CN102507197B - 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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- CN102507197B CN102507197B CN201110300204.3A CN201110300204A CN102507197B CN 102507197 B CN102507197 B CN 102507197B CN 201110300204 A CN201110300204 A CN 201110300204A CN 102507197 B CN102507197 B CN 102507197B
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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, be the solid lithium propellant constant temperature liquid state conveying device 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, there is the advantages such as high specific impulse, high thrust scope, long-life, high control precision, repeated starting, in the tasks such as spacecraft rail control, survey of deep space and interplanetary flight, there is broad prospect of application.
It is propellant that magnetoplasmadynamics engine can be take hydrogen, lithium, neon, argon, xenon etc., utilize magnetic field and Interaction Law of Electric Current to generate Lorentz force and come accelerate plasma state propellant to produce thrust, be therefore also referred to as Lorentz accelerator (Lorentz Force Accelerator).The bar-shaped negative electrode that the citation form of MPDT is taper by head and forming around the cylindrical anode of negative electrode.During MPDT work, by electric discharge between negative electrode and anode, form electric arc, the high-temperature plasma that propellant forms.For self-field magnetoplasmadynamics engine, electric current generates Induced magnetic field by plasma, and the magnetic field of inducting and Interaction Law of Electric Current form axial Lorentz force, accelerates propellant and discharges engine generation thrust; For externally-applied magnetic field magnetoplasmadynamics engine, propellant is realized acceleration under the acting in conjunction of externally-applied magnetic field, Induced magnetic field and electric current.
By ground experiment, the various performances of MPDT are studied just worldwide and carried out.Experimental test shows that lithium can provide outstanding propulsive performance for magnetoplasmadynamics engine, is the first-selection of magnetoplasmadynamics engine propellant.Effectively realizing is the basis of carrying out correlation test to the removing of lithium magnetoplasmadynamics engine propellant feed and propellant feed pipeline and maintenance, directly affects test effect.
Summary of the invention
The object of the present invention is to provide a kind of solid lithium propellant constant temperature liquid state conveying device with blow-line purging's function, the liquid propellant feed of magnetoplasmadynamics engine that to be applicable to take solid alkali metal lithium be propellant, the propellant adopting for lithium magnetoplasmadynamics engine is the situation of solid at normal temperatures, solved a difficult problem for the liquefaction of propellant solid alkali metal lithium controllable temperature and precise control of flew, and effective removing of liquid lithium propellant in assurance pipeline, realizes clean and test unit reusable of pipeline.
The present invention has the solid lithium propellant constant temperature liquid state conveying device of blow-line purging's function, comprises liquid lithium propellant feed separating device and argon gas gas circuit separating device.
Described liquid lithium propellant feed separating device comprises 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 lithium tank outer wall.Lithium tank bottom is communicated with lithium transfer tank bottom by the first propellant pipeline.Described lithium transfer tank bottom is connected with magnetoplasmadynamics engine by the second propellant pipeline, and it is inner that described piston is arranged on lithium transfer tank, by stepper motor driven plunger, in lithium transfer tank, carries out piston movement.Lithium transfer tank heating film is installed on lithium transfer tank outer wall, on the first propellant pipeline outer wall and the second propellant pipeline outer wall, is separately installed with lithium transfer tank heating film and propellant pipeline heating film.
Described argon gas gas circuit separating device comprises argon gas gas cylinder, argon gas pipeline, hand stop valve and filtrator; Wherein, argon gas gas cylinder is communicated with lithium tank by argon gas pipeline; Inlet end place at argon gas pipeline is provided with hand stop valve and filtrator.
The invention has the advantages that:
1, conveying device of the present invention, for the specific (special) requirements of liquid propellant pipeline scavenge unit in lithium magnetoplasmadynamics rocket engine ground test, adopts argon gas gas circuit separating device that high pressure swept-off gases is provided; Tank and feeding pipe with heating film make propellant in 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, in apparatus of the present invention, pass through to regulate stepper motor job 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 ground experiment the liquid lithium propellant of magnetoplasmadynamics engine constant temperature and supply with problem, can make propellant effectively, to magnetoplasmadynamics engine, carry;
4, solved the liquid concrete application difficult problem of supplying with related pipeline removing of solid propellant in lithium magnetoplasmadynamics rocket engine ground test, for further in-depth magnetoplasmadynamics engine research and engineering application provide guarantee.
