CN103953464A - Ground calibration method for on-orbit performance of two-component attitude control thruster - Google Patents
Ground calibration method for on-orbit performance of two-component attitude control thruster Download PDFInfo
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- CN103953464A CN103953464A CN201410189060.2A CN201410189060A CN103953464A CN 103953464 A CN103953464 A CN 103953464A CN 201410189060 A CN201410189060 A CN 201410189060A CN 103953464 A CN103953464 A CN 103953464A
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Abstract
The invention relates to a ground calibration method for on-orbit performance of a two-component attitude control thruster, in particular to a ground calibration method for a two-component attitude control thruster with high performance and long service life for a spacecraft, and belongs to the technical field of spacecraft propulsion. The method comprises the following steps: a first control valve is installed at the head part of the two-component attitude control thruster to form a thermal calibration thruster; the thermal calibration thruster is installed in a closed container to perform a thermal calibration test; the thermal calibration thruster after the thermal calibration test is cleaned for the first time; the cleaned thermal calibration thruster is taken out from the closed container; the first control valve is dismantled; the head part of the two-component attitude control thruster is cleaned for the second time; a second control valve is installed at the head part of the secondly cleaned two-component attitude control thruster, so as to finish ground thermal calibration for the on-orbit performance of the two-component attitude control thruster.
Description
Technical field
The present invention relates to a kind of method that double elements appearance control thruster on-orbit performance is carried out to ground demarcation, particularly a kind of for high performance and long service life double elements thruster ground calibration method for astrovehicle, belong to spacecraft propulsion technical field.
Background technique
Double elements appearance control thruster is generally used for large-scale long lifetime astrovehicle, between astrovehicle total life cycle, carry out the task of Attitude and orbit control, its on-orbit performance directly affects performance and the life-span of astrovehicle, therefore, double elements appearance control thruster on-orbit performance is carried out to ground in advance and demarcate significant.
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 is had relatively high expectations on the one hand, requires very high to the degree of vacuum of pilot system; On the other hand because appearance control thruster flow is very little, inner passage complexity, conventional is difficult to meet the demands compared with cleaning method after the demarcation of high thrust liquid propellant rocket engine, 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 in order to overcome prior art deficiency, a kind of method that double elements appearance control thruster on-orbit performance is 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 that double elements appearance control thruster on-orbit performance is carried out to ground demarcation of the present invention, step is:
1) the first control valve is arranged on to double elements appearance control thruster head, forms heat and demarcate thruster;
2) by step 1) heat that obtains demarcates thruster and is arranged on and in seal container, carries out hot rating test;
3) by step 2) heat after hot rating test demarcates thruster and cleans for the first time;
4) by step 3) clean after heat demarcate thruster from seal container, take out, remove the first control valve, double elements appearance control thruster head is cleaned for the second time;
5) the second control valve is arranged on to step 4) for the second time clean 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 demarcating medium, demarcates medium and supplied with separately by the external world, and 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, carry out the heat of continuous 10s and demarcate thruster fire trial, obtain double elements appearance control thruster vacuum thrust, vacuum specific impulse and proportions of ingredients performance; Second step, carry out dutycycle while the being 1280ms:128ms pulse igniting test of 500 times, obtains the pulse performance of double elements appearance control thruster under this dutycycle; The 3rd step, carries out the heat of continuous 800s and demarcates thruster fire trial, obtains each several part temperature distribution after double elements appearance control thruster thermodynamic equilibrium;
Described step 3) in heat demarcate thruster methyl hydrazine passage and adopt isopropanol as cleansing medium for the first time, liquid dinitrogen tetroxide passage adopts F113 as cleansing medium for the first time;
Described step 3) middle heat demarcation thruster cleaning method for the first time, step is: the first step, heat is demarcated thruster methyl hydrazine passage and is rinsed 100s with isopropanol, and liquid dinitrogen tetroxide passage rinses 100s with F113; Second step, demarcates thruster by heat and in seal container, places 10 minutes.
