CN108301997A - Pulsed plasma thruster based on Z-PINCH no-spark plugs - Google Patents
Pulsed plasma thruster based on Z-PINCH no-spark plugs Download PDFInfo
- Publication number
- CN108301997A CN108301997A CN201810066946.6A CN201810066946A CN108301997A CN 108301997 A CN108301997 A CN 108301997A CN 201810066946 A CN201810066946 A CN 201810066946A CN 108301997 A CN108301997 A CN 108301997A
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- Prior art keywords
- propellant
- pulsed plasma
- plasma thruster
- solid propellant
- anode
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- 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.)
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H1/00—Using plasma to produce a reactive propulsive thrust
- F03H1/0087—Electro-dynamic thrusters, e.g. pulsed plasma thrusters
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H1/00—Using plasma to produce a reactive propulsive thrust
- F03H1/0006—Details applicable to different types of plasma thrusters
- F03H1/0018—Arrangements or adaptations of power supply systems
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Plasma Technology (AREA)
Abstract
A kind of pulsed plasma thruster based on Z PINCH no-spark plugs includes the anode of the cathode of the tray type structure that is set in turn between pedestal and outer insulator, solid propellant and pyramidal structure, wherein：Cathode and anode are respectively arranged at the both ends of solid propellant, and outer insulator is placed on the outside of solid propellant and is connected with pedestal.The present invention is not necessarily to spark plug auxiliary firing, realizes propellant fire and electric discharge integration, reduces ignition voltage；Propellant feed is carried out without spring, it is simple in structure without any movable part；Unique structure design can effectively improve the utilization ratio of propellant, push away work(and compare higher；Size is not particularly limited.
Description
Technical field
The present invention relates to a kind of technology of space electric propulsion technology and electric thruster design field, specifically a kind of bases
In the pulsed plasma thruster of Z-PINCH no-spark plugs.
Background technology
Pulsed plasma thruster is to utilize pulsed discharge, and ablation, decomposition, ionization propellant make plasma
Body.Traditional pulse plasma thruster generally use solid polytetrailuoroethylene is supplied as propellant combination spring, also there is
Person has studied gas and liquid propellant.From structure, traditional pulse plasma thruster combines for parallel-plate electrode
Spark plug realizes igniting and generates pulsed arc, also it is proposed that coaxial pulse plasma thruster, but lights a fire and generates
The principle of thrust is that plasma is accelerated under discharge current collective effect by the effect of Generalized Lorentz's Force in magnetic field
It sprays and generates thrust.When Conventional parallel plate electrode pulsed plasma thruster works, energy-storage capacitor is charged into institute first
Voltage is needed, then semiconductor spark plug is lighted a fire, and capacitor discharges along working medium ptfe surface, and electric current is formed in working medium table
Face, hot-fluid is by molecule depolymerization, division, the ionization of ptfe surface, subsequent being total in Generalized Lorentz's Force and Pneumatic pressure
Under same-action, plasma is accelerated, and expansion, which sprays, generates thrust.After capacitor discharge, thruster be stopped or into
Enter next cycle.Due to the hysteresis quality of heat transfer, it is gas but nothing still to have part propellant distillation after electric discharge every time
Method ionizes, and causes propellant utilization ratio very low.
Invention content
The present invention relies on spark plug for existing pulsed plasma thruster causes the more volume of structure member excessive
Increase security risk simultaneously, and the defects such as propellant utilization ratio is low, proposes a kind of pulse etc. based on Z-PINCH no-spark plugs
Gas ions thruster is not necessarily to spark plug auxiliary firing, realizes propellant fire and electric discharge integration, reduces ignition voltage；
Propellant feed is carried out without spring, it is simple in structure without any movable part；Unique structure design can be effectively improved and be pushed away
Into the utilization ratio of agent, pushes away work(and compare higher；Size is not particularly limited.
The present invention is achieved by the following technical solutions：
The present invention include the cathode of the tray type structure being set in turn between pedestal and outer insulator, solid propellant and
The anode of pyramidal structure, wherein：Cathode and anode are respectively arranged at the both ends of solid propellant, and outer insulator is placed on solid
The outside of propellant is simultaneously connected with pedestal.
The cathode is preferably metal disc structure made of copper, and the circle that top is equipped with for connecting external circuit is small
Hole.
The anode is preferably metal conical structure made of copper, and the circle that bottom is equipped with for connecting external circuit is small
Hole.
The solid propellant is preferably cylindrical cavity structure, and further preferably infiltration has the polytetrafluoro of conductive material
Ethylene is made.
The pedestal and outer insulator is preferably that makrolon is made.
Technique effect
Compared with prior art, the present invention charges to given voltage to thruster negative and positive the two poles of the earth, in propellant surface, cylinder
Shape current sheet quickly forms, ablation polytetrafluoroethylene (PTFE), radially accelerated ablation resultant, and electric current starts to flow between two electrodes.
