CN106134385B - Spacecraft thermal control loop working medium charging system and methods for filling thereof - Google Patents
Spacecraft thermal control loop working medium charging system and methods for filling thereofInfo
- Publication number
- CN106134385B CN106134385B CN200710082606.4A CN200710082606A CN106134385B CN 106134385 B CN106134385 B CN 106134385B CN 200710082606 A CN200710082606 A CN 200710082606A CN 106134385 B CN106134385 B CN 106134385B
- Authority
- CN
- China
- Prior art keywords
- liang
- ball valve
- control loop
- thermal control
- pass
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
- 238000000034 method Methods 0.000 title claims abstract description 18
- 239000012530 fluid Substances 0.000 claims abstract description 35
- 230000000712 assembly Effects 0.000 claims abstract description 6
- 238000000429 assembly Methods 0.000 claims abstract description 6
- 238000012856 packing Methods 0.000 claims description 9
- 238000012546 transfer Methods 0.000 claims description 5
- 238000005429 filling process Methods 0.000 claims description 4
- 239000007788 liquid Substances 0.000 claims description 4
- 238000010438 heat treatment Methods 0.000 claims description 3
- 238000005303 weighing Methods 0.000 claims description 3
- 238000012790 confirmation Methods 0.000 claims description 2
- 238000002347 injection Methods 0.000 claims description 2
- 239000007924 injection Substances 0.000 claims description 2
- 239000003507 refrigerant Substances 0.000 claims description 2
- 238000013461 design Methods 0.000 abstract description 3
- 238000004140 cleaning Methods 0.000 abstract description 2
- 238000013508 migration Methods 0.000 abstract description 2
- 230000005012 migration Effects 0.000 abstract description 2
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 6
- 239000007791 liquid phase Substances 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- 229910052757 nitrogen Inorganic materials 0.000 description 3
- 239000012071 phase Substances 0.000 description 3
- 238000004364 calculation method Methods 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 238000001802 infusion Methods 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000000205 computational method Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 229920006395 saturated elastomer Polymers 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 230000001988 toxicity Effects 0.000 description 1
- 231100000419 toxicity Toxicity 0.000 description 1
Landscapes
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
Spacecraft thermal control loop working medium charging system and methods for filling thereof, adopt integrated design for disassembly method, by the migration of hot working fluid phase equilibrium principle control quality, the Portable movable of feasible system and on-the-spot high accuracy fill, propose effective solution for the hot working fluid of two-phase fluid thermal control loop fills, solved the key technique difficult problem of thermal control loop in the application of spacecraft model; In addition, by adding high order to count filter assemblies realization in charging system, the cleaning of thermal control loop working medium is filled, improved the strainability of system.
Description
Technical field
The present invention relates to a kind of charging system and methods for filling thereof, particularly a kind of spacecraft thermal control loop working mediumCharging system and methods for filling thereof.
Background technology
Spacecraft thermal control loop becomes the important thermal control means of following Large Spacecraft with its heat transfer efficiently.The normal CO that uses in spacecraft thermal control loop2、C3H6、NH3As hot working fluid, and the filling of these hot working fluidsDress is the critical process that thermal control loop is produced, and the precision filling and quality have determined thermal control loop to a great extentService behaviour.
Spacecraft hot working fluid General Requirements in the time filling should be able to be realized and micro-ly quantitatively filling, and filling weight meets heat transfer meritThe requirement of rate design; Should be able to meet the requirement that fills quality precision, guarantee the service behaviour of thermal control loop; ShouldAvoid polluting thermal control loop and hot working fluid, reduce the impact of impurity on heat transfer property; Hot working fluid filling process shouldUnder closed environment, work, avoid toxicity and the excitant of leaking working medium to damage human and environment.
According to above-mentioned requirements, spacecraft heat pipe being carried out to hot working fluid while filling, first to hot working fluid supercharging,Make hot working fluid become full liquid phase state; Then full liquid phase state working medium smooth drive is filled in heat pipe, simultaneously essenceThe really actual volume that fills hot working fluid of metering, and the quality filling according to the density calculation of working medium under different temperatures;The last changes in weight according to heat pipe before and after filling is confirmed the actual quality that fills of heat pipe. But in practice,Spacecraft heat pipe is to refill and be fitted on spacecraft comprising after all process steps that hot working fluid fills completes, and thermal controlLoop is to carry out filling of hot working fluid after having assembled on spacecraft again, and this just requires the thermal technology of thermal control loopMatter fills and should implement in spacecraft test site, and can not be by the Weighing method of thermal control loop is come reallyRecognize the quality that fills of thermal control loop hot working fluid reality. Therefore, thermal control loop is as a kind of novel thermal control means,Equally with heat pipe need to carry out filling of hot working fluid, but cannot adopt traditional spacecraft heat-pipe working medium to fillMethod is carried out filling of hot working fluid to it.
