CN102507197A - Solid lithium propelling agent constant temperature liquid state conveying device with pipeline blowing down function - Google Patents
Solid lithium propelling agent constant temperature liquid state conveying device with pipeline blowing down function Download PDFInfo
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- CN102507197A CN102507197A CN2011103002043A CN201110300204A CN102507197A CN 102507197 A CN102507197 A CN 102507197A CN 2011103002043 A CN2011103002043 A CN 2011103002043A CN 201110300204 A CN201110300204 A CN 201110300204A CN 102507197 A CN102507197 A CN 102507197A
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Abstract
The invention relates to a solid lithium propelling agent constant temperature liquid state conveying device with a pipeline blowing down function. The conveying device comprises a liquid state lithium propelling agent supplying sub-device and an argon gas path sub-device; in the liquid state lithium propelling agent supplying sub-device, a heating film is started up, a solid lithium propelling agent in a lithium storage box is heated and liquefied under the condition that the temperature monitoring is realizable, argon gas provided by the argon gas path sub-device pushes a liquid state lithium propelling agent in the lithium storage box in the liquid state lithium propelling agent supplying sub-device to enter a lithium transferring storage box along a propelling agent pipeline; a piston pushes the lithium transferring storage box to obtain liquid state lithium, and the liquid state lithium is transferred to a magnetoplasma dynamics engine along the propelling agent pipeline; and the argon gas path sub-device provides argon gas so as to implement the blowing down function of residual liquid state lithium in the liquid state lithium propelling agent supplying sub-device.
Description
Technical field
The present invention relates to magnetoplasmadynamics engine (MPDT) ground experiment field, specifically, is the liquid transport of the solid lithium propellant constant temperature with blow-line purging's function in a kind of magnetoplasmadynamics engine (MPDT) ground experiment field.
Background technology
Magnetoplasmadynamics engine (MPDT) is a kind of typical electromagnetic type space electric propulsion system; Have advantages such as high specific impulse, high thrust scope, long-life, high control accuracy, repeated starting, in tasks such as spacecraft rail control, survey of deep space and interplanetary flight, have broad prospect of application.
The magnetoplasmadynamics engine can be a propellant with hydrogen, lithium, neon, argon, xenon etc.; Utilize magnetic field and Interaction Law of Electric Current to generate Lorentz force and come accelerate plasma attitude propellant to produce thrust, therefore also be called as Lorentz accelerator (Lorentz Force Accelerator).The citation form of MPDT is the bar-shaped negative electrode of taper by head and forms around the cylindrical anode of negative electrode.During MPDT work, form electric arc through discharge between negative electrode and anode, the high-temperature plasma that propellant forms.For self-field magnetoplasmadynamics engine, electric current generates the magnetic field of inducting through plasma, and magnetic field of inducting and Interaction Law of Electric Current form axial Lorentz force, quickens propellant and discharges engine producing thrust; For externally-applied magnetic field magnetoplasmadynamics engine, propellant is realized quickening under the acting in conjunction of externally-applied magnetic field, induct magnetic field and electric current.
Through ground experiment the various performances of MPDT are studied just worldwide and to be carried out.Experimental test shows that lithium can provide outstanding propulsive performance for the magnetoplasmadynamics engine, is the first-selection of magnetoplasmadynamics engine propellant.Realize that effectively removing and maintenance to lithium magnetoplasmadynamics engine propellant feed and propellant feed pipeline are the bases of carrying out correlation test, directly influence test effect.
Summary of the invention
The object of the present invention is to provide a kind of liquid transport of solid lithium propellant constant temperature with blow-line purging's function; Be applicable to the solid alkali metal lithium to be the liquid propellant feed of magnetoplasmadynamics engine of propellant; The propellant that is adopted to lithium magnetoplasmadynamics engine is the situation of solid at normal temperatures; Solved the accurately difficult problem of control of liquefaction of propellant solid alkali metal lithium controllable temperature and flow; And effective removing of liquid lithium propellant in the assurance pipeline realizes cleaning and test unit reusable of pipeline.
