cabin vacuum vessel, push-pull valve, secondary cabin vacuum vessel, vacuum pumping system, ion beam target, Anti-splash shields, thruster travel mechanism, quartz crystal microbalance QCM, thruster divergence angle measurement system, grid on-line corrosion monitoring system, ground experiment power-supply system, apparatus control system, xenon gas supply system, multiple pressing system, cooling water system, pneumatic element gas supply system, liquid nitrogen storage and supply system and camera lighting system,
Wherein, vacuum vessel one end, main cabin is provided with main cabin door, and the other end is connected with secondary cabin vacuum vessel by push-pull valve, and vacuum vessel one end, secondary cabin is provided with secondary cabin door, and the other end is connected with main cabin vacuum vessel by push-pull valve; Main cabin vacuum vessel is the work chamber of ion thruster ground life test, and secondary cabin is the placement cabin of ion thruster;
Vacuum pumping system forms by for the common heavy caliber cryopump of exhaust and the xenon heavy caliber cryopump for taking out xenon, is provided with push-pull valve, for ground-testing plant being evacuated to the degree of vacuum of requirement between every platform cryopump and main cabin vacuum vessel;
Ion beam target is arranged on the main cabin door inside face of main cabin vacuum vessel, and ion beam target outside face is provided with high purity graphite target plate;
Anti-splash screen is arranged on the inner peripheral surface of main cabin vacuum vessel linear portion, and Anti-splash screen material is pure titanium Ta1;
Grid on-line corrosion monitoring system comprises the photographic camera in mechanical arm and fitting machine mechanical arm, obtains the corrosion condition of process of the test intermediate ion thruster grid by taking a picture; Described grid on-line corrosion monitoring system is arranged in the sensing chamber in the vacuum vessel of main cabin;
Thruster divergence angle measurement system is arranged on vacuum vessel leading portion distance ion thruster front, main cabin, can spin upside down and horizontal translation, when participating in the detection of ion thruster beam divergence angle, thruster divergence angle measurement system level moves to ion thruster end face front, and by the upset of the detection end face of thruster divergence angle measurement system for vertical state, alignd in the test surfaces center of thruster divergence angle measurement system and test surfaces is parallel with the ejiction opening end face of ion thruster with ion thruster center; When not participating in detecting, be horizontal state by the upset of the test surfaces of thruster divergence angle measurement system, test surfaces is downward;
QCM is arranged in thruster travel mechanism, is positioned at the front end face front upper place of thruster, for monitoring sputtering deposition thing pollution situation;
Main cabin vacuum vessel and secondary cabin vacuum vessel being provided with multiple pressing system separately, during for testing stopping, being filled with clean gas to main cabin vacuum vessel and secondary cabin vacuum vessel vacuum chamber;
Cooling water system is used for providing cooling water expansion tank to vacuum pumping system;
Pneumatic element gas supply system provides compressed gas to the pneumatic element of vacuum pumping system;
Liquid nitrogen storage and supply system stores also provides cold nitrogen to the large aperture cryopump in ion beam target, vacuum pumping system, for reducing the temperature of ion beam target and large aperture cryopump;
Camera lighting system is arranged on vacuum vessel top, main cabin, for the realtime graphic of thruster in main cabin vacuum vessel in Real-Time Monitoring and record ground experiment process;
Thruster travel mechanism is positioned at secondary cabin vacuum vessel, for installing and automatically controlling moving iron thruster;
Ground experiment power-supply system is connected with ion thruster, for thruster provides experiment power supply by the crossing cabin flange wire on the vacuum vessel of secondary cabin;
Apparatus control system is used for monitoring in real time and record each equipment working state, is responsible for the control and management of thruster power supply and the analyzing and processing of experimental test data, has warning;
Xenon gas supply system is connected with ion thruster, for thruster provides source of the gas by the crossing cabin adaptor union on the vacuum vessel of secondary cabin.
Further, main cabin vacuum vessel and secondary cabin vacuum vessel are made by 0Cr18Ni9 material.