Described step 4) in double elements appearance control thruster head methyl hydrazine passage adopt isopropanol as cleansing medium for the second time, liquid dinitrogen tetroxide passage adopts F113 as cleansing medium for the second time;
Described step 4) middle double elements appearance control thruster head cleaning method for the second time, step is: the first step, double elements appearance control thruster methyl hydrazine passage carries out pulse with isopropanol and rinses 1000 times, pulse duty factor is 1s:1s, liquid dinitrogen tetroxide passage carries out pulse with F113 and rinses 1000 times, and pulse duty factor is 1s:1s; Second step, double elements appearance control thruster methyl hydrazine passage carries out continuous flushing 1h with isopropanol, and liquid dinitrogen tetroxide passage carries out continuous flushing 1h with F113; The 3rd step, double elements appearance control thruster methyl hydrazine passage and liquid dinitrogen tetroxide passage all carry out pulse with anhydrous alcohol and rinse 1000 times, and pulse duty factor is 1s:1s; The 4th step, double elements appearance control thruster methyl hydrazine and liquid dinitrogen tetroxide passage carry out continuous flushing 1h with anhydrous alcohol; The 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 the first control valve is only for hot rating test, after hot rating test, the second control valve is arranged on double elements appearance control thruster head, solve double elements appearance control thruster control valve inner passage complexity, the problem that is difficult to thoroughly clean up;
In the present invention, in the closed environment of condition of high vacuum degree, carry out hot rating test, effectively simulated dual constituent element appearance control thruster true environment in-orbit, can obtain thruster accurate performance in-orbit;
In the present invention, in seal container, carry out for the first time and to clean, most methyl hydrazines and liquid dinitrogen tetroxide can be remained in seal container and get rid of, reduced the injury to personnel health when thruster is removed the first control valve;
In the present invention, in double elements appearance control thruster head cleans for the second time, first adopt pulse and two kinds of methods of stable state to clean thruster head channel with cleansing medium, can thoroughly remove methyl hydrazine and dinitrogen tetroxide remnants in thruster head channel; Then adopt pulse and two kinds of methods of stable state to clean thruster head channel with anhydrous alcohol, can thoroughly remove the cleansing medium remnants in thruster head channel; Finally rinse thruster head channel with high pure nitrogen, can thoroughly remove the anhydrous alcohol remnants in thruster head channel.
Embodiment
Below in conjunction with embodiment, the invention will be further described.
Embodiment
The method that double elements appearance control thruster on-orbit performance is carried out to ground demarcation, step is:
1) the first control valve is arranged on to double elements appearance control thruster head, forms heat and demarcate thruster;
2) by step 1) heat that obtains demarcates thruster and is arranged on and in seal container, carries out hot rating test;
3) by step 2) heat after hot rating test demarcates thruster and cleans for the first time;
4) by step 3) clean after heat demarcate thruster from seal container, take out, remove the first control valve, double elements appearance control thruster head is cleaned for the second time;
5) the second control valve is arranged on to step 4) for the second time clean 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 demarcating medium, demarcates medium and supplied with separately by the external world, and supply pressure is 1.6MPa, and temperature is 20 DEG C;
Described step 2) method of hot rating test, step is: the first step, carry out the heat of continuous 10s and demarcate thruster fire trial, obtain double elements appearance control thruster vacuum thrust, vacuum specific impulse and proportions of ingredients performance; Second step, carry out dutycycle while the being 1280ms:128ms pulse igniting test of 500 times, obtains the pulse performance of double elements appearance control thruster under this dutycycle; The 3rd step, carries out the heat of continuous 800s and demarcates thruster fire trial, obtains each several part temperature distribution after double elements appearance control thruster thermodynamic equilibrium;
Described step 3) in heat demarcate thruster methyl hydrazine passage and adopt isopropanol as cleansing medium for the first time, liquid dinitrogen tetroxide passage adopts F113 as cleansing medium for the first time;
Described step 3) middle heat demarcation thruster cleaning method for the first time, step is: the first step, heat is demarcated thruster methyl hydrazine passage and is rinsed 100s with isopropanol, and liquid dinitrogen tetroxide passage rinses 100s with F113; Second step, demarcates thruster by heat and in seal container, places 10 minutes.
Described step 4) in double elements appearance control thruster head methyl hydrazine passage adopt isopropanol as cleansing medium for the second time, liquid dinitrogen tetroxide passage adopts F113 as cleansing medium for the second time;
Described step 4) middle double elements appearance control thruster head cleaning method for the second time, step is: the first step, double elements appearance control thruster methyl hydrazine passage carries out pulse with isopropanol and rinses 1000 times, pulse duty factor is 1s:1s, liquid dinitrogen tetroxide passage carries out pulse with F113 and rinses 1000 times, and pulse duty factor is 1s:1s; Second step, double elements appearance control thruster methyl hydrazine passage carries out continuous flushing 1h with isopropanol, and liquid dinitrogen tetroxide passage carries out continuous flushing 1h with F113; The 3rd step, double elements appearance control thruster methyl hydrazine passage and liquid dinitrogen tetroxide passage all carry out pulse with anhydrous alcohol and rinse 1000 times, and pulse duty factor is 1s:1s; The 4th step, double elements appearance control thruster methyl hydrazine and liquid dinitrogen tetroxide passage carry out continuous flushing 1h with anhydrous alcohol; The 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. a method of double elements appearance control thruster on-orbit performance being carried out to ground demarcation, is characterized in that step is:
1) the first control valve is arranged on to double elements appearance control thruster head, forms heat and demarcate thruster;
2) by step 1) heat that obtains demarcates thruster and is arranged on and in seal container, carries out hot rating test;
3) by step 2) heat after hot rating test demarcates thruster and cleans for the first time;
4) by step 3) clean after heat demarcate thruster from seal container, take out, remove the first control valve, double elements appearance control thruster head is cleaned for the second time;
5) the second control valve is arranged on to step 4) for the second time clean 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 that double elements appearance control thruster on-orbit performance is carried out to ground 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 that double elements appearance control thruster on-orbit performance is carried out to ground demarcation according to claim 1, it is characterized in that: step 2) heat demarcates thruster and adopts methyl hydrazine and liquid dinitrogen tetroxide as demarcating medium, demarcating medium is supplied with separately by the external world, supply pressure is 1.6MPa, and temperature is 20～25 DEG C.
