CN102374146A - Pulse laser plasma electricity hybrid micro-propulsion unit and method - Google Patents
Pulse laser plasma electricity hybrid micro-propulsion unit and method Download PDFInfo
- Publication number
- CN102374146A CN102374146A CN2010102491777A CN201010249177A CN102374146A CN 102374146 A CN102374146 A CN 102374146A CN 2010102491777 A CN2010102491777 A CN 2010102491777A CN 201010249177 A CN201010249177 A CN 201010249177A CN 102374146 A CN102374146 A CN 102374146A
- Authority
- CN
- China
- Prior art keywords
- plasma
- propellant
- pulse laser
- pulse
- produces
- 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.)
- Granted
Links
Images
Landscapes
- Plasma Technology (AREA)
Abstract
The invention discloses a plasma laser plasma electricity hybrid micro-propulsion unit which comprises a pulse laser ablation device, a propellant supply device and a plasma accelerating device, wherein the pulse laser ablation device irradiates a propellant supplied by the propellant supply device to generate high-speed plasma; and the plasma accelerating device is used for accelerating the high-speed plasma again. The invention also provides a pulse laser plasma electricity hybrid micro-propulsion method which comprises the following steps of: generating high-temperature and high-speed plasma through the high-frequency pulse laser ablation propellant; and accelerating the high-temperature and high-speed plasma through an electric field or magnetic field. According to the invention, a pushing force with high specific impulse and high thrust-to-power ratio can be provided for a mini satellite.
Description
Technical field
The present invention relates to the plasma propulsion field, particularly a kind of pulse laser plasma electrically mixing micro propulsion device and method.
Background technique
The developing rapidly of microsatellite makes that research is efficient, light-duty, little Push Technology of low power consumption, low thrust, little momentum becomes necessary.At present, little Push Technology pulsed plasma of main research advances (PPT), Hall to advance propulsion modes such as (SPT) that pluses and minuses are respectively arranged.At present, PPT propulsion mode degree of ionization is low, and most of particle can't directly receive electromagnetic field and quicken, and propulsive efficiency is very low, and all less than 10%, it is higher than not to push away merit.And the propellant agent that Hall advances (SPT) to adopt is generally xenon, has higher specific impulse and the high merit ratio that pushes away; Shortcoming is that the steel cylinder of storage gas has accounted for a greater part of of system's dry weight, causes quality and volume bigger, complex structure, and the useful load rate is low, also receives cathode emission device age limit simultaneously, is difficult on microsatellite, use.
Summary of the invention
One of the object of the invention provides a kind of pulse laser plasma electrically mixing micro propulsion device and method that the microthrust that high specific impulse, height push away the merit ratio is provided.
According to an aspect of the present invention, a kind of pulse laser plasma electrically mixing micro propulsion device is provided, comprises: pulse laser ablation device, propellant supply equipment and plasma accelerating unit; The said pulse laser ablation device propellant agent that said propellant supply equipment provides of ablating produces the high speed plasma; Said plasma accelerating unit quickens said high speed plasma.
According to an aspect of the present invention, provide a kind of pulse laser plasma electrically to mix little propulsion method, comprising:, produce high temperature, high speed plasma through high-frequency impulse laser ablation propellant agent; And
Through electric field or magnetic field said high temperature, high speed plasma are quickened.
According to pulse laser plasma electrically mixing micro propulsion device provided by the invention and method, can be microsatellite high specific impulse and the high micro thrust that pushes away the merit ratio are provided.
Description of drawings
Fig. 1 is the structural representation of the pulse laser plasma electrically mixing micro propulsion device that provides of the embodiment of the invention;
Fig. 2 is the structural representation of the pulse laser plasma electrically mixing micro propulsion device that provides of another embodiment of the present invention;
Fig. 3 is the structural representation of the pulse laser plasma electrically mixing micro propulsion device that provides of another embodiment of the present invention;
Fig. 4 is the structural representation of the pulse laser plasma electrically mixing micro propulsion device that provides of another embodiment of the present invention;
Fig. 5 is the schematic representation that the electronics in Fig. 4 ionic medium body group is bound in the closed loop drift motion of making hoop in the acceleration channel
Fig. 6 is the schematic flow sheet that pulse laser plasma electrically that the embodiment of the invention provides mixes little propulsion method.
The object of the invention, function and advantage will combine embodiment, further specify with reference to accompanying drawing.