Further, main cabin vacuum vessel requires that final vacuum is less than 1.0 × 10
-5pa, background vacuum is less than 1.3 × 10
-4pa, working vacuum degree is less than 5.0 × 10
-4pa; Secondary cabin vacuum level requirements is less than 1.0 × 10
-2pa.
Beneficial effect:
(1) specially taken out combination and the backup consideration of heavy caliber cryopump by common heavy caliber cryopump and xenon, improve the pumping efficiency of equipment, substantially increase the reliability of the equipment of test.By configuring online monitoring equipment (divergence angle measurement device, grid on-line corrosion monitoring system and QCM), Real-Time Monitoring ion thruster state, for the design and simulation of ion thruster and research provide strong backing.The control and management of apparatus control system integrated equipment and controlling test management function, handled easily.Have employed mechanism's Anti-splash in high purity graphite sphere ion beam target, vacuum main cabin vacuum vessel inside face Anti-splash screen and main cabin vacuum vessel coated, effectively reduce the sputtering of thruster line and return the impact of sediment on thruster.
(2) use this test facility and test method can obtain the legitimate reading in ion thruster life-span, the life and reliability evaluation of thruster provide truly in order to evaluate, failure-free test figures.By a large amount of tests in process of the test, the Specifeca tion speeification of the whole life period thruster of ion thruster can be obtained, and then obtain the Changing Pattern of thruster performance perameter with cumulative operation time, for ion thruster long-lived operation and application provide foundation, can be that actv. ion thruster accelerated test will obtain basic data more from now on.This test method is effective, reliable, significantly reduces financial cost and the time cost of life test.
Accompanying drawing explanation
Fig. 1 is ion thruster ground experiment theory of constitution figure of the present invention.
Fig. 2 is ion thruster ground experiment ion thruster test condition figure of the present invention.
Fig. 3 is the 3D schematic diagram of ion thruster ground experiment of the present invention.
Fig. 4 is test method diagram of circuit of the present invention.
Fig. 5 is long-time life test diagram of circuit.
Fig. 6 is the structural representation that heavy caliber of the present invention extracts xenon cryopump.
Fig. 7 is baffle of the present invention and absorbing array hiding relation figure.
Fig. 8 is absorbing array structure schematic diagram.
Fig. 9 is baffle structural representation.
Wherein, 1-Cryo Refrigerator, 2-absorbing array, 3-is heat sink, 4-protective shield of radiation, 5-pump case, 6-baffle, 7-baffle temperature element, 8-absorbing array temperature element, the cold screen of 9-one-level, 10-fin.
Detailed description of the invention
To develop simultaneously embodiment below in conjunction with accompanying drawing, describe the present invention.
The invention provides a kind of ion thruster life-span ground-testing plant, can be used for the life-span ground experiment of 1 or 2 ion thruster.As shown in Figure 1, ground-testing plant comprises main cabin vacuum vessel, push-pull valve, secondary cabin vacuum vessel, vacuum pumping system, ion beam target, Anti-splash screen, thruster travel mechanism, quartz crystal microbalance (QCM), thruster divergence angle measurement system, grid on-line corrosion monitoring system, ground experiment power-supply system, apparatus control system, xenon gas supply system, multiple pressing system, cooling water system, pneumatic element gas supply system, liquid nitrogen storage and supply system, out of my cabin platform and camera lighting system.
Ion thruster life test must be less than 5.0 × 10 at working vacuum degree
-4the vacuum vessel of Pa carries out, because the ion thruster life test cycle reaches tens thousand of hours, if duration of test main cabin vacuum vessel et out of order, particularly vacuum pumping system fault or main cabin vacuum vessel leak, will produce the ion thruster life-span and have a strong impact on, therefore the secondary volume of compartment device of vacuum is set, and push-pull valve is set between the main volume of compartment device of vacuum and vacuum secondary cabin vacuum vessel, if duration of test main cabin vacuum vessel et out of order, ion thruster will retract secondary cabin vacuum vessel by travel mechanism, close push-pull valve, shutdown flow processing is done to ion thruster.
