CN103953464B - A kind of method of double elements appearance control thruster on-orbit performance being carried out to ground demarcation - Google Patents
A kind of method of double elements appearance control thruster on-orbit performance being carried out to ground demarcation Download PDFInfo
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- CN103953464B CN103953464B CN201410189060.2A CN201410189060A CN103953464B CN 103953464 B CN103953464 B CN 103953464B CN 201410189060 A CN201410189060 A CN 201410189060A CN 103953464 B CN103953464 B CN 103953464B
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Abstract
The present invention relates to a kind of method of double elements appearance control thruster on-orbit performance being carried out to ground demarcation, particularly one is used for astrovehicle high performance and long service life double elements thruster ground calibration method, belongs to spacecraft propulsion technical field.First control valve is arranged on double elements appearance control thruster head, forms heat and demarcate thruster; Heat is demarcated thruster to be arranged in seal container and to carry out hot rating test; Heat after hot rating test is demarcated thruster and carry out first time cleaning; Heat after cleaning is demarcated thruster take out from seal container, remove the first control valve, second time cleaning is carried out to double elements appearance control thruster head; Second control valve is installed on the double elements appearance control thruster head after second time cleaning, complete double elements appearance control thruster on-orbit performance ground level heat and demarcate.
Description
Technical field
The present invention relates to a kind of method of double elements appearance control thruster on-orbit performance being carried out to ground demarcation, particularly one is used for astrovehicle high performance and long service life double elements thruster ground calibration method, belongs to spacecraft propulsion technical field.
Background technique
Double elements appearance control thruster is generally used for large-scale long lifetime astrovehicle, the task of Attitude and orbit control is performed between astrovehicle total life cycle, its on-orbit performance directly affects performance and the life-span of astrovehicle, therefore, carries out ground in advance demarcate significant to double elements appearance control thruster on-orbit performance.
The obstacle that double elements appearance control thruster on-orbit performance carries out ground level heat demarcation is mainly derived from two aspects, and double elements appearance control thruster on-orbit performance stated accuracy requires higher on the one hand, very high to the vacuum level requirements of pilot system; On the other hand because appearance control thruster flow is very little, inner passage is complicated, conventional comparatively high thrust liquid propellant rocket engine is demarcated rear cleaning method and is difficult to meet the demands, and remaining poisonous propellant agent will damage the test of thruster later stage and astrovehicle integrated installation personnel.
Summary of the invention
The object of the invention is to overcome prior art deficiency, a kind of method of double elements appearance control thruster on-orbit performance being carried out to ground demarcation is provided.
The object of the invention is to be achieved through the following technical solutions.
A kind of method of double elements appearance control thruster on-orbit performance being carried out to ground demarcation of the present invention, step is:
1) the first control valve is arranged on double elements appearance control thruster head, forms heat and demarcate thruster;
2) by step 1) heat that obtains demarcates thruster and is arranged in seal container and carries out hot rating test;
3) by step 2) heat after hot rating test demarcates thruster and carries out first time and clean;
4) by step 3) cleaning after heat demarcate thruster take out from seal container, remove the first control valve, to double elements appearance control thruster head carry out second time clean;
5) the second control valve is arranged on step 4) second time cleaning after double elements appearance control thruster head on, complete double elements appearance control thruster on-orbit performance ground level heat demarcate;
Described step 1) middle heat demarcation thruster is under 2.0MPa, and helium mass spectrum leak rate is not higher than 1 × 10
-2pa.L/s;
Described step 2) pressure is not higher than 133Pa in hot rating test process for middle seal container, and temperature is 15 ~ 30 DEG C;
Described step 2) heat demarcates thruster and adopts methyl hydrazine and liquid dinitrogen tetroxide as demarcation medium, and demarcate medium and supplied separately by the external world, supply pressure is 1.6MPa, and temperature is 20 ~ 25 DEG C;
Described step 2) method of hot rating test, step is: the first step, and the heat of carrying out continuous 10s demarcates thruster fire trial, obtains double elements appearance control thruster vacuum thrust, vacuum specific impulse and proportions of ingredients performance; Second step, carries out the pulse igniting test of when dutycycle is 1280ms:128ms 500 times, obtains the pulse behaviors of double elements appearance control thruster under this dutycycle; 3rd step, the heat of carrying out continuous 800s demarcates thruster fire trial, obtains each several part temperature distribution after double elements appearance control thruster thermodynamic equilibrium;
Described step 3) middle heat demarcation thruster methyl hydrazine passage employing isopropanol is as first time cleansing medium, and liquid dinitrogen tetroxide passage adopts F113 as first time cleansing medium;
Described step 3) middle heat demarcation thruster first time cleaning method, step is: the first step, and heat demarcation thruster methyl hydrazine passage isopropanol carries out flushing 100s, and liquid dinitrogen tetroxide passage F113 carries out flushing 100s; Second step, demarcates thruster and place 10 minutes in seal container by heat.