Accompanying drawing explanation
Fig. 1 is conveying device one-piece construction schematic diagram of the present invention;
Fig. 2 is the blow-line purging's method flow diagram based on conveying device of the present invention;
Fig. 3 is the carrying method process flow diagram based on conveying device of the present invention.
In figure:
1-liquid lithium propellant feed separating device 2-argon gas gas circuit separating device 3-magnetoplasmadynamics engine
4-vacuum chamber 101-lithium tank 102-lithium transfer tank
103-piston 104-stepper motor 105-the first propellant pipeline
106-the second propellant feed pipeline 107-lithium tank heating film 108-lithium transfer tank heating film
109-propellant pipeline heating film 110-first temperature sensor 111-the 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 will be further described.
A kind of solid lithium propellant constant temperature liquid state conveying device with blow-line purging's function of the present invention, comprises liquid lithium propellant feed separating device 1 and argon gas gas circuit separating device 2.
Described liquid lithium propellant feed separating device 1 is used for carrying 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, to the solid-state lithium heating in lithium tank 101, making it change liquid lithium into; Lithium tank 101 bottoms are communicated with lithium transfer tank 102 bottoms by the first propellant pipeline 105, by argon gas gas circuit separating device 2, in lithium tank 1, constantly pour argon gas, owing to there not being chemical reaction between argon gas and lithium, therefore by argon gas, push the liquid lithium in lithium tank 101, it can be entered in lithium transfer tank 102 by the first propellant pipeline 105.Described lithium transfer tank 102 bottoms are connected with magnetoplasmadynamics engine 3 by the second propellant pipeline 106, described piston 103 is arranged on lithium transfer tank 102 inside, by stepper motor 104 driven plunger 103, in lithium transfer tank 102, carry out piston movement, the liquid lithium promoting in lithium transfer tank 102 enters into magnetoplasmadynamics engine 3 with the second propellant pipeline 106.Because argon gas continues to pass into, make the first propellant pipeline 105 in airtight conditions, the liquid lithium in lithium transfer tank 102 can be back in lithium tank 101 with the first propellant pipeline 105.Described stepper motor 104 also can be used to control piston 103 and carries out the speed of piston movement, thereby reaches the flow control of propellant.In order to remain liquid in the process that makes liquid lithium arrive magnetoplasmadynamics engine 3 by lithium transfer tank 102, therefore the present invention is provided 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 all installed, coming is respectively 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 the first temperature sensor 110, the second temperature sensor 111 and three-temperature sensor 112, be used for respectively monitoring the temperature of lithium tank 101, lithium transfer tank 102 and the second propellant pipeline 106, liquid lithium in assurance lithium tank 101, lithium transfer tank 102 and the second propellant pipeline 106 is all the time in liquid state, and the first temperature sensor 110, the 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 separating device 1 is arranged in the vacuum chamber 4 of vacuum environment.
Described argon gas gas circuit separating device 2 comprises 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 is communicated with the lithium tank 101 in liquid lithium propellant feed separating device 1 by argon gas pipeline 202.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 in argon gas and obtains impurity, guarantees the cleanliness of argon gas in argon gas pipeline 202.Pressure transducer 205 is also installed on argon gas pipeline 202, is used for monitoring the pressure of argon gas pipeline 202 interior gases.After opening hand stop valve 203, the argon gas in argon gas gas cylinder 201 arrives lithium tank 101 through argon gas pipeline 202.
In conveying device of the present invention, each pipeline is stainless-steel tube; the material adopting is 1Cr18Ni9Ti; there is good corrosion resistance; 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 process acid wash passivation after welding; carry out again Ultrasonic Cleaning, nitrogen blow-off, and then guarantee the cleanliness of conveying device of the present invention.