Consider that this ground-testing plant can carry out the life-span ground experiment of 2 ion thrusters, according to the comprehensive analysis of ion thruster angle of divergence characteristic and sputtering, the main cabin vacuum vessel determining carrying out ion thruster life test is of a size of
3800mm (internal diameter) × 8500mm (straight section length), center height is 2250mm, be made up of 0Cr18Ni9 material, vacuum vessel one end, main cabin is provided with main cabin door, the other end is connected with secondary cabin vacuum vessel by push-pull valve, wherein, rubber seal is equipped with in the junction of main cabin vacuum vessel and push-pull valve, main cabin vacuum vessel and main cabin door.Secondary cabin vacuum vessel is of a size of
1600mm (internal diameter) × 1600mm (straight section length), center height is 2250mm, be made up of 0Cr18Ni9 material, secondary vacuum vessel one end, cabin is provided with secondary cabin door, the other end is connected with main cabin vacuum vessel by push-pull valve, and rubber seal is equipped with in the junction of secondary cabin vacuum vessel and push-pull valve, secondary cabin vacuum vessel and secondary cabin door.Push-pull valve effective drift diameter is
1600mm, is arranged between main cabin vacuum vessel and secondary cabin vacuum vessel by bolt, is used for cutting off or being communicated with main cabin vacuum vessel and secondary cabin vacuum vessel.
Vacuum pumping system provides vacuum environment for ground experiment, be made up of 6 heavy caliber cryopumps (comprise 2 Daeporis and lead to heavy caliber cryopump and 4 xenon heavy caliber cryopumps), and before every platform cryopump, push-pull valve is housed, ion thruster is when life test, its large discharge xenon load leads to heavy caliber cryopump by 1 Daepori and 3 xenon heavy caliber cryopumps have come, remain 2 standby backups, if the heavy caliber cryopump of work breaks down, can switch to backup machine work.Wherein, main cabin vacuum vessel requires that final vacuum is less than 1.0 × 10
-5pa, background vacuum is less than 1.3 × 10
-4pa, working vacuum degree is less than 5.0 × 10
-4pa; Secondary cabin vacuum level requirements is less than 1.0 × 10
-2pa.
Wherein, heavy caliber extracts xenon cryopump and comprises Cryo Refrigerator 1, absorbing array 2, heat sink 3, protective shield of radiation 4, pump case 5, baffle 6, baffle temperature element 7, absorbing array temperature element 8 and the cold screen 9 of one-level.Wherein, described pump case 5 internal diameter Ф 1250mm, the long 850mm of straight section; Cryo Refrigerator 1 is used for providing cold to absorbing array and the cold screen of one-level, generally select secondary Cryo Refrigerator, Cryo Refrigerator 1 is arranged on pump case 5 by flange, and adopt rubber seal rings for seal with pump case 5, absorbing array 6 is arranged on the secondary cold head of fefrigerator, absorbing array 2 is riveted by the thick oxygen-free copper of 1.5mm to form, and is lined with indium pad in the junction of absorbing array and secondary cold head.Absorbing array of the present invention is mainly used in adsorbing xenon, and xenon saturated vapor pressure when 50K reaches 5 × 10-7Pa, so, as long as keep absorbing array temperature lower than 50K, common cryopump requires that absorbing array is within 10K, for this feature, and the absorbing array of special design cryopump and thermal protection system.Absorbing array skeleton adopts oblong housing structure, and the upper and lower surface along pump shaft line of oblong housing is open, and 4 peripheral side of oblong housing increase by 4 groups of fins, can increase cryogenic condensation area like this, greatly can improve the pumping speed of cryopump to xenon.Absorbing array 2 is provided with temperature element 8, to monitor the temperature index of absorbing array when cryopump runs.The measurement range of temperature element is 10K ~ 400K, and precision is ± 1K.The cold screen of one-level 9 is processed by the thick oxygen-free copper of 2mm, is fixed on the one-level cold head of Cryo Refrigerator 1, surface blackening process by screw, for reducing pump case to heat sink thermal radiation.Heat sink 3 are arranged on cryopump housing 5, be made up of 304 stainless steel tubes and copper fin, analyze as calculated, relative to General low temperature pump, this pump is relatively