Described step 4) middle double elements appearance control thruster head methyl hydrazine passage employing isopropanol is as second time cleansing medium, and liquid dinitrogen tetroxide passage adopts F113 as second time cleansing medium;
Described step 4) middle double elements appearance control thruster head second time cleaning method, step is: the first step, double elements appearance control thruster methyl hydrazine passage isopropanol carries out pulse lavage 1000 times, pulse duty factor is 1s:1s, liquid dinitrogen tetroxide passage F113 carries out pulse lavage 1000 times, and pulse duty factor is 1s:1s; Second step, double elements appearance control thruster methyl hydrazine passage isopropanol carries out continuous flushing 1h, and liquid dinitrogen tetroxide passage F113 carries out continuous flushing 1h; 3rd step, double elements appearance control thruster methyl hydrazine passage and liquid dinitrogen tetroxide passage all carry out pulse lavage 1000 times with anhydrous alcohol, and pulse duty factor is 1s:1s; 4th step, double elements appearance control thruster methyl hydrazine and liquid dinitrogen tetroxide passage anhydrous alcohol carry out continuous flushing 1h; 5th step, double elements appearance control thruster methyl hydrazine and liquid dinitrogen tetroxide passage all carry out continuous flushing 1h with 2.0MPa high pure nitrogen.
Described step 5) middle double elements appearance control thruster is under 2.0MPa, and helium mass spectrum leak rate is not higher than 1 × 10
-4pa.L/s.
Beneficial effect
In the present invention, double elements appearance control thruster first control valve is only for hot rating test, second control valve is arranged on double elements appearance control thruster head after hot rating test, solve double elements appearance control thruster control valve inner passage complicated, be difficult to the problem thoroughly cleaned up;
In the closed environment of condition of high vacuum degree, hot rating test is carried out in the present invention, can effective simulated dual constituent element appearance control thruster true environment in-orbit, thruster accurate performance in-orbit can be obtained;
In seal container, carry out first time cleaning in the present invention, the methyl hydrazine of the overwhelming majority and liquid dinitrogen tetroxide can be remained in seal container and get rid of, decrease the injury to personnel health when the first control valve removed by thruster;
In the cleaning of double elements appearance control thruster head second time, first adopt pulse and stable state two kinds of method cleaning thruster head channel with cleansing medium in the present invention, thoroughly can remove the methyl hydrazine in thruster head channel and dinitrogen tetroxide remnants; Then adopt pulse and stable state two kinds of method cleaning thruster head channel with anhydrous alcohol, the cleansing medium can thoroughly removed in thruster head channel is remaining; Finally rinse thruster head channel with high pure nitrogen, the anhydrous alcohol can thoroughly removed in thruster head channel is remaining.
Embodiment
Below in conjunction with embodiment, the invention will be further described.