The present invention has the liquid transport of solid lithium propellant constant temperature of blow-line purging's function, comprises that the liquid lithium propellant feed divides device and argon gas gas circuit to divide device.
Said liquid lithium propellant feed divides device to comprise lithium tank, lithium transfer tank, piston, stepper motor, the first propellant pipeline and the second propellant feed pipeline.Wherein, lithium tank heating film is installed on the lithium tank outer wall.Lithium tank bottom is communicated with lithium transfer tank bottom through the first propellant pipeline.Said lithium transfer tank bottom links to each other with the magnetoplasmadynamics engine through the second propellant pipeline, and it is inner that said piston is arranged on lithium transfer tank, in lithium transfer tank, carries out piston motion through the step motor drive piston.Lithium transfer tank heating film is installed on the lithium transfer tank outer wall, is separately installed with lithium transfer tank heating film and propellant pipeline heating film on the first propellant pipeline outer wall and the second propellant pipeline outer wall.
Said argon gas gas circuit divides device to comprise argon gas gas cylinder, argon gas pipeline, hand stop valve and filtrator; Wherein, the argon gas gas cylinder is communicated with the lithium tank through the argon gas pipeline; Inlet end place at the argon gas pipeline is equipped with hand stop valve and filtrator.
The invention has the advantages that:
1, transport of the present invention adopts the argon gas gas circuit to divide device that high pressure swept-off gases is provided to the specific (special) requirements of liquid propellant pipeline scavenge unit in the test of lithium magnetoplasmadynamics engines ground; The tank and the feeding pipe that have heating film make propellant in the blowing process, keep liquid, and all device has been realized temperature monitoring simultaneously, has strengthened stability, practicality, ease for operation and the precision of feed system;
2, pass through in apparatus of the present invention to regulate stepper motor work control piston, realize the method for the secondary booster of swept-off gases, effectively improved the test efficiency of liquid lithium propellant pipeline blowing and the practicality of operation;
3, apparatus of the present invention can effectively solve in the ground experiment the liquid lithium propellant of magnetoplasmadynamics engine constant temperature and supply with problem, can make propellant effectively, carry to the magnetoplasmadynamics engine;
4, solved the liquid concrete application difficult problem of supplying with related pipeline removing of solid propellant in the test of lithium magnetoplasmadynamics engines ground, for further in-depth magnetoplasmadynamics engine research and practical applications provide guarantee.
Description of drawings
Fig. 1 is a transport one-piece construction synoptic diagram of the present invention;
Fig. 2 is the blow-line purging's method flow diagram based on transport of the present invention;
Fig. 3 is the carrying method process flow diagram based on transport of the present invention.
Among the figure:
1-liquid lithium propellant feed divides device 2-argon gas gas circuit to divide device 3-magnetoplasmadynamics engine
4-vacuum chamber 101-lithium tank 102-lithium transfer tank
The 103-piston 104-stepper motor 105-first propellant pipeline
The 106-second propellant feed pipeline 107-lithium tank heating film 108-lithium transfer tank heating film
The 109-propellant pipeline heating film 110-first temperature sensor 111-second temperature sensor
112-three-temperature sensor 201-argon gas gas cylinder 202-argon gas pipeline
203-hand stop valve 204-filtrator
Embodiment
Below in conjunction with accompanying drawing the present invention is further specified.
A kind of liquid transport of solid lithium propellant constant temperature with blow-line purging's function of the present invention comprises that the liquid lithium propellant feed divides device 1 and argon gas gas circuit to divide device 2.
