CN202360313U - Propellant injection device for liquid pulse plasma thruster - Google Patents
Propellant injection device for liquid pulse plasma thruster Download PDFInfo
- Publication number
- CN202360313U CN202360313U CN2011204617572U CN201120461757U CN202360313U CN 202360313 U CN202360313 U CN 202360313U CN 2011204617572 U CN2011204617572 U CN 2011204617572U CN 201120461757 U CN201120461757 U CN 201120461757U CN 202360313 U CN202360313 U CN 202360313U
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- propellant
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- piston
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Abstract
The utility model relates to a propellant injection device for a liquid pulse plasma thruster. The propellant injection device is particularly suitable for trace injection for an electric thruster in which hydrocarbon, such as water or ethanol, is used as a liquid propellant and belongs to the technical field of propellant injection. The propellant injection device comprises a propellant storehouse, a connection piece and an injector, wherein the propellant storehouse comprises an air inlet nozzle, a top cover, a bottom cover, a barrel body, a pressure gauge, a piston, a liquid inlet, a liquid exhaust port and an air exhaust port; and the injector comprises a sleeve, an injection chamber and a sprayer. The propellant injection device has a simple structure and can supply trace liquid propellant to a discharging cavity of the liquid pulse plasma thruster, so that the problems of long injection response time, trace flow control difficulty and low control precision of the conventional electromagnetic valve are solved.
Description
Technical field
The utility model relates to a kind of propellant agent injection device that is used for the liquid pulse plasma thruster, and being specially adapted to adopt hydrocarbons such as water or ethanol in the electric thruster is the micro-spray of liquid propellant, belongs to propellant agent spray technical field.
Background technique
Pulsed plasma thruster (PPT) is a kind of electromagnetic push device; Have than leap high, low in energy consumption, be easy to integrated, control is convenient, response fast, can produce characteristics such as power is little on small but excellent true thrust pulse and the required star, the attitude and the track that are particularly suitable for moonlet are controlled.
Pulsed plasma thruster adopts solid propellant usually, and solid pulsed plasma thruster technology is simple in structure because of it, and development is ripe relatively.But also there are some tangible performance deficiencies, such as: whole efficiency is low, and propellant agent exists to lag behind ablates, and plume contamination is serious.
With respect to the solid pulsed plasma thruster, the power system that the liquid pulse plasma thruster is used as moonlet has remarkable advantages.At first, the ionization of liquid pulse plasma thruster is abundant, does not have the hysteresis ablation phenomenon, can reduce the amount of carrying of propellant agent on the star greatly, makes it in the long lifetime in future moonlet is used, occupy a clear edge; Secondly, the liquid pulse plasma thruster can carry out the propellant agent scheduling and share between different thrusters; At last, the liquid pulse plasma thruster since used working medium for being mostly water or hydrocarbon, the plume contamination that causes is less relatively.
For the liquid pulse plasma thruster, except igniting and charging circuit, the thruster body mainly comprises parts such as liquid injection device, cathode-anode plate, electric capacity, supporting part and spark plug.Wherein cathode-anode plate, electric capacity, supporting part and spark plug etc. are all same or similar with the solid pulsed plasma thruster, and injection device is that liquid pulse plasma thruster institute is peculiar, is the core technology and the research emphasis of the type thruster.It is accurately micro-propellant agent to be injected the discharging chamber of liquid pulse plasma thruster that injection device mainly acts on, thereby makes the liquid pulse plasma thruster can accomplish serial working procedure such as discharge, ablation, acceleration.Therefore design a kind of simple and effective liquid injection device and have crucial meaning for the exploitation and the SPACE APPLICATION that realize liquid pulse plasma thruster.
The model utility content
The purpose of the utility model is for a kind of liquid propellant injection device is provided, and solves the moment before liquid pulse plasma thruster discharge igniting, and liquid how to supply with μ g magnitude gets into the technical barrier of discharging chamber between pole plate.
The purpose of the utility model realizes through following technological scheme.
The utility model is a kind of propellant agent injection device that is used for the liquid pulse plasma thruster, comprises propellant agent bunker, link and ejector filler; Wherein the propellant agent bunker comprises air inlet nozzle 1, top cover 2, bottom 3, cylindrical shell 4, pressure gauge 5, piston 6, liquid entering hole 7, liquid port 8 and relief opening 9; Ejector filler comprises sleeve 12, shot chamber 13 and shower nozzle 14; Cylindrical shell 4 is a hollow cylinder, and top cover 2 is fixedly connected on the two ends of cylindrical shell 4 through screw thread respectively with bottom 3 and is sealed by seal ring; There is a boss at inner chamber centermost place at cylindrical shell 4, between boss and bottom 4, piston 6 is arranged, and is air chamber 10 between piston 6 and the top cover 2, is propellant chamber 11 between piston 6 and the bottom 3; Piston 6 can move between boss in the cylindrical shell 4 and bottom 4; Seal ring in piston 6 grooves is used to cut off air chamber 10 and propellant chamber 11; Outer wall near a side neck body 4 of bottom 3 is provided with liquid entering hole 7 and liquid port 8; Outer wall near a side neck body 4 of top cover 2 is provided with relief opening 9 and pressure gauge 5; The center of top cover 2 and bottom 3 has a through hole respectively; Air inlet nozzle 1 is fixedly connected with top cover 2; Gas enters into air chamber 10 through the through hole on air inlet nozzle 1 and the top cover 2; Pressure gauge 5 is used for the pressure in the measurement of gas body cavity 10; Propellant chamber 11 is used for the contain fluid propellant agent, and an end of link is fixedly connected with bottom 3, and liquid propellant can enter into link through the through hole on the bottom 3; Shot chamber 13 is a hollow cylinder, and an end of shot chamber 13 is fixedly connected with link, and the other end of shot chamber 13 is fixedly connected with shower nozzle 14; Sleeve 12 is enclosed within the end of shot chamber 13 near link; Liquid propellant enters into the inner chamber of shot chamber 13 via link, thereby sprays through shower nozzle 14; Sleeve 12 is used to protect link and shot chamber 13 is installed.