Initial current is distributed in insulator surface, forms cylindrical current piece.Current sheet is formed at the maximum radius of chamber, this is because
The position loop impedance is minimum.With the increase of electric current, magnetic field is generated in the outside of current sheet.Magnetic field and current sheet phase interaction
With the inside radial electromagnetic force of generation.This power causes current sheet to disintegrate to chamber center, but current sheet be not completely with
Cylinder is moved to center, but produces inclination, which is referred to as slide fastener effect.Under the action of current sheet, propellant
Initially it is accelerated radially；When current sheet is shunk completely, the presence of aperture can lead to larger axial pressure gradient.Therefore, etc.
Gas ions can axially accelerate to spray.Plasma is squeezed under the action of radial load and is expanded, and expands in an axial direction
It dissipates.
Description of the drawings
Fig. 1, Fig. 2 are the overall structure diagram of the present invention；
Fig. 3 is heretofore described outer insulator schematic diagram；
Fig. 4 is heretofore described cathode schematic diagram；
Fig. 5 is heretofore described propulsion chamber schematic diagram；
Fig. 6 is heretofore described anode schematic diagram；
Fig. 7 is heretofore described pedestal schematic diagram；
Fig. 8 and Fig. 9 is embodiment effect diagram；
In figure：1 outer insulator, 2 cathodes, 3 solid propellants, 4 anodes, 5 pedestals.
Specific implementation mode
As depicted in figs. 1 and 2, be novel pulse based on Z-PINCH principle no-spark plugs for being related to of the present embodiment etc. from
Daughter propulsion device, including：Outer insulator 1, cathode 2, solid propellant 3,4 and of anode being connected successively from top to bottom
Pedestal 5, wherein：2 top circular aperture of cathode is for connecting external circuit.The 4 bottom circular aperture of anode is for connecting
External circuit.
As shown in Fig. 3,7, the outer insulator 1 and pedestal 6 are made of makrolon, and makrolon has resistance
Combustion, wear-resisting and inoxidizability.
As shown in Fig. 4,6, the cathode 2 and anode 4 are made of metallic copper, and copper has good electric conductivity, and resistance to height
Temperature, fusing point are high.There is aperture among cathode 2, the plasma generated after solid propellant 3 is ablated is sprayed from hole.On anode 4
Portion is cone, when current sheet is formed, convenient for generating radial load.
As shown in figure 5, the solid propellant 3 is made of polytetrafluoroethylene (PTFE), polytetrafluoroethylene (PTFE) infiltration is specifically led
Electric material.Polytetrafluoroethylene (PTFE) has high temperature resistant, corrosion-resistant and insulation characteristic, and plasma is generated after ablation.Using cylinder
Arc chamber is under the conditions of intended size, can utmostly utilize space storage propellant.
The present embodiment is the work is performed in the following manner：Hollow cylindrical polytetrafluoroethylene (PTFE) is placed between positive and negative electrode.
Propellant surface, cylindrical current piece quickly form, ablation polytetrafluoroethylene (PTFE), radially accelerated ablation resultant, and electric current starts two
It is flowed between a electrode.Initial current is distributed in insulator surface, forms cylindrical current piece.Maximum radius of the current sheet in chamber
Place is formed, this is because the position loop impedance is minimum.With the increase of electric current, magnetic field is generated in the outside of current sheet.Magnetic field
It interacts with current sheet, generates inwardly radial electromagnetic force.This power causes current sheet to disintegrate to chamber center, but electric current
Piece is not to be moved completely to center with cylinder, but produce inclination, which is referred to as slide fastener effect.In current sheet
Under effect, propellant is initially accelerated radially；When current sheet is shunk completely, the presence of aperture can lead to larger axial compressive force
Gradient.Therefore, plasma can axially accelerate to spray.Plasma is squeezed under the action of radial load and occurs swollen
It is swollen, it spreads in an axial direction.
According to the thruster described in the invention, devises experimental program and verify its performance, be as follows：
Thruster is fixed on the thrust-measuring device in vacuum chamber by step 1), adjusts the position of motion platform in cabin,
In order to be monitored to thruster working condition by the observation window on bulkhead；
Step 2) carries out debugging and static demarcating to thrust-measuring device；
Step 3) positions thrust-measuring device electricity, is evacuated to the vacuum degree of requirement；
Step 4) releases the positioning of thrust-measuring device electricity, the indicating value for showing power window on measurement and control instrument is observed, after basicly stable
Preparing experiment；
Step 5) opens thruster power-supply system (including main capacitor charge power supply and ignition system power supply), opens simultaneously
Data collecting system power supply records the zero of current thrust-measuring device；
Step 6) thruster igniting experiments, data collecting system record thrust measurement data.
After the negative and positive two-stage to thruster adds voltage, as shown in figure 8, thruster is just started to work.