Said liquid lithium propellant feed divides device 1 to be used for carrying the lithium propellant into magnetoplasmadynamics engine 3, comprises lithium tank 101, lithium transfer tank 102, piston 103, stepper motor 104, the first propellant pipeline 105 and the second propellant feed pipeline 106.Wherein, lithium tank 101 is used for holding the solid-state lithium as propellant; Lithium tank heating film 107 is installed on lithium tank 101 outer walls, is used for making it change liquid lithium into the solid-state lithium heating in the lithium tank 101; Lithium tank 101 bottoms are communicated with lithium transfer tank 102 bottoms through the first propellant pipeline 105; Divide device 2 in lithium tank 1, constantly to pour argon gas through the argon gas gas circuit; Owing to do not have chemical reaction between argon gas and the lithium; Therefore through the liquid lithium in the argon gas extruding lithium tank 101, it can be entered in the lithium transfer tank 102 through the first propellant pipeline 105.Said lithium transfer tank 102 bottoms link to each other with magnetoplasmadynamics engine 3 through the second propellant pipeline 106; Said piston 103 is arranged on lithium transfer tank 102 inside; In lithium transfer tank 102, carry out piston motion through stepper motor 104 driven plunger 103, the liquid lithium that promotes in the lithium transfer tank 102 enters into magnetoplasmadynamics engine 3 with the second propellant pipeline 106.Because argon gas continues to feed, and makes the first propellant pipeline 105 be in airtight conditions, and the liquid lithium in the lithium transfer tank 102 can be back in the lithium tank 101 with the first propellant pipeline 105.Said stepper motor 104 also can be used to control piston 103 and carries out the speed of piston motion, thereby reaches the flow control of propellant.Remain liquid state in order to make in the process of liquid lithium by lithium transfer tank 102 arrival magnetoplasmadynamics engines 3; Therefore the present invention is equipped with lithium transfer tank heating film 108 in lithium transfer tank 102 bottoms; And on the first propellant pipeline 105 and the second propellant pipeline, 106 outer walls propellant pipeline heating film 109 is installed all, coming respectively is the liquid lithium heating in lithium transfer tank 102 and the first propellant pipeline 105, the second propellant pipeline 106.On lithium tank 101 outer walls, lithium transfer tank 102 outer walls and the second propellant pipeline, 106 outer walls, be separately installed with first temperature sensor 110, second temperature sensor 111 and the three-temperature sensor 112; Be used for monitoring the temperature of lithium tank 101, lithium transfer tank 102 and the second propellant pipeline 106 respectively; Guarantee that the liquid lithiums in lithium tank 101, lithium transfer tank 102 and the second propellant pipeline 106 are in liquid state all the time, first temperature sensor 110, second temperature sensor 111 and three-temperature sensor 112 all adopt PT100.Because solid-state lithium has strong reducing property, in empty G&W, very easily polluted, therefore a whole set of liquid lithium propellant feed divides in the vacuum chamber 4 that device 1 is arranged on vacuum environment.
Said argon gas gas circuit divides device 2 to comprise argon gas gas cylinder 201, argon gas pipeline 202, hand stop valve 203 and filtrator 204.Wherein, argon gas gas cylinder 201 is used for containing argon gas, and argon gas gas cylinder 201 divides the lithium tank 101 in the device 1 to be communicated with through argon gas pipeline 202 and liquid lithium propellant feed.Hand stop valve 203 and filtrator 204 are installed at the inlet end place of argon gas pipeline 202, and hand stop valve 203 is used for controlling opening of argon gas pipeline 202 and cuts out, and filtrator 204 is used for filtering and gets impurity in the argon gas, guarantees the cleanliness of argon gas in the argon gas pipeline 202.Pressure transducer 205 also is installed on argon gas pipeline 202, is used for monitoring the pressure of gas in the argon gas pipeline 202.After opening hand stop valve 203, the argon gas in the argon gas gas cylinder 201 arrives lithium tank 101 through argon gas pipeline 202.
Each pipeline is stainless-steel tube in the transport of the present invention; The material that adopts is 1Cr18Ni9Ti; Has good anti-corrosion; Argon gas pipeline 202, the first propellant pipeline 105, the second propellant pipeline 106 and argon gas gas cylinder 201, lithium tank 101,102 of lithium transfer tanks all adopt argon arc welding or other inert gas arc weldings, can reduce the oxide of weld thus, and welding finish after the overpickling passivation; Carry out ultrasonic cleaning, nitrogen blow-off again, and then guarantee the cleanliness of transport of the present invention.