low to heat sink temperature requirement, and temperature is lower than 120K, so, liquid nitrogen, cold nitrogen can be led in heat sink pipeline, also can lead to mechanical refrigeration working medium (three grades of overlapping mechanical refrigeration units provide), can use cost be reduced.Baffle 6 is positioned at the pumping hole position of cryopump, in process of the test, test line can produce sputtering effect to cryopump baffle, causes the corrosion of baffle, thus reduce the service life of cryopump, therefore, the generous 1.5mm of baffle 6 of the present invention, adopts platy structure, and its vertical direction realizes an optics shielding to absorbing array, at baffle surface spraying equadag coating, the thick 0.5mm of equadag coating, to reduce test line to the sputtering of baffle.Concrete structure is shown in Fig. 4.Baffle be fixed by screws in heat sink on, baffle 6 is provided with temperature element 7, so as to monitor cryopump run time baffle 6 temperature index.The measurement range of temperature element is 40K ~ 400K, and precision is ± 1K.This cryopump Anti-splash, and to xenon 1.5 times that take out scooter General low temperature pump, greatly can save equipment xenon and extract pump acquisition cost, remarkable in economical benefits.
Ion beam target is arranged on the main cabin door inside face of main cabin vacuum vessel, ion beam target outside face is pasted with high purity graphite (carbon content > 99.99%) target plate, for reducing ion sputtering and beam reflection, absorb the ion beam energy that ion thruster is launched.
Anti-splash screen is arranged on the inner peripheral surface of main cabin vacuum vessel linear portion, and it is of a size of
3600mm (internal diameter) × 6000mm (length), in Anti-splash screen, material is pure titanium (Ta1), for reducing in the vacuum vessel of main cabin ion sputtering to the impact of ion thruster.
Grid on-line corrosion monitoring system comprises the photographic camera in mechanical arm and fitting machine mechanical arm, is used for the corrosion condition of monitoring test process intermediate ion thruster grid.Grid on-line corrosion monitoring system is arranged in the sensing chamber in the vacuum vessel of main cabin, during grid on-line corrosion monitoring system works, opens sensing chamber, and photographic camera moves to ion thruster grid front by mechanical arm, the corrosion condition of monitoring grid; During inoperative, photographic camera and mechanical arm are positioned at airtight sensing chamber, avoid the damage being subject to plasma.
Thruster divergence angle measurement system is arranged on distance ion thruster front end face 500mm place, vacuum vessel front end, main cabin, can spin upside down and horizontal translation, can meet 2 ion thruster beam divergence angles and detect demand.When the thruster angle of divergence measured by needs, thruster divergence angle measurement system is moved to ion thruster ejiction opening end face front, and be vertical state by the upset of the detection end face of thruster divergence angle measurement system, alignd in the test surfaces center of thruster divergence angle measurement system and test surfaces is parallel with the ejiction opening end face of ion thruster with the center of ion thruster, measure the thruster angle of divergence, after measurement, upset thruster divergence angle measurement system is horizontal state, test surfaces is downward, prevents thruster divergence angle measurement system by plasma damage.
QCM installed thrust device travel mechanism, is positioned at the front end face front upper place of thruster, for monitoring sputtering deposition thing pollution situation.
Main cabin vacuum vessel and secondary cabin vacuum vessel being provided with multiple pressing system separately, during for testing stopping, being filled with clean gas to main cabin vacuum vessel and secondary cabin vacuum vessel vacuum chamber.
Cooling water system is used for providing cooling water expansion tank to vacuum pumping system.
Pneumatic element gas supply system provides compressed gas to the pneumatic element of vacuum pumping system.
Liquid nitrogen storage and supply system stores also provides cold nitrogen to the large aperture cryopump in ion beam target, vacuum pumping system, for reducing the temperature of ion beam target and large aperture cryopump.