Summary of the invention
Technology of the present invention is dealt with problems and is: overcome the deficiencies in the prior art, a kind of high precision that fills is providedSpacecraft thermal control loop working medium charging system and methods for filling thereof.
Technical solution of the present invention is: spacecraft thermal control loop working medium charging system, is characterized in that bagContain: standard fills bottle, first liang of pass ball valve, second liang of pass ball valve, the 3rd liang of pass ball valve, the 4th liang of logical ballValve, the 5th liang of pass ball valve, the 6th liang of pass ball valve, the 8th liang of pass ball valve, the 9th liang of pass ball valve, pressure regulateValve, first liang of pass joint, the 3rd liang of pass joint, the 4th liang of pass joint, four-way connection, vacuum system joint,The first filter and the second filter; Standard fill bottle successively through first liang of pass ball valve, first liang of pass joint,Second liang of pass ball valve is connected to four-way connection; By four-way connection, the pipeline of charging system is divided into three tunnels, theOne tunnel is successively through the first filter, the 4th liang of pass ball valve, the 3rd liang of pass joint and the 5th liang of pass ball valve and working mediumStock bottle is connected, and fills bottle for the hot working fluid in working medium stock bottle is filled with to standard; The 3rd liang, the second tunnelPass ball valve, vacuum system joint are connected with vacuum extractor, vacuumize for standard being filled to bottle; Third RoadSuccessively through the 6th liang of pass ball valve, pressure-regulating valve, the second filter, the 4th liang of pass joint and the 8th liang of logical ballValve is connected with thermal control loop, is filled with thermal control loop for the hot working fluid that standard is filled to bottle; The 3rd liang of logical ballBetween the tie point of the tie point of valve and vacuum system joint and the second filter and the 4th liang of pass joint, be connected toThe 9th liang of pass ball valve, the 9th liang of pass ball valve and the 4th liang of pass joint, the 8th liang of pass ball valve, vacuum system jointCoordinate, for thermal control loop is vacuumized.
Between described second liang of pass ball valve and four-way connection, be also connected with Pressure gauge.
Between described the 6th liang of pass ball valve and pressure-regulating valve, be also connected with pressure sensor.
Between described the 3rd liang of pass ball valve and vacuum system joint, be also connected with vacuum meter.
The first described filter and the second filter are that high order is counted filter assemblies, comprise plinth, briquetting,High order is counted filter, jacking block, plug, spiral shell cover, O type circle and packing ring; Plinth is cylindrical cavity body structure,One end is cylindrical hole, and the other end is the cylindrical cavity of three sections of different inner diameters, and internal diameter increases successively, internal diameter minimumOne section near the cylinder nose end of intracavity structure and the cylindrical briquetting of two axial porous is housed, two pressuresBetween piece, be positioned with high order and count filter, packing ring and plug are installed successively, are positioned at internal diameter for one section of internal diameter maximumIn inner chamber body between one section of minimum one section and internal diameter maximum, interference fits is installed jacking block; The circle of plinthPost chamber is external thread structure and is connected with spiral shell cover; Mounting O-shaped rings on the excircle of plug; Plinth and spiral shell coverForm structural support, plug, O type circle and packing ring form seal.
Spacecraft thermal control loop working medium methods for filling, is characterized in that step is as follows:
(1) demarcate the volume of thermal control loop working medium charging system pipeline self, and standard is filled to bottle vacuumize;
(2) according to the volume of the charging system pipeline own vol obtaining in step (1) and thermal control loop,In conjunction with the desired pressure and temperature of filling process, calculate and fill required working medium quality;
(3) fill quality according to the definite hot working fluid of step (2), hot working fluid injection standard is filled to bottle alsoThe confirmation of weighing;
(4) heating standard fills bottle and makes liquid refrigerant transfer gradually superheated steam to and inject thermal control loop;
(5) pressure occurring while filling bottle liquid and vaporize completely according to standard and temperature jump variation, judgement is filledThe end of process of assembling;
(6) standard is filled to bottle and finally weigh, confirm the actual hot working fluid quality filling of thermal control loop.