Based on above-mentioned carrying method, realize through following seven steps with liquid transport of solid lithium propellant constant temperature of blow-line purging's function:
Step 1: heating liquid lithium propellant feed divides lithium propellant remaining in the device 1;
Before on-test, open lithium tank heating film 107, lithium transfer tank heating film 108 and the second propellant pipeline heating film 109, heat residual liquid lithium propellant in lithium tank 101, lithium transfer tank 102 and the second propellant pipeline 106 respectively; And monitor first temperature sensor 110, second temperature sensor 111 and the three-temperature sensor 112; The temperature of lithium tank 101, lithium transfer tank 102 and the second propellant pipeline 106 is in the testing requirements scope, keeps that residual liquid lithium propellant is in liquid state in heating lithium tank 101, lithium transfer tank 102 and the first propellant pipeline 105, the second propellant pipeline 106.
Step 2: blow down the liquid lithium propellant feed and divide the impurity in the device;
Open hand stop valve 203, make argon gas enter into argon gas pipeline 202, filter out the impurity in the argon gas through filtrator 104; Observation argon gas gas circuit tensimeter 105, and regulate hand stop valve 103, keep being in the testing requirements scope to the pressurization gas pressure that lithium tank 101 provides.
Step 3: further blow down the liquid lithium propellant feed and divide the impurity in the device 1;
After treating the first propellant pipeline 105 and lithium transfer tank 102 places of connection having liquid lithium to blow out; Start stepper motor 104; Promoting piston 103 moves downward; Realization is strengthened the blowing effect to the second propellant pipeline 106 to the supercharging of swept-off gases, the final blowing work that realizes impurity in the pipeline in the liquid transport of solid lithium propellant constant temperature.
Step 4: stop the liquid lithium propellant feed and divide impurity blowing work in the device 1;
After blowing finishes, close stepper motor 104, close hand stop valve 203 simultaneously, stop air feed; Keep lithium tank heating film 107, lithium transfer tank heating film 108 and the second propellant pipeline heating film 109 in running order.
It is a kind of based on above-mentioned carrying method with liquid transport of solid lithium propellant constant temperature of blow-line purging's function that the present invention also provides, and realizes through following three steps:
Step 1: put into the solid lithium in the lithium tank 101;
In lithium tank 101, put into the solid lithium, the solid-state lithium in the lithium tank 101 is heated and transfers liquid state to, and opens hand stop valve 203 once more, in lithium tank 101, feeds argon gas.
Step 2: in magnetoplasmadynamics engine 3, carry propellant;
Through getting liquid lithium in the argon gas extruding lithium tank 101, make liquid lithium with the first propellant pipeline 105, enter into lithium transfer tank 102; Start stepper motor 104, promote piston 103 to-and-fro movements, adjustment stepper motor 104 rotating speed Control Flow size makes the liquid lithium in the lithium tank 101 enter into the second propellant pipeline 106 through piston 103, arrives magnetoplasmadynamics engine 3 at last.
Step 3: stop the supply of propellant;
After experiment finishes, close stepper motor 104 piston 102 motions are stopped, closing hand stop valve 203 simultaneously and interrupt the supply of argon gas, propellant is carried and is stopped.In order to prevent that the liquid lithium propellant feed from dividing lithium propellant residual in the pipeline in the device 1 cooling back to solidify, influence is used next time, after off-test, keeps all heating film in running order.
When needs recover the propellant conveying, open hand stop valve 203, in lithium tank 101, supply with argon gas, open stepper motor 104 simultaneously and make piston 103 work, realize the conveying once more of liquid lithium.