Based on the above-mentioned carrying method with the solid lithium propellant constant temperature liquid state conveying device of blow-line purging's function, by following seven steps, realize:
Step 1: remaining lithium propellant in heating liquid lithium propellant feed separating 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 respectively residual liquid lithium propellant in lithium tank 101, lithium transfer tank 102 and the second propellant pipeline 106; And monitor the first temperature sensor 110, the second temperature sensor 111 and three-temperature sensor 112, make the temperature of lithium tank 101, lithium transfer tank 102 and the second propellant pipeline 106 within the scope of testing requirements, keep heating liquid lithium propellant residual in lithium tank 101, lithium transfer tank 102 and the first propellant pipeline 105, the second propellant pipeline 106 in liquid state.
Step 2: blow down the impurity in liquid lithium propellant feed separating device;
Open hand stop valve 203, make argon gas enter into argon gas pipeline 202, through filtrator 104, filter out the impurity in argon gas; Observation argon gas gas circuit tensimeter 105, and regulate hand stop valve 103, keep the pressurization gas pressure providing to lithium tank 101 within the scope of testing requirements.
Step 3: further blow down the impurity in liquid lithium propellant feed separating device 1;
After the first propellant pipeline 105 has liquid lithium to blow out with lithium transfer tank 102 connectivity parts, start stepper motor 104, promoting piston 103 moves downward, the supercharging of realization to swept-off gases, the blowing effect of strengthening to the second propellant pipeline 106, finally realizes the blowing work to impurity in pipeline in solid lithium propellant constant temperature liquid state conveying device.
Step 4: stop impurity blowing work in liquid lithium propellant feed separating device 1;
After blowing, 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 the above-mentioned carrying method with the solid lithium propellant constant temperature liquid state conveying device of blow-line purging's function that the present invention also provides, and by following three steps, realizes:
Step 1: put into solid lithium in lithium tank 101;
In lithium tank 101, put into solid lithium, the solid-state lithium in lithium tank 101 is heated and transfers liquid state to, and again opens hand stop valve 203, in lithium tank 101, passes into argon gas.
Step 2: carry propellant in magnetoplasmadynamics engine 3;
By argon gas, push in lithium tank 101 and obtain liquid lithium, 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, adjust stepper motor 104 rotating speeds and control uninterrupted, by piston 103, make the liquid lithium in lithium tank 101 enter into the second propellant pipeline 106, finally arrive magnetoplasmadynamics engine 3.
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 cooling rear solidify of lithium propellant residual in the pipeline in liquid lithium propellant feed separating device 1, impact is used next time, after off-test, keeps all heating film in running order.
When needs recover 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 again of liquid lithium.
Claims (9)
1. a solid lithium propellant constant temperature liquid state conveying device with blow-line purging's function, is characterized in that: comprise liquid lithium propellant feed separating device and argon gas gas circuit separating device;
Described liquid lithium propellant feed separating device comprises 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 lithium tank outer wall; Lithium tank bottom is communicated with lithium transfer tank bottom by the first propellant pipeline; Described lithium transfer tank bottom is connected with magnetoplasmadynamics engine by the second propellant feed pipeline, and it is inner that described piston is arranged on lithium transfer tank, by stepper motor driven plunger, in lithium transfer tank, carries out piston movement; Lithium transfer tank heating film is installed on lithium transfer tank outer wall, on the first propellant pipeline outer wall and the second propellant feed pipeline outer wall, is separately installed with lithium transfer tank heating film and propellant pipeline heating film;
Described argon gas gas circuit separating device comprises argon gas gas cylinder, argon gas pipeline, hand stop valve and filtrator; Wherein, argon gas gas cylinder is communicated with lithium tank by argon gas pipeline; Inlet end place at argon gas pipeline is provided with hand stop valve and filtrator.
2. a kind of solid lithium propellant constant temperature liquid state conveying device with blow-line purging's function as claimed in claim 1, is characterized in that: described liquid lithium propellant feed separating device is arranged in vacuum chamber.