Embodiment
Double elements appearance control thruster on-orbit performance is carried out to a method for ground demarcation, step is:
1) the first control valve is arranged on double elements appearance control thruster head, forms heat and demarcate thruster;
2) by step 1) heat that obtains demarcates thruster and is arranged in seal container and carries out hot rating test;
3) by step 2) heat after hot rating test demarcates thruster and carries out first time and clean;
4) by step 3) cleaning after heat demarcate thruster take out from seal container, remove the first control valve, to double elements appearance control thruster head carry out second time clean;
5) the second control valve is arranged on step 4) second time cleaning after double elements appearance control thruster head on, complete double elements appearance control thruster on-orbit performance ground level heat demarcate;
Described step 1) middle heat demarcation thruster is under 2.0MPa, and helium mass spectrum leak rate is not higher than 1 × 10
-2pa.L/s;
Described step 2) pressure is not higher than 133Pa in hot rating test process for middle seal container, and temperature is 25 DEG C;
Described step 2) heat demarcates thruster and adopts methyl hydrazine and liquid dinitrogen tetroxide as demarcation medium, and demarcate medium and supplied separately by the external world, supply pressure is 1.6MPa, and temperature is 20 DEG C;
Described step 2) method of hot rating test, step is: the first step, and the heat of carrying out continuous 10s demarcates thruster fire trial, obtains double elements appearance control thruster vacuum thrust, vacuum specific impulse and proportions of ingredients performance; Second step, carries out the pulse igniting test of when dutycycle is 1280ms:128ms 500 times, obtains the pulse behaviors of double elements appearance control thruster under this dutycycle; 3rd step, the heat of carrying out continuous 800s demarcates thruster fire trial, obtains each several part temperature distribution after double elements appearance control thruster thermodynamic equilibrium;
Described step 3) middle heat demarcation thruster methyl hydrazine passage employing isopropanol is as first time cleansing medium, and liquid dinitrogen tetroxide passage adopts F113 as first time cleansing medium;
Described step 3) middle heat demarcation thruster first time cleaning method, step is: the first step, and heat demarcation thruster methyl hydrazine passage isopropanol carries out flushing 100s, and liquid dinitrogen tetroxide passage F113 carries out flushing 100s; Second step, demarcates thruster and place 10 minutes in seal container by heat.
Described step 4) middle double elements appearance control thruster head methyl hydrazine passage employing isopropanol is as second time cleansing medium, and liquid dinitrogen tetroxide passage adopts F113 as second time cleansing medium;
Described step 4) middle double elements appearance control thruster head second time cleaning method, step is: the first step, double elements appearance control thruster methyl hydrazine passage isopropanol carries out pulse lavage 1000 times, pulse duty factor is 1s:1s, liquid dinitrogen tetroxide passage F113 carries out pulse lavage 1000 times, and pulse duty factor is 1s:1s; Second step, double elements appearance control thruster methyl hydrazine passage isopropanol carries out continuous flushing 1h, and liquid dinitrogen tetroxide passage F113 carries out continuous flushing 1h; 3rd step, double elements appearance control thruster methyl hydrazine passage and liquid dinitrogen tetroxide passage all carry out pulse lavage 1000 times with anhydrous alcohol, and pulse duty factor is 1s:1s; 4th step, double elements appearance control thruster methyl hydrazine and liquid dinitrogen tetroxide passage anhydrous alcohol carry out continuous flushing 1h; 5th step, double elements appearance control thruster methyl hydrazine and liquid dinitrogen tetroxide passage all carry out continuous flushing 1h with 2.0MPa high pure nitrogen.
Described step 5) middle double elements appearance control thruster is under 2.0MPa, and helium mass spectrum leak rate is not higher than 1 × 10
-4pa.L/s.
Claims (8)
1. double elements appearance control thruster on-orbit performance is carried out to a method for ground level heat demarcation, it is characterized in that step is:
1) the first control valve is arranged on double elements appearance control thruster head, forms heat and demarcate thruster;
2) by step 1) heat that obtains demarcates thruster and is arranged in seal container and carries out hot rating test;
3) by step 2) heat after hot rating test demarcates thruster and carries out first time and clean;
4) by step 3) cleaning after heat demarcate thruster take out from seal container, remove the first control valve, to double elements appearance control thruster head carry out second time clean;
5) the second control valve is arranged on step 4) second time cleaning after double elements appearance control thruster head on, complete double elements appearance control thruster on-orbit performance ground level heat demarcate.
2. a kind of method of double elements appearance control thruster on-orbit performance being carried out to ground level heat demarcation according to claim 1, is characterized in that: step 2) pressure is not higher than 133Pa in hot rating test process for middle seal container, and temperature is 15 ~ 30 DEG C.
3. a kind of method of double elements appearance control thruster on-orbit performance being carried out to ground level heat demarcation according to claim 1, it is characterized in that: step 2) heat demarcates thruster employing methyl hydrazine and liquid dinitrogen tetroxide demarcates medium as heat, heat is demarcated medium and is supplied separately by the external world, supply pressure is 1.6MPa, and temperature is 20 ~ 25 DEG C.