Claims (9)
1. the liquid transport of solid lithium propellant constant temperature with blow-line purging's function is characterized in that: comprise that the liquid lithium propellant feed divides device and argon gas gas circuit to divide device;
Said liquid lithium propellant feed divides device to comprise lithium tank, lithium transfer tank, piston, stepper motor, the first propellant pipeline and the second propellant feed pipeline; Wherein, lithium tank heating film is installed on the lithium tank outer wall; Lithium tank bottom is communicated with lithium transfer tank bottom through the first propellant pipeline; Said lithium transfer tank bottom links to each other with the magnetoplasmadynamics engine through the second propellant pipeline, and it is inner that said piston is arranged on lithium transfer tank, in lithium transfer tank, carries out piston motion through the step motor drive piston; Lithium transfer tank heating film is installed on the lithium transfer tank outer wall, is separately installed with lithium transfer tank heating film and propellant pipeline heating film on the first propellant pipeline outer wall and the second propellant pipeline outer wall;
Said argon gas gas circuit divides device to comprise argon gas gas cylinder, argon gas pipeline, hand stop valve and filtrator; Wherein, the argon gas gas cylinder is communicated with the lithium tank through the argon gas pipeline; Inlet end place at the argon gas pipeline is equipped with hand stop valve and filtrator.
2. a kind of according to claim 1 liquid transport of solid lithium propellant constant temperature with blow-line purging's function, it is characterized in that: said liquid lithium propellant feed divides device to be arranged in the vacuum chamber.
3. a kind of according to claim 1 liquid transport of solid lithium propellant constant temperature with blow-line purging's function is characterized in that: be separately installed with first temperature sensor, second temperature sensor and three-temperature sensor on said lithium tank outer wall, lithium transfer tank outer wall and the second propellant pipeline outer wall.
4. a kind of according to claim 1 liquid transport of solid lithium propellant constant temperature with blow-line purging's function, it is characterized in that: said first temperature sensor, second temperature sensor and three-temperature sensor all adopt PT100.
5. a kind of according to claim 1 liquid transport of solid lithium propellant constant temperature with blow-line purging's function is characterized in that: on the said argon gas pipeline pressure transducer is installed.
6. a kind of according to claim 1 liquid transport of solid lithium propellant constant temperature with blow-line purging's function; It is characterized in that: said argon gas pipeline, the first propellant pipeline, the second propellant pipeline are stainless-steel tube, and the material of employing is 1Cr18Ni9Ti.
7. a kind of according to claim 1 liquid transport of solid lithium propellant constant temperature with blow-line purging's function; It is characterized in that: all adopt argon arc welding or inert gas arc welding to connect between said argon gas pipeline, the first propellant pipeline, the second propellant pipeline and argon gas gas cylinder, lithium tank, lithium transfer tank; And welding finishes after ultrasonic cleaning, nitrogen blow-off are carried out in the overpickling passivation again.
8. a kind of blow-line purging's method with liquid transport of solid lithium propellant constant temperature of blow-line purging's function as claimed in claim 1, realize through following four steps:
Step 1: heating liquid lithium propellant feed divides lithium propellant remaining in the device;
Before on-test, open lithium tank heating film, lithium transfer tank heating film and the second propellant pipeline heating film;
Step 2: blow down the liquid lithium propellant feed and divide the impurity in the device;
Open hand stop valve, begin to and regulate hand stop valve, keep in the gaseous tension that the lithium tank provides is in the testing requirements scope.
Step 3: further blow down the liquid lithium propellant feed and divide the impurity in the device;
After treating the first propellant pipeline and the lithium transfer tank place of connection having liquid lithium to blow out, start stepper motor, promote piston and move downward;
Step 4: stop the liquid lithium propellant feed and divide impurity blowing work in the device;
After blowing finishes, close stepper motor, close hand stop valve simultaneously; Keep lithium tank heating film, lithium transfer tank heating film and the second propellant pipeline heating film in running order.