As shown in figure 9, for the flash-over characteristic of a pulse during thruster steady operation, can be seen according to U-I curves
Go out, voltage is 20V, ignition voltage 480V when initial.The charging process duration is 1ms, and electric current increases at this time, and maximum value is
24A, subsequent electric current slowly decline.The entire discharge process duration is 1.04ms.It can be calculated from figure, this is novel to push away
The operation power of power device is 4.8W.
The experimental results showed that the thruster can work, design requirement is tentatively reached.It is 17.83 μ N/W to push away work(ratio, than
Traditional pulse plasma thruster pushes away work(than big.Above-mentioned specific implementation can be by those skilled in the art without departing substantially from this hair
Local directed complete set is carried out to it in different ways under the premise of bright principle and objective, protection scope of the present invention is with claims
Subject to and do not limited by above-mentioned specific implementation, each implementation within its scope is by the constraint of the present invention.
Claims (6)
1. a kind of pulsed plasma thruster based on Z-PINCH no-spark plugs, which is characterized in that including being set in turn in base
The cathode of tray type structure between seat and outer insulator, the anode of solid propellant and pyramidal structure, wherein：Cathode and anode
The both ends of solid propellant are respectively arranged at, outer insulator is placed on the outside of solid propellant and is connected with pedestal.
2. pulsed plasma thruster according to claim 1, characterized in that the cathode is metal circle made of copper
Dish structure, top are equipped with the circular aperture for connecting external circuit.
3. pulsed plasma thruster according to claim 1, characterized in that the anode is metal circle made of copper
Wimble structure, bottom are equipped with the circular aperture for connecting external circuit.
4. pulsed plasma thruster according to claim 1, characterized in that the solid propellant is cylindrical cavity
Body structure.
5. pulsed plasma thruster according to claim 4, characterized in that the solid propellant, which is infiltration, to be had
The polytetrafluoroethylene (PTFE) of conductive material is made.
6. pulsed plasma thruster according to claim 1, characterized in that the pedestal and outer insulator be
Makrolon is made.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810066946.6A CN108301997A (en) | 2018-01-24 | 2018-01-24 | Pulsed plasma thruster based on Z-PINCH no-spark plugs |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810066946.6A CN108301997A (en) | 2018-01-24 | 2018-01-24 | Pulsed plasma thruster based on Z-PINCH no-spark plugs |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108301997A true CN108301997A (en) | 2018-07-20 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810066946.6A Pending CN108301997A (en) | 2018-01-24 | 2018-01-24 | Pulsed plasma thruster based on Z-PINCH no-spark plugs |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109000011A (en) * | 2018-08-14 | 2018-12-14 | 上海交通大学 | For being cold-started the pin type isolating valve of high-pressure mini gas |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4821509A (en) * | 1985-06-10 | 1989-04-18 | Gt-Devices | Pulsed electrothermal thruster |
| EP1185833B1 (en) * | 2000-04-11 | 2005-07-20 | Giat Industries | Plasma torch incorporating a reactive priming fuse and igniter tube integrating such a torch |
| US7530219B1 (en) * | 2002-06-14 | 2009-05-12 | Cu Aerospace, Llc | Advanced pulsed plasma thruster with high electromagnetic thrust |
| CN107091210A (en) * | 2017-05-18 | 2017-08-25 | 西安交通大学 | A kind of pulsed plasma thruster based on capillary discharging |
-
2018
- 2018-01-24 CN CN201810066946.6A patent/CN108301997A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4821509A (en) * | 1985-06-10 | 1989-04-18 | Gt-Devices | Pulsed electrothermal thruster |
| EP1185833B1 (en) * | 2000-04-11 | 2005-07-20 | Giat Industries | Plasma torch incorporating a reactive priming fuse and igniter tube integrating such a torch |
| US7530219B1 (en) * | 2002-06-14 | 2009-05-12 | Cu Aerospace, Llc | Advanced pulsed plasma thruster with high electromagnetic thrust |
| US7926257B1 (en) * | 2002-06-14 | 2011-04-19 | Cu Aerospace, Llc | Advanced pulsed plasma thruster with high electromagnetic thrust |
| CN107091210A (en) * | 2017-05-18 | 2017-08-25 | 西安交通大学 | A kind of pulsed plasma thruster based on capillary discharging |
Non-Patent Citations (2)
| Title |
|---|
| THOMAS E. MARKUSIC: "Ablative Z-Pinch Pulsed Plasma Thruster", 《JOURNAL OF PROPULSION Z-PINCH PULSED THRUSTER》 * |
| 杨乐: "脉冲等离子体推力器工作过程理论和实验研究", 《中国博士学位论文全文数据库（电子期刊）》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109000011A (en) * | 2018-08-14 | 2018-12-14 | 上海交通大学 | For being cold-started the pin type isolating valve of high-pressure mini gas |
| CN109000011B (en) * | 2018-08-14 | 2019-08-02 | 上海交通大学 | For being cold-started the pin type isolating valve of high-pressure mini gas |
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Application publication date: 20180720 |
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