Camera lighting system is arranged on vacuum vessel top, main cabin, for the realtime graphic of thruster in main cabin vacuum vessel in Real-Time Monitoring and record ground experiment process.
Thruster travel mechanism is positioned at secondary cabin vacuum vessel, for installing and automatically controlling moving iron thruster, rated load 100kg, moving velocity 5mm/min.
Ground experiment power-supply system is connected with ion thruster, for thruster provides experiment power supply by the crossing cabin flange wire on the vacuum vessel of secondary cabin.
Apparatus control system can intelligent autonomous operation, monitors in real time and record, have warning to each equipment working state, is responsible for the control and management of thruster power supply and the analyzing and processing of experimental test data.
Xenon gas supply system is connected with ion thruster, for thruster provides source of the gas by the crossing cabin adaptor union on the vacuum vessel of secondary cabin.
Platform is convenient to operation and the observation of test out of my cabin.
Ion thruster life-span ground experiment method is:
Step 1, test prepares:
Ion thruster is arranged in thruster travel mechanism; Close the main cabin door of main cabin vacuum vessel and the secondary cabin door of secondary cabin vacuum vessel; Open push-pull valve, utilize thruster travel mechanism to be delivered to by ion thruster in the vacuum vessel of main cabin; Start vacuum suction unit, main cabin is evacuated to and requires degree of vacuum; Open camera lighting system, grid on-line corrosion monitoring system, QCM etc.;
Step 2, ion thruster pretreatment:
When the local degree of vacuum of main cabin vacuum vessel is less than 1.3 × 10
-4during Pa, pretreatment is carried out to ion thruster, then start ion thruster igniting;
Step 3, carry out ion thruster performance testing:
Performance testing comprises:
(1) under ion thruster standard duty, plume divergence angle measurement is carried out: under standard duty, thruster divergence angle measurement system level is moved to ion thruster front, and be vertical state by the upset of the test surfaces of thruster divergence angle measurement system, alignd with ion thruster center in the test surfaces center of thruster divergence angle measurement system, and test surfaces is parallel with the end face of ion thruster, measure the thruster angle of divergence, after measurement, downward upset thruster divergence angle measurement system test face is downward to test surfaces, prevent thruster divergence angle measurement system by plasma damage,
(2) carry out ion thruster and draw inclined performance testing: draw inclined operating mode I to test, under standard duty, ion thruster anode gas flow rate is adjusted to (1+5%) of rated value, (1-5%) that (1-5%) that main cathode flow is adjusted to rated value, neutralizer flow are rated value, condition of power supply is adjusted to (1+5%) of rated value, checks ion thruster performance change; Inclined operating mode II is drawn to test, under standard duty, ion thruster anode gas flow rate is adjusted to (1-5%) of rated value, (1+5%) that (1+5%) that main cathode flow is adjusted to rated value, neutralizer flow are rated value, condition of power supply is adjusted to (1-5%) of rated value, checks ion thruster performance change.
(3) main cathode pinnate pattern margin of safety test: adopt flow rate fine-tuning method to test, only open main cathode, main cathode is progressively reduced by standard duty for rate of air flow, until main cathode changes plume pattern into from dot pattern, touch and hold pole tension peak-to-peak changing value and namely think more than 5V plume pattern occurs, the difference of confession rate of air flow when main cathode standard duty is critical with plume is main cathode pinnate pattern margin of safety.
(4) neutralizer pinnate pattern margin of safety test: adopt flow rate fine-tuning method to test, only drive neutralizer, neutralizer is progressively reduced by standard duty for rate of air flow, until neutralizer changes plume pattern into from dot pattern, touch and hold pole tension peak-to-peak changing value and namely think more than 5V plume pattern occurs, the difference of confession rate of air flow when neutralizer standard duty is critical with plume is neutralizer pinnate pattern margin of safety.
(5) electronics reflux limit voltage test: adopt accelerating grid voltage trim method to test, under standard duty, progressively reduce accelerating grid voltage, until beam current has the increment of 0.1mA, accelerating grid voltage is now electronics reflux limit voltage.