Working procedure: in propellant chamber 11, inject liquid propellant through liquid entering hole 7; After the fluid injection, liquid entering hole 7, liquid port 8 and relief opening 9 all are closed state; Gas is passed into gas in the air chamber 10 through air inlet nozzle 1, when pressure gauge 5 shows that pressure reaches setting value, stops air inlet; The free extrusion piston 6 of gas enters into the inner chamber of shot chamber 13 with the liquid propellant in the propellant chamber 11 by link, thereby sprays through shower nozzle 14.
Behind the end-of-job, the remaining liq propellant agent in the propellant chamber 11 is discharged through liquid port 8, the residual gas in the air chamber 10 is discharged through relief opening 9.
Above-mentioned liquid propellant is water or liquid hydrocarbon; Liquid hydrocarbon is ethanol or propyl alcohol;
Above-mentioned liquid propellant is 3-100 μ g/s from the speed of shower nozzle 14 ejections;
The pressure of above-mentioned air chamber 10 is 0.05-2MPa.
Beneficial effect
The device of the utility model, simple in structure, can be with the discharging chamber of Micro-volume liquid propellant feed liquid pulse plasma propeller, solved long, difficult control of micrometeor of traditional electrical magnet valve spray response time and the low problem of control accuracy.
Description of drawings
Fig. 1 is the structural representation of the utility model;
Wherein, 1-air inlet nozzle, 2-top cover 3-bottom, 4-cylindrical shell, 5-pressure gauge, 6-piston, 7-liquid entering hole, 8-liquid port, 9-relief opening, 10-air chamber, 11-propellant chamber, 12-sleeve, 13-shot chamber, 14-shower nozzle.
Embodiment
Below in conjunction with accompanying drawing the preferred embodiment of the utility model is done further explain.
Embodiment
A kind of propellant agent injection device that is used for the liquid pulse plasma thruster comprises propellant agent bunker, link and ejector filler; Wherein the propellant agent bunker comprises air inlet nozzle 1, top cover 2, bottom 3, cylindrical shell 4, pressure gauge 5, piston 6, liquid entering hole 7, liquid port 8 and relief opening 9; Ejector filler comprises sleeve 12, shot chamber 13 and shower nozzle 14; Cylindrical shell 4 is a hollow cylinder, and top cover 2 is fixedly connected on the two ends of cylindrical shell 4 through screw thread respectively with bottom 3 and is sealed by seal ring; There is a boss at inner chamber centermost place at cylindrical shell 4, between boss and bottom 4, piston 6 is arranged, and is air chamber 10 between piston 6 and the top cover 2, is propellant chamber 11 between piston 6 and the bottom 3; Piston 6 can move between boss in the cylindrical shell 4 and bottom 4; Seal ring in piston 6 grooves is used to cut off air chamber 10 and propellant chamber 11; Outer wall near a side neck body 4 of bottom 3 is provided with liquid entering hole 7 and liquid port 8; Outer wall near a side neck body 4 of top cover 2 is provided with relief opening 9 and pressure gauge 5; The center of top cover 2 and bottom 3 has a through hole respectively; Air inlet nozzle 1 is fixedly connected with top cover 2; Gas enters into air chamber 10 through the through hole on air inlet nozzle 1 and the top cover 2; Pressure gauge 5 is used for the pressure in the measurement of gas body cavity 10; Propellant chamber 11 is used for the contain fluid propellant agent, and link is the microfluid flexible pipe of peroxidating silica gel material; One end and the bottom 3 of link are adhesively fixed, and liquid propellant can enter into link through the through hole on the bottom 3; Shot chamber 13 is a hollow cylinder, and an end and the link of shot chamber 13 are adhesively fixed, and the other end of shot chamber 13 and shower nozzle 14 end faces are adhesively fixed; Sleeve 12 is enclosed within the end of shot chamber 13 near link; Liquid propellant enters into the inner chamber of shot chamber 13 via link, thereby sprays through shower nozzle 14; Sleeve 12 is used to protect link and shot chamber 13 is installed.