9. a kind of carrying method as claimed in claim 1 with liquid transport of solid lithium propellant constant temperature of blow-line purging's function, realize through following three steps:
Step 1: put into the solid lithium in the lithium tank;
In the lithium tank, put into the solid lithium, it is in running order to open lithium tank heating film, lithium transfer tank heating film and the second propellant pipeline heating film; And open hand stop valve, in the lithium tank, feed argon gas; Through getting liquid lithium in the argon gas extruding lithium tank, make liquid lithium with the first propellant pipeline, enter into lithium transfer tank;
Step 2: in the magnetoplasmadynamics engine, carry propellant;
Start stepper motor, promote reciprocating motion of the pistons, make the liquid lithium in the lithium tank enter into the second propellant pipeline, arrive the magnetoplasmadynamics engine at last through piston;
Step 3: stop the supply of propellant; Experiment is closed stepper motor after finishing, and closes hand stop valve simultaneously; When needs recover the propellant conveying, open hand stop valve, open stepper motor simultaneously and make pistons work.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110300204.3A CN102507197B (en) | 2011-09-29 | 2011-09-29 | Solid lithium propelling agent constant temperature liquid state conveying device with pipeline blowing down function |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201110300204.3A CN102507197B (en) | 2011-09-29 | 2011-09-29 | Solid lithium propelling agent constant temperature liquid state conveying device with pipeline blowing down function |
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| CN102507197A true CN102507197A (en) | 2012-06-20 |
| CN102507197B CN102507197B (en) | 2014-01-22 |
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| CN201110300204.3A Expired - Fee Related CN102507197B (en) | 2011-09-29 | 2011-09-29 | Solid lithium propelling agent constant temperature liquid state conveying device with pipeline blowing down function |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104571117A (en) * | 2013-10-29 | 2015-04-29 | 北京精密机电控制设备研究所 | Multichannel servo system controlled by direct force |
| CN108190047A (en) * | 2017-11-27 | 2018-06-22 | 上海空间推进研究所 | Spacecraft liquid alkali metal feedway |
| CN109407719A (en) * | 2018-11-27 | 2019-03-01 | 上海空间推进研究所 | Target spot compensates propellant temperature control device |
| CN111622866A (en) * | 2020-05-15 | 2020-09-04 | 大连理工大学 | Constant force spring type storage tank for liquid propellant |
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| US3595022A (en) * | 1967-04-01 | 1971-07-27 | Licentia Gmbh | Thermodynamic reaction drive |
| WO2002015216A1 (en) * | 2000-08-15 | 2002-02-21 | The Regents Of The University Of California | Hydrogen scavengers |
| US6367244B1 (en) * | 1997-05-09 | 2002-04-09 | Hy Pat Corporation | Propulsion system containing a mixed-phase propellant and a method for propelling an object with the same |
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2011
- 2011-09-29 CN CN201110300204.3A patent/CN102507197B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| GB885409A (en) * | 1958-04-14 | 1961-12-28 | Hexcel Products Inc | Fuel grains for rocket engines |
| US3595022A (en) * | 1967-04-01 | 1971-07-27 | Licentia Gmbh | Thermodynamic reaction drive |
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| WO2002015216A1 (en) * | 2000-08-15 | 2002-02-21 | The Regents Of The University Of California | Hydrogen scavengers |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104571117A (en) * | 2013-10-29 | 2015-04-29 | 北京精密机电控制设备研究所 | Multichannel servo system controlled by direct force |
| CN108190047A (en) * | 2017-11-27 | 2018-06-22 | 上海空间推进研究所 | Spacecraft liquid alkali metal feedway |
| CN109407719A (en) * | 2018-11-27 | 2019-03-01 | 上海空间推进研究所 | Target spot compensates propellant temperature control device |
| CN109407719B (en) * | 2018-11-27 | 2020-12-04 | 上海空间推进研究所 | Target point compensation propellant temperature control device |
| CN111622866A (en) * | 2020-05-15 | 2020-09-04 | 大连理工大学 | Constant force spring type storage tank for liquid propellant |
| CN111622866B (en) * | 2020-05-15 | 2021-09-24 | 大连理工大学 | Constant force spring type storage tank for liquid propellant |
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