(6) gate surface wear testing: after ion thruster is shut down, after accelerating grid cooling, utilizes grid on-line corrosion monitoring system to take pictures to accelerating grid, thus obtains the corrosion condition of accelerating grid.
(7) vacuum environment insulating power test: after ion thruster is shut down, uses Hi-pot Tester to measure the insulativity between the cable of thruster.
When carrying out the long-time life-span ground experiment of ion thruster, to prepare and after step 2 carries out ion thruster pretreatment carrying out test according to step 1,
The first step, carries out ion thruster accumulative cyclic test in 500 hours, and records the relation of thruster performance and cumulative operation time, in order to conclude the basic law of thruster performance change.
Step 1.1, carries out ion thruster switching on and shutting down cyclic test: ion thruster work 120min, shutdown wait for that 30min, again the start shooting circulation of thruster work 120min are carried out.
Step 1.2, carries out ion thruster performance testing according to the mode of step 3;
Step 1.3, carries out regular maintenance to ion thruster, if test facility and ion thruster are not exposed in air, then proceeds to the 3rd step; Otherwise, proceed to second step.
Second step, carries out ion thruster pretreatment according to step 2, then proceeds to the 3rd step.
3rd step, carries out ion thruster accumulative cyclic test in 500 hours according to the first step, often works and carry out primary ions thruster life-span and reliability evaluation in 2000 hours; Till thruster operational failure or thruster accumulated operating time reach 11000h.
In addition, duration of test, should be able to monitor ion thruster working parameter and pilot system working parameter at any time.
During vacuum pumping system regeneration or equipment troubleshooting barrier, utilize thruster travel mechanism to be retreated to by ion thruster in the vacuum vessel of secondary cabin, close push-pull valve.
Test is till reaching when premature failure appears in life test work-hours and on-off times or system.
In sum, these are only preferred embodiment of the present invention, be not intended to limit protection scope of the present invention.Within the spirit and principles in the present invention all, any amendment done, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (2)
1. an ion thruster life-span ground experiment method, is characterized in that, comprise the steps:
Step 1, set up ion thruster life-span ground-testing plant:
Ion thruster life-span ground-testing plant comprises: main cabin vacuum vessel, push-pull valve, secondary cabin vacuum vessel, vacuum pumping system, ion beam target, Anti-splash screen, thruster travel mechanism, quartz crystal microbalance QCM, thruster divergence angle measurement system, grid on-line corrosion monitoring system, ground experiment power-supply system, apparatus control system, xenon gas supply system, multiple pressing system, cooling water system, pneumatic element gas supply system, liquid nitrogen storage and supply system and camera lighting system;
Wherein, vacuum vessel one end, main cabin is provided with main cabin door, and the other end is connected with secondary cabin vacuum vessel by push-pull valve, and vacuum vessel one end, secondary cabin is provided with secondary cabin door, and the other end is connected with main cabin vacuum vessel by push-pull valve; Main cabin vacuum vessel is the work chamber of ion thruster ground life test, and secondary cabin is the placement cabin of ion thruster;
Vacuum pumping system by for exhaust common heavy caliber cryopump and and xenon heavy caliber cryopump for taking out xenon form, be provided with push-pull valve between every platform cryopump and main cabin vacuum vessel;
Ion beam target is arranged on the main cabin door inside face of main cabin vacuum vessel, and ion beam target outside face is provided with high purity graphite target plate; Anti-splash screen is arranged on the inner peripheral surface of main cabin vacuum vessel linear portion, and Anti-splash screen material is pure titanium Ta1;
Grid on-line corrosion monitoring system comprises the photographic camera in mechanical arm and fitting machine mechanical arm, obtains the corrosion condition of process of the test intermediate ion thruster grid by taking a picture; Described grid on-line corrosion monitoring system is arranged in the sensing chamber in the vacuum vessel of main cabin; Thruster divergence angle measurement system is arranged on vacuum vessel leading portion distance ion thruster front, main cabin, can spin upside down and horizontal translation; QCM is arranged in thruster travel mechanism, is positioned at the front end face front upper place of thruster, for monitoring sputtering deposition thing pollution situation;