The present invention's advantage is compared with prior art: spacecraft thermal control loop working medium charging system and fillingDress method, adopts integrated design for disassembly method, by the migration of hot working fluid phase equilibrium principle control quality,The Portable movable of feasible system and on-the-spot high accuracy fill, for the hot working fluid of two-phase fluid thermal control loop fillsDress has proposed effective solution; In addition, real by adding high order to count filter assemblies in charging systemNow the cleaning of thermal control loop working medium is filled, improved the strainability of system.
Brief description of the drawings
Fig. 1 is charging system structure chart of the present invention;
Fig. 2 is that the high order of the present invention is counted filter assemblies structure chart.
Detailed description of the invention
As shown in Figure 1, be the structure chart of charging system of the present invention, comprising: standard fills a bottle Q1 two logical ballsValve V1, V2, V3, V4, V5, V6, V8 and V9, pressure-regulating valve V7, two pass joint J1, J3And J4, four-way connection J2, vacuum system joint J5, filter F 1 and F2, Pressure gauge M1, pressureSensor M2 and vacuum meter M3; Standard fill bottle Q1 successively through two pass ball valve V1, two pass joint J1,Two pass ball valve V2 and Pressure gauge M1 are connected to four-way connection J2; By four-way connection J2 by charging system pipeRoad is divided into three tunnels, and the first via is passed through filter F1, two pass ball valve V4, two pass joint J3 and two pass ball valves successivelyV5 is connected with working medium stock bottle Q2, fills bottle for the hot working fluid in working medium stock bottle Q2 is filled with to standardQ1; The second tunnel is connected with vacuum system joint J5 through two pass ball valve V3, vacuum meter M3 successively, for rightStandard fills a bottle Q1 and vacuumizes; Third Road is adjusted through two pass ball valve V6, pressure sensor M2, pressure successivelyJoint valve V7, filter F 2, two pass joint J4, two pass ball valve V8 are connected with thermal control loop R1, forThe hot working fluid that standard is filled in bottle Q1 is filled with thermal control loop R1; Vacuum meter M3 and vacuum system joint J5Tie point and filter F 2 and the tie point of two pass joint J4 between be connected to two pass ball valve V9.
The methods for filling of this charging system is: as shown in Figure 1, close two pass ball valve V4, V6, V9, openOpen two pass ball valve V1, V2, V3, be connected with vacuum system by vacuum adapter J5, standard is filled to bottleQ1 vacuumizes, and determines whether to reach vacuum state by vacuum meter M3; Close two pass ball valve V3, V6,Open two pass ball valve V1, V2, V4, V5, connect by working medium stock bottle Q2, two pass ball valve V5, twoJ3, two pass ball valve V4, filter F 1, four-way connection J2, two pass ball valve V2, two pass joint J1,Two pass ball valve V1 and standard fill bottle Q1 and form fluid infusion stream, and hot working fluid is added to mark from stock bottle Q2Standard fills a bottle Q1; Close stop valve V2, V3, V4, opening stop valve V6, V8, V9, pass through vacuumJoint J5 is connected with vacuum system, and thermal control loop is vacuumized; Close stop valve V3, V4, V9, openStop valve V1, V2, V6, V7, V8, fill a bottle Q1, two pass ball valve V1, two pass joints by standardJ1, two pass ball valve V2, two pass joint J2, two pass ball valve V6, two pass ball valve V7, filter F 2, twoPass joint J4, two pass ball valve V8, thermal control loop R1 formation fill stream, and standard is filled in bottle Q1Hot working fluid heating is filled into thermal control loop R1 after liquid phase becomes gas phase, when standard fills the temperature of bottle Q1Step rises or when the reading fast-descending of Pressure gauge M1, shows that standard fills and in bottle Q1, do not had liquidPhase working medium, filling process finishes.