4. a kind of method of double elements appearance control thruster on-orbit performance being carried out to ground level heat demarcation according to claim 1, it is characterized in that: step 2) method of hot rating test, step is: the first step, and the heat of carrying out continuous 10s demarcates thruster fire trial; Second step, carries out the pulse igniting test of when dutycycle is 1280ms:128ms 500 times; 3rd step, the heat of carrying out continuous 800s demarcates thruster fire trial.
5. a kind of method of double elements appearance control thruster on-orbit performance being carried out to ground level heat demarcation according to claim 1, it is characterized in that: step 3) middle heat demarcation thruster methyl hydrazine passage employing isopropanol is as first time cleansing medium, and liquid dinitrogen tetroxide passage adopts F113 as first time cleansing medium.
6. a kind of method of double elements appearance control thruster on-orbit performance being carried out to ground level heat demarcation according to claim 1, it is characterized in that: step 3) middle heat demarcation thruster first time cleaning method, step is: the first step, heat is demarcated thruster methyl hydrazine passage isopropanol and is carried out flushing 100s, and liquid dinitrogen tetroxide passage F113 carries out flushing 100s; Second step, demarcates thruster and place 10 minutes in seal container by heat.
7. a kind of method of double elements appearance control thruster on-orbit performance being carried out to ground level heat demarcation according to claim 1, it is characterized in that: step 4) middle double elements appearance control thruster head methyl hydrazine passage employing isopropanol is as second time cleansing medium, and liquid dinitrogen tetroxide passage adopts F113 as second time cleansing medium.
8. a kind of method of double elements appearance control thruster on-orbit performance being carried out to ground level heat demarcation according to claim 1, it is characterized in that: step 4) middle double elements appearance control thruster head second time cleaning method, step is: the first step, double elements appearance control thruster methyl hydrazine passage isopropanol carries out pulse lavage 1000 times, pulse duty factor is 1s:1s, liquid dinitrogen tetroxide passage F113 carries out pulse lavage 1000 times, and pulse duty factor is 1s:1s; Second step, double elements appearance control thruster methyl hydrazine passage isopropanol carries out continuous flushing 1h, and liquid dinitrogen tetroxide passage F113 carries out continuous flushing 1h; 3rd step, double elements appearance control thruster methyl hydrazine passage and liquid dinitrogen tetroxide passage all carry out pulse lavage 1000 times with anhydrous alcohol, and pulse duty factor is 1s:1s; 4th step, double elements appearance control thruster methyl hydrazine and liquid dinitrogen tetroxide passage anhydrous alcohol carry out continuous flushing 1h; 5th step, double elements appearance control thruster methyl hydrazine and liquid dinitrogen tetroxide passage all carry out continuous flushing 1h with 2.0MPa high pure nitrogen.
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| CN106516165B (en) * | 2016-10-27 | 2018-10-09 | 北京控制工程研究所 | A method of improving double elements attitude control thruster Pulse Width Control precision |
| CN111891394B (en) * | 2020-08-11 | 2022-01-04 | 北京控制工程研究所 | On-orbit calibration method for flow sensor of satellite cold air propulsion system |
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| CN102513312A (en) * | 2011-12-23 | 2012-06-27 | 北京控制工程研究所 | Method for cleaning electromagnetic valve after thermal condition calibration of double-component thrustor |
| CN103406312A (en) * | 2013-07-26 | 2013-11-27 | 北京控制工程研究所 | Cleaning method for thrust section of hot calibrated two-component thruster |
| CN103412088A (en) * | 2013-07-26 | 2013-11-27 | 北京控制工程研究所 | Chemical test method for bipropellant thruster after thermal standard cleaning |
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| JPS6245965A (en) * | 1985-08-23 | 1987-02-27 | Mitsubishi Heavy Ind Ltd | Pressure controller |
| JP2548483B2 (en) * | 1992-03-24 | 1996-10-30 | 川崎重工業株式会社 | A performance evaluation system for a flight system using thrust deflection control. |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102513312A (en) * | 2011-12-23 | 2012-06-27 | 北京控制工程研究所 | Method for cleaning electromagnetic valve after thermal condition calibration of double-component thrustor |
| CN103406312A (en) * | 2013-07-26 | 2013-11-27 | 北京控制工程研究所 | Cleaning method for thrust section of hot calibrated two-component thruster |
| CN103412088A (en) * | 2013-07-26 | 2013-11-27 | 北京控制工程研究所 | Chemical test method for bipropellant thruster after thermal standard cleaning |
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