Main cabin vacuum vessel and secondary cabin vacuum vessel being provided with multiple pressing system separately, during for testing stopping, being filled with clean gas to main cabin vacuum vessel and secondary cabin vacuum vessel vacuum chamber; Cooling water system is used for providing cooling water expansion tank to vacuum pumping system; Pneumatic element gas supply system provides compressed gas to the pneumatic element of vacuum pumping system; Liquid nitrogen storage and supply system stores also provides cold nitrogen to the large aperture cryopump in ion beam target, vacuum pumping system, for reducing the temperature of ion beam target and large aperture cryopump;
Camera lighting system is arranged on vacuum vessel top, main cabin, for the realtime graphic of thruster in main cabin vacuum vessel in Real-Time Monitoring and record ground experiment process; Thruster travel mechanism is positioned at secondary cabin vacuum vessel, for installing and automatically controlling moving iron thruster; Ground experiment power-supply system is connected with ion thruster, for thruster provides experiment power supply by the crossing cabin flange wire on the vacuum vessel of secondary cabin; Apparatus control system is used for monitoring in real time and record each equipment working state, is responsible for the control and management of thruster power supply and the analyzing and processing of experimental test data, has warning; Xenon gas supply system is connected with ion thruster, for thruster provides source of the gas by the crossing cabin adaptor union on the vacuum vessel of secondary cabin;
Step 2, test prepares:
Ion thruster is arranged in thruster travel mechanism; Close the main cabin door of main cabin vacuum vessel and the secondary cabin door of secondary cabin vacuum vessel; Open push-pull valve, utilize thruster travel mechanism to be delivered to by ion thruster in the vacuum vessel of main cabin; Start vacuum suction unit, main cabin is evacuated to and requires degree of vacuum;
Step 3, ion thruster pretreatment:
When the local degree of vacuum of main cabin vacuum vessel is less than 1.3 × 10
-4during Pa, pretreatment is carried out to ion thruster, then start ion thruster igniting;
Step 4, carry out ion thruster performance testing:
Performance testing comprises:
(1) under ion thruster standard duty, beam divergence angular measurement is carried out: under standard duty, thruster divergence angle measurement system level is moved to ion thruster front, and be vertical state by the upset of the test surfaces of thruster divergence angle measurement system, alignd with ion thruster center in the test surfaces center of thruster divergence angle measurement system, and test surfaces is parallel with the end face of ion thruster, measure the thruster angle of divergence, after measurement, downward upset thruster divergence angle measurement system test face is downward to test surfaces, prevent thruster divergence angle measurement system by plasma damage,
(2) carry out ion thruster and draw inclined performance testing: draw inclined operating mode I to test, under standard duty, ion thruster anode gas flow rate is adjusted to (1+5%) of rated value, (1-5%) that (1-5%) that main cathode flow is adjusted to rated value, neutralizer flow are rated value, condition of power supply is adjusted to (1+5%) of rated value, checks ion thruster performance change; Inclined operating mode II is drawn to test, under standard duty, ion thruster anode gas flow rate is adjusted to (1-5%) of rated value, (1+5%) that (1+5%) that main cathode flow is adjusted to rated value, neutralizer flow are rated value, condition of power supply is adjusted to (1-5%) of rated value, checks ion thruster performance change;
(3) main cathode pinnate pattern margin of safety test: only open main cathode, main cathode is progressively reduced by standard duty for rate of air flow, until main cathode changes plume pattern into from dot pattern, touch and hold pole tension peak-to-peak changing value and namely think more than 5V plume pattern occurs, the difference of confession rate of air flow when main cathode standard duty is critical with plume is main cathode pinnate pattern margin of safety;
(4) neutralizer pinnate pattern margin of safety test: only drive neutralizer, neutralizer is progressively reduced by standard duty for rate of air flow, until neutralizer changes plume pattern into from dot pattern, touch and hold pole tension peak-to-peak changing value and namely think more than 5V plume pattern occurs, the difference of confession rate of air flow when neutralizer standard duty is critical with plume is neutralizer pinnate pattern margin of safety;
(5) electronics reflux limit voltage test: under standard duty, progressively reduce accelerating grid voltage, until beam current has the increment of 0.1mA, accelerating grid voltage is now electronics reflux limit voltage;
(6) gate surface wear testing: after ion thruster is shut down, after accelerating grid cooling, utilizes grid on-line corrosion monitoring system to take pictures to accelerating grid, thus obtains the corrosion condition of accelerating grid;
(7) vacuum environment insulating power test: after ion thruster is shut down, uses Hi-pot Tester to measure the insulativity between the cable of thruster.