For the precision that ensures that thermal control loop fills, must demarcate the volume that fills stream self, finally reallyRecognize and actually revised while filling quality. Thermal control loop actual fills quality=fill front standard to fill a bottle Q1The rear standard of quality-the fill quality that fills bottle Q1-the fill working medium quality of stream remnants. At concrete meterWhen calculation fills the working medium quality of stream remnants, can adopt following computational methods: in system shown in Figure 1,Substitute thermal control loop and vacuumize taking another one standard jar (establishing volume as v2); To standard jar, Q1 (establishesVolume is v1) be filled with the high pure nitrogen (being considered as perfect gas) of certain pressure; Close two pass ball valve V3, V4,V8, V9, open two pass ball valve V1, V2, V6, V7, and high pure nitrogen is filled to the whole stream that fills, steadyAfter fixed, record the now reading value p1 of pressure sensor M2; Open two pass ball valve V8, high pure nitrogen is filled withTo additional standard jar, after stablizing, record the now reading value p2 of pressure sensor M2; According to p1, p2,V1, v2, can calculate the volume that fills stream self according to formula v=(p2v2+p2v1-p1v1)/(p1-p2);According to the volume V of the stream calculating self, fill working medium temperature T, filled the saturated of rear working mediumPressure P, according to formula M0=PV/RT can calculate the working medium quality that fills stream remnants.
For ensureing to fill the clean of working medium, at the fluid infusion stream of charging system of the present invention with fill stream and respectively installA high order count filter assemblies, i.e. F1 and F2. As shown in Figure 2, this kind high order counted filter assembliesComprise plinth 1, briquetting 2, high order count filter 3, jacking block 4, plug 5, spiral shell cover 6, O type circle 7,Packing ring 8. Plinth 1 is cylindrical cavity body structure, and one end is cylindrical hole, and the other end is three sections of different inner diametersCylindrical cavity, internal diameter increases successively, one section of the internal diameter minimum cylinder nose end near intracavity structure and being equipped withBetween 2, two briquettings 2 of cylindrical briquetting of two axial porous, be positioned with high order and count filter 3, inOne section of footpath maximum packing ring 8 and plug 5 are installed successively, at one section and a section of internal diameter maximum of internal diameter minimumBetween inner chamber body, interference fits is installed jacking block 4; The cylindrical cavity of plinth 1 be external thread structure and with spiral shell cover 6Connect; Mounting O-shaped rings 7 on the excircle of plug 5; Plinth 1 and spiral shell cover 6 form structural support,Plug 5, O type circle 7 and packing ring 8 form seal; Filter 3 can be selected the stainless steel cloth of high order number.
Claims (6)
1. spacecraft thermal control loop working medium charging system, is characterized in that comprising: standard fill bottle (Q1),First liang of pass ball valve (V1), second liang of pass ball valve (V2), the 3rd liang of pass ball valve (V3), the 4th liang of logical ballValve (V4), the 5th liang of pass ball valve (V5), the 6th liang of pass ball valve (V6), the 8th liang of pass ball valve (V8),The 9th liang of pass ball valve (V9), pressure-regulating valve (V7), first liang of pass joint (J1), the 3rd liang of pass joint(J3), the 4th liang of pass joint (J4), four-way connection (J2), vacuum system joint (J5), first filterDevice (F1) and the second filter (F2); Standard fill bottle (Q1) successively through first liang of pass ball valve (V1),First liang of pass joint (J1), second liang of pass ball valve (V2) are connected to four-way connection (J2); Connect by four-wayThe pipeline of charging system is divided into three tunnels by head (J2), and the first via is successively through the first filter (F1), the 4thTwo pass ball valves (V4), the 3rd liang of pass joint (J3) and the 5th liang of pass ball valve (V5) and working medium stock bottle phaseConnect, fill bottle (Q1) for the hot working fluid in working medium stock bottle being filled with to standard; The 3rd liang, the second tunnel is logicalBall valve (V3), vacuum system joint (J5) are connected with vacuum extractor, for standard being filled to bottle (Q1)Vacuumize; Third Road successively through the 6th liang of pass ball valve (V6), pressure-regulating valve (V7), the second filter (F2),The 4th liang of pass joint (J4) is connected with thermal control loop with the 8th liang of pass ball valve (V8), for standard is filledHot working fluid in bottle (Q1) is filled with thermal control loop; The 3rd liang of pass ball valve (V3) and vacuum system joint (J5)Tie point and the second filter (F2) and the tie point of the 4th liang of pass joint (J4) between be connected to the 9thTwo pass ball valves (V9), the 9th liang of pass ball valve (V9) and the 4th liang of pass joint (J4), the 8th liang of pass ball valve (V8),Vacuum system joint (J5) coordinates, for thermal control loop is vacuumized.