4. a kind of method that double elements appearance control thruster on-orbit performance is carried out to ground demarcation according to claim 1, is characterized in that: step 2) method of hot rating test, step is: the first step, carry out the heat of continuous 10s and demarcate thruster fire trial; Second step, carry out dutycycle while the being 1280ms:128ms pulse igniting test of 500 times; The 3rd step, carries out the heat of continuous 800s and demarcates thruster fire trial.
5. a kind of method that double elements appearance control thruster on-orbit performance is carried out to ground demarcation according to claim 1, it is characterized in that: step 3) in heat demarcate thruster methyl hydrazine passage and adopt isopropanol as cleansing medium for the first time, liquid dinitrogen tetroxide passage adopts F113 as cleansing medium for the first time.
6. a kind of method that double elements appearance control thruster on-orbit performance is carried out to ground demarcation according to claim 1, it is characterized in that: step 3) middle heat demarcation thruster cleaning method for the first time, step is: the first step, heat is demarcated thruster methyl hydrazine passage and is rinsed 100s with isopropanol, and liquid dinitrogen tetroxide passage rinses 100s with F113; Second step, demarcates thruster by heat and in seal container, places 10 minutes.
7. a kind of method that double elements appearance control thruster on-orbit performance is carried out to ground demarcation according to claim 1, it is characterized in that: step 4) in double elements appearance control thruster head methyl hydrazine passage adopt isopropanol as cleansing medium for the second time, liquid dinitrogen tetroxide passage adopts F113 as cleansing medium for the second time.
8. a kind of method that double elements appearance control thruster on-orbit performance is carried out to ground demarcation according to claim 1, it is characterized in that: step 4) middle double elements appearance control thruster head cleaning method for the second time, step is: the first step, double elements appearance control thruster methyl hydrazine passage carries out pulse with isopropanol and rinses 1000 times, pulse duty factor is 1s:1s, liquid dinitrogen tetroxide passage carries out pulse with F113 and rinses 1000 times, and pulse duty factor is 1s:1s; Second step, double elements appearance control thruster methyl hydrazine passage carries out continuous flushing 1h with isopropanol, and liquid dinitrogen tetroxide passage carries out continuous flushing 1h with F113; The 3rd step, double elements appearance control thruster methyl hydrazine passage and liquid dinitrogen tetroxide passage all carry out pulse with anhydrous alcohol and rinse 1000 times, and pulse duty factor is 1s:1s; The 4th step, double elements appearance control thruster methyl hydrazine and liquid dinitrogen tetroxide passage carry out continuous flushing 1h with anhydrous alcohol; The 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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|---|---|---|---|
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| CN201410189060.2A CN103953464B (en) | 2014-05-06 | 2014-05-06 | A kind of method of double elements appearance control thruster on-orbit performance being carried out to ground demarcation |
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| CN103953464B CN103953464B (en) | 2015-11-25 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106516165A (en) * | 2016-10-27 | 2017-03-22 | 北京控制工程研究所 | Method for improving bipropellant attitude control thruster pulse control precision |
| CN111891394A (en) * | 2020-08-11 | 2020-11-06 | 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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| JPS6245965A (en) * | 1985-08-23 | 1987-02-27 | Mitsubishi Heavy Ind Ltd | Pressure controller |
| JPH05272897A (en) * | 1992-03-24 | 1993-10-22 | Kawasaki Heavy Ind Ltd | Performance evaluating apparatus for missile system using thrust deflection control |
| 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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2014
- 2014-05-06 CN CN201410189060.2A patent/CN103953464B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS6245965A (en) * | 1985-08-23 | 1987-02-27 | Mitsubishi Heavy Ind Ltd | Pressure controller |
| JPH05272897A (en) * | 1992-03-24 | 1993-10-22 | Kawasaki Heavy Ind Ltd | Performance evaluating apparatus for missile system using thrust deflection control |
| 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 |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106516165A (en) * | 2016-10-27 | 2017-03-22 | 北京控制工程研究所 | Method for improving bipropellant attitude control thruster pulse control precision |
| CN111891394A (en) * | 2020-08-11 | 2020-11-06 | 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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| CN103953464B (en) | 2015-11-25 |
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