Working procedure: in propellant chamber 11, inject water through liquid entering hole 7; After the fluid injection, liquid entering hole 7, liquid port 8 and relief opening 9 all are closed state; Air is passed into air in the air chamber 10 through air inlet nozzle 1, when pressure gauge 5 shows that pressure reaches 2 * 10
5During Pa, stop air inlet; The free extrusion piston 6 of air enters into the inner chamber of shot chamber 13 with the water in the propellant chamber 11 by link, and water is 10 μ g/s ejections through shower nozzle 14 with flow.Said shower nozzle 14 places discharging chamber inner; In the discharge interim of liquid pulse plasma thruster; Can accurately supply with the proper amount of water propellant agent and get into discharging chamber, thereby make the liquid pulse plasma thruster accomplish serial processes such as discharge, ablation, acceleration, produce thrust.
Remaining water behind the end-of-job in propellant chamber 11 is discharged through liquid port 8, and the surplus air in the chamber 10 is discharged through relief opening 9.
The Rescor-902 porous ceramic film material that shower nozzle 14 adopts Cotronics Corp. to produce.
Claims (1)
1. a propellant agent injection device that is used for the liquid pulse plasma thruster is characterized in that: comprise propellant agent bunker, link and ejector filler; Wherein the propellant agent bunker comprises air inlet nozzle (1), top cover (2), bottom (3), cylindrical shell (4), pressure gauge (5), piston (6), liquid entering hole (7), liquid port (8) and relief opening (9); Ejector filler comprises sleeve (12), shot chamber (13) and shower nozzle (14); Cylindrical shell (4) is a hollow cylinder, and top cover (2) and bottom (3) are fixedly connected on the two ends of cylindrical shell (4) through screw thread respectively and are sealed by seal ring; There is a boss at inner chamber centermost place at cylindrical shell (4), and piston (6) is arranged between boss and bottom 4, is air chamber (10) between piston (6) and the top cover (2), is propellant chamber (11) between piston (6) and the bottom (3); Piston (6) can move between boss in the cylindrical shell (4) and bottom 4; Seal ring in piston (6) groove is used to cut off air chamber (10) and propellant chamber (11); Outer wall near a side neck body (4) of bottom (3) is provided with liquid entering hole (7) and liquid port (8); Outer wall near a side neck body (4) of top cover (2) is provided with relief opening (9) and pressure gauge (5); The center of top cover (2) and bottom (3) has a through hole respectively; Air inlet nozzle (1) is fixedly connected with top cover (2); Gas enters into air chamber (10) through the through hole on air inlet nozzle (1) and the top cover (2); One end of link is fixedly connected with bottom (3), and liquid propellant enters into link through the through hole on the bottom (3); Shot chamber (13) is a hollow cylinder, and an end of shot chamber (13) is fixedly connected with link, and the other end of shot chamber (13) is fixedly connected with shower nozzle (14); Sleeve (12) is enclosed within the end of shot chamber (13) near link; Liquid propellant enters into the inner chamber of shot chamber (13) via link, thereby sprays through shower nozzle (14).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011204617572U CN202360313U (en) | 2011-11-18 | 2011-11-18 | Propellant injection device for liquid pulse plasma thruster |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011204617572U CN202360313U (en) | 2011-11-18 | 2011-11-18 | Propellant injection device for liquid pulse plasma thruster |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202360313U true CN202360313U (en) | 2012-08-01 |
Family
ID=46571503
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011204617572U Withdrawn - After Issue CN202360313U (en) | 2011-11-18 | 2011-11-18 | Propellant injection device for liquid pulse plasma thruster |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202360313U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102400879A (en) * | 2011-11-18 | 2012-04-04 | 北京理工大学 | Propellant spraying device for liquid pulse plasma thruster |
| CN107587989A (en) * | 2017-10-17 | 2018-01-16 | 北京理工大学 | A kind of double state solid pulsed plasma thrusters of high efficiency |
| CN107795474A (en) * | 2017-11-29 | 2018-03-13 | 北京众驰伟业科技发展有限公司 | A kind of micro automatic injection pump |
-
2011
- 2011-11-18 CN CN2011204617572U patent/CN202360313U/en not_active Withdrawn - After Issue
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102400879A (en) * | 2011-11-18 | 2012-04-04 | 北京理工大学 | Propellant spraying device for liquid pulse plasma thruster |
| CN102400879B (en) * | 2011-11-18 | 2013-07-03 | 北京理工大学 | Propellant spraying device for liquid pulse plasma thruster |
| CN107587989A (en) * | 2017-10-17 | 2018-01-16 | 北京理工大学 | A kind of double state solid pulsed plasma thrusters of high efficiency |
| CN107587989B (en) * | 2017-10-17 | 2019-01-25 | 北京理工大学 | A kind of double state solid pulsed plasma thrusters of high efficiency |
| CN107795474A (en) * | 2017-11-29 | 2018-03-13 | 北京众驰伟业科技发展有限公司 | A kind of micro automatic injection pump |
| CN107795474B (en) * | 2017-11-29 | 2024-03-08 | 北京众驰伟业科技发展有限公司 | Micro automatic injection pump |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20120801 Effective date of abandoning: 20130710 |
|
| RGAV | Abandon patent right to avoid regrant |