3. a kind of solid lithium propellant constant temperature liquid state conveying device with blow-line purging's function as claimed in claim 1, is characterized in that: on described lithium tank outer wall, lithium transfer tank outer wall and the second propellant feed pipeline outer wall, be separately installed with the first temperature sensor, the second temperature sensor and three-temperature sensor.
4. a kind of solid lithium propellant constant temperature liquid state conveying device with blow-line purging's function as claimed in claim 3, is characterized in that: described the first temperature sensor, the second temperature sensor and three-temperature sensor all adopt PT100.
5. a kind of solid lithium propellant constant temperature liquid state conveying device with blow-line purging's function as claimed in claim 1, is characterized in that: on described argon gas pipeline, pressure transducer is installed.
6. a kind of solid lithium propellant constant temperature liquid state conveying device with blow-line purging's function as claimed in claim 1, it is characterized in that: described argon gas pipeline, the first propellant pipeline, the second propellant feed pipeline are stainless-steel tube, and the material of employing is 1Cr18Ni9Ti.
7. a kind of solid lithium propellant constant temperature liquid state conveying device with blow-line purging's function as claimed in claim 1; it is characterized in that: between described argon gas pipeline, the first propellant pipeline, the second propellant feed pipeline and argon gas gas cylinder, lithium tank, lithium transfer tank, all adopt argon arc welding or inert gas arc welding to connect; and process acid wash passivation after welding, then carry out Ultrasonic Cleaning, nitrogen blow-off.
8. a kind of blow-line purging's method with the solid lithium propellant constant temperature liquid state conveying device of blow-line purging's function as claimed in claim 1, realizes by following four steps:
Step 1: remaining lithium propellant in heating liquid lithium propellant feed separating device;
Before on-test, open lithium tank heating film, lithium transfer tank heating film and the second propellant feed pipeline heating film;
Step 2: blow down the impurity in liquid lithium propellant feed separating device;
Open hand stop valve, and regulate hand stop valve, keep the gaseous tension providing to lithium tank within the scope of testing requirements;
Step 3: further blow down the impurity in liquid lithium propellant feed separating device;
After the first propellant pipeline and lithium transfer tank connectivity part have liquid lithium to blow out, start stepper motor, promote piston and move downward;
Step 4: stop impurity blowing work in liquid lithium propellant feed separating device;
After blowing, close stepper motor, close hand stop valve simultaneously; Keep lithium tank heating film, lithium transfer tank heating film and the second propellant feed pipeline heating film in running order.
9. a kind of carrying method with the solid lithium propellant constant temperature liquid state conveying device of blow-line purging's function as claimed in claim 1, by following three steps, realize:
Step 1: put into solid lithium in lithium tank;
In lithium tank, put into solid lithium, open lithium tank heating film, lithium transfer tank heating film and the second propellant feed pipeline heating film in running order; And open hand stop valve, in lithium tank, pass into argon gas; By argon gas, push the liquid lithium in lithium tank, make liquid lithium with the first propellant pipeline, enter into lithium transfer tank;
Step 2: carry propellant in magnetoplasmadynamics engine;
Start stepper motor, promote reciprocating motion of the pistons, by piston, make the liquid lithium in lithium tank enter into the second propellant feed pipeline, finally arrive magnetoplasmadynamics engine;
Step 3: stop the supply of propellant;
After experiment finishes, close stepper motor, close hand stop valve simultaneously; When needs recover propellant conveying, open hand stop valve, open stepper motor simultaneously and make pistons work.
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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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| 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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| CN102507197B true CN102507197B (en) | 2014-01-22 |
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| 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 |
| CN109407719B (en) * | 2018-11-27 | 2020-12-04 | 上海空间推进研究所 | Target point compensation propellant temperature control device |
| CN111622866B (en) * | 2020-05-15 | 2021-09-24 | 大连理工大学 | Constant force spring type storage tank for liquid propellant |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
-
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 |
|---|---|---|---|---|
| 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 |
| 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 |
| WO2002015216A1 (en) * | 2000-08-15 | 2002-02-21 | The Regents Of The University Of California | Hydrogen scavengers |
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