2. ion thruster life-span ground experiment method as claimed in claim 1, is characterized in that, when carrying out the long-time life-span ground experiment of ion thruster, is carrying out after test preparation and step 2 carry out ion thruster pretreatment according to step 1,
The first step, carry out ion thruster accumulative cyclic test in 500 hours:
Step 1.1, carries out the accumulative test of ion thruster switching on and shutting down in 500 hours circulation: ion thruster work 120min, shutdown wait for that 30min, again the start shooting circulation of thruster work 120min are carried out;
Step 1.2, carries out ion thruster performance testing according to the mode of step 4; The relation of record thruster performance and cumulative operation time, in order to conclude the basic law of thruster performance change;
Step 1.3, carries out regular maintenance to ion thruster, if test facility and ion thruster are not exposed in air, then proceeds to the 3rd step; Otherwise, proceed to second step;
Second step, carries out ion thruster pretreatment according to step 3, then proceeds to the 3rd step;
3rd step, carries out ion thruster accumulative cyclic test in 500 hours according to the first step, often works and carry out primary ions thruster life-span and reliability evaluation in 2000 hours; Till thruster operational failure or thruster accumulated operating time reach 11000h.
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2245825C1 (en) * | 2003-11-03 | 2005-02-10 | Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" им. С.П. Королева" | Automated testing system for optimization, electrical checks and preparation of spacecraft for launch |
| CN203299289U (en) * | 2013-04-25 | 2013-11-20 | 兰州空间技术物理研究所 | Vacuum auxiliary cabin for electromagnetic radiation emission test of electric thruster |
| CN104232849A (en) * | 2014-09-04 | 2014-12-24 | 兰州空间技术物理研究所 | Stabilizing treatment method for magnetic steel of ion thruster |
| RU2013131324A (en) * | 2013-07-08 | 2015-01-20 | Открытое акционерное общество "Информационные спутниковые системы" имени академика М.Ф. Решётнева" | METHOD OF ELECTRICAL CHECKS OF SPACE VEHICLE |
| CN104330661A (en) * | 2014-10-23 | 2015-02-04 | 兰州空间技术物理研究所 | Device and method for simulating load characteristics of kaufmann ion thruster |
-
2015
- 2015-07-16 CN CN201510419025.XA patent/CN105173124B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2245825C1 (en) * | 2003-11-03 | 2005-02-10 | Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" им. С.П. Королева" | Automated testing system for optimization, electrical checks and preparation of spacecraft for launch |
| CN203299289U (en) * | 2013-04-25 | 2013-11-20 | 兰州空间技术物理研究所 | Vacuum auxiliary cabin for electromagnetic radiation emission test of electric thruster |
| RU2013131324A (en) * | 2013-07-08 | 2015-01-20 | Открытое акционерное общество "Информационные спутниковые системы" имени академика М.Ф. Решётнева" | METHOD OF ELECTRICAL CHECKS OF SPACE VEHICLE |
| CN104232849A (en) * | 2014-09-04 | 2014-12-24 | 兰州空间技术物理研究所 | Stabilizing treatment method for magnetic steel of ion thruster |
| CN104330661A (en) * | 2014-10-23 | 2015-02-04 | 兰州空间技术物理研究所 | Device and method for simulating load characteristics of kaufmann ion thruster |
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|---|---|---|---|---|
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