2. spacecraft thermal control loop working medium charging system according to claim 1, is characterized in that:Between described second liang of pass ball valve (V2) and four-way connection (J2), be also connected with Pressure gauge.
3. spacecraft thermal control loop working medium charging system according to claim 1, is characterized in that:Between described the 6th liang of pass ball valve (V6) and pressure-regulating valve (V7), be also connected with pressure sensor.
4. spacecraft thermal control loop working medium charging system according to claim 1, is characterized in that:Between described the 3rd liang of pass ball valve (V3) and vacuum system joint (J5), be also connected with vacuum meter.
5. spacecraft thermal control loop working medium charging system according to claim 1, is characterized in that:Described the first filter (F1) and the second filter (F2) are that high order is counted filter assemblies, comprise jointSeat (1), briquetting (2), high order are counted filter (3), jacking block (4), plug (5), spiral shell cover (6), OType circle (7) and packing ring (8); Plinth (1) is cylindrical cavity body structure, and one end is cylindrical hole, anotherEnd is the cylindrical cavity of three sections of different inner diameters, and internal diameter increases successively, and one section of internal diameter minimum near intracavity structureCylinder nose end and the cylindrical briquetting (2) of two axial porous is housed, fixed between two briquettings (2)Position has high order to count filter (3), one section of internal diameter maximum packing ring (8) and plug (5) is installed successively, positionIn the inner chamber body between one section of internal diameter minimum and internal diameter maximum one section, interference fits is installed jacking block (4);The cylindrical cavity of plinth (1) is external thread structure and is connected with spiral shell cover (6); The excircle of plug (5)Upper mounting O-shaped rings (7); Plinth (1) and spiral shell cover (6) form structural support, plug (5), OType circle (7) and packing ring (8) form seal.
6. spacecraft thermal control loop working medium methods for filling, is characterized in that step is as follows:
(1) demarcate the volume of thermal control loop working medium charging system pipeline self, and standard is filled to bottle vacuumize;
(2) according to the volume of the charging system pipeline own vol obtaining in step (1) and thermal control loop,In conjunction with the desired pressure and temperature of filling process, calculate and fill required working medium quality;
(3) fill quality according to the definite hot working fluid of step (2), hot working fluid injection standard is filled to bottle alsoThe confirmation of weighing;
(4) heating standard fills bottle and makes liquid refrigerant transfer gradually superheated steam to and inject thermal control loop;
(5) pressure occurring while filling bottle liquid and vaporize completely according to standard and temperature jump variation, judgement is filledThe end of process of assembling;
(6) standard is filled to bottle and finally weigh, confirm the actual hot working fluid quality filling of thermal control loop.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200710082606.4A CN106134385B (en) | 2007-10-31 | 2007-10-31 | Spacecraft thermal control loop working medium charging system and methods for filling thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200710082606.4A CN106134385B (en) | 2007-10-31 | 2007-10-31 | Spacecraft thermal control loop working medium charging system and methods for filling thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106134385B true CN106134385B (en) | 2011-10-19 |
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ID=57251123
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200710082606.4A Expired - Fee Related CN106134385B (en) | 2007-10-31 | 2007-10-31 | Spacecraft thermal control loop working medium charging system and methods for filling thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106134385B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108106471A (en) * | 2017-12-15 | 2018-06-01 | 陕西仙童科技有限公司 | A kind of accurate filling system of heat-pipe working medium and filling method |
| CN111536414A (en) * | 2020-06-11 | 2020-08-14 | 大连大特气体有限公司 | High-precision gas filling device and filling method |
-
2007
- 2007-10-31 CN CN200710082606.4A patent/CN106134385B/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108106471A (en) * | 2017-12-15 | 2018-06-01 | 陕西仙童科技有限公司 | A kind of accurate filling system of heat-pipe working medium and filling method |
| CN111536414A (en) * | 2020-06-11 | 2020-08-14 | 大连大特气体有限公司 | High-precision gas filling device and filling method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR03 | Grant of secret patent right | ||
| DC01 | Secret patent status has been lifted | ||
| DCSP | Declassification of secret patent | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20111019 |