Embodiment
The embodiment of the invention provides a kind of pulse laser plasma electrically mixing micro propulsion device, comprising: pulse laser ablation device, propellant supply equipment and plasma accelerating unit; The propellant agent that pulse laser ablation device ablation propellant supply equipment provides produces the high speed plasma; The plasma accelerating unit quickens the high speed plasma.This pulse laser plasma electrically mixing micro propulsion device is launched explanation below in conjunction with Fig. 1 in detail to embodiment shown in Figure 4.
As shown in Figure 1, the pulse laser plasma electrically mixing micro propulsion device that the embodiment of the invention provides comprises: control logic circuit, pulse laser ablation device, place propellant agent 1, the energy-storage capacitor 6 between anode 4 and the negative electrode 5 and be used for low-voltage DC supply is converted into the power supply change-over device 7 of high voltage direct current.Wherein, the pulse laser ablation device comprises pulse optical fiber 2 and focus lamp 10, and pulse optical fiber is connected with focus lamp 10 through optical fiber.Control logic circuit produces and is used for the control signal that control impuls optical fibre laser 2 produces pulse signal.Pulse optical fiber 2 receives control signal, produces corresponding high-frequency impulse laser according to control signal.Anode 4 constitutes discharge channel with negative electrode 5.High-frequency impulse laser is radiated on the propellant agent 1 through the spout that focus lamp 10, anode 4 have successively.High-frequency impulse laser focuses on propellant agent 1 surface it is ablated and abundant plasmaization, thereby between anode 4 and negative electrode 5, produces plasma slab.Power supply change-over device 7 is connected with energy-storage capacitor 6, receives the high voltage direct current that power supply change-over device 7 produces.Energy-storage capacitor 6 constitutes the closed-loop path with anode 4, negative electrode 5 and plasma slab, and produces induction field.The high-temperature plasma that laser ablation irradiates has very high speed, receives in induction field that Lorentz force quickens once more and outwards ejection, produces a thrust pulse.Propellant agent can be solid propellant (for example, polymer, double-base powder etc.), outside it constant force spring can be set, and produces a constant force and acts on the solid propellant, guarantees that propellant agent can be sent to the laser focal spot that is positioned under the spout under the required speed.
Another kind of pulse laser plasma electrically mixing micro propulsion device as shown in Figure 2, that the embodiment of the invention provides.With embodiment illustrated in fig. 1 different be that this embodiment adopts liquid, gas or lotion as propellant agent.Liquid, gas or lotion (liquid such as hydrazine, gas such as xenon, lotion such as polyamines polyene etc.) are stored in the storage bottle 13.Storage bottle 13 is delivered to liquid, gas or lotion in the discharge channel of being made up of anode 4 and negative electrode 5 through a pipeline 12 (pipeline is provided with valve 11).During work, valve 11 is opened a period of time, and liquid, gas or lotion are by the flow ejection of setting.When liquid, gas or lotion arrived pipeline 12 oral areas, pulse optical fiber 2 produced corresponding laser pulse according to control signal (being produced by control logic circuit).Laser pulse focuses on through the propellant surface of 10 pairs of pipeline 12 oral areas of focus lamp, and propellant agent is ablated and abundant plasmaization.Become plasma slab between anode 4 and the negative electrode 5.Energy-storage capacitor 6, anode 4, negative electrode 5 and plasma slab constitute the closed-loop path, and produce induction field.Itself just has very high speed the high-temperature plasma that laser ablation ejects, and receives in induction field that Lorentz force quickens once more and outwards ejection, produces a thrust pulse.
Another kind of pulse laser plasma electrically mixing micro propulsion device as shown in Figure 3, that the embodiment of the invention provides.With embodiment illustrated in fig. 2 different be that the storage bottle 13 that is used to store gas, lotion or liquid propellant is pushed to transparent substrates layer 14 (the transparent substrates layer is arranged between the discharge channel that anode 4 and negative electrode 5 constitute) through a pipeline 12 (pipeline is provided with valve 11) with the propellant agent of storage.During work, valve 11 is opened a period of time, and gas, lotion or liquid propellant flow out by the flow of setting, and gas/liquid arrives and forms one deck liquid or gas membrane near the transparent substrates layer the pipeline oral area.This moment, pulse optical fiber 2 produced corresponding laser pulse according to control signal (being produced by control logic circuit); Laser sees through transparent substrates layer 14 and is focusing on gas, lotion or the fluid film near pipeline 12 oral areas, and gas, lotion or liquid propellant are ablated and abundant plasmaization.5 on anode 4 and negative electrode become plasma slab.Energy-storage capacitor 6, anode 4, negative electrode 5 and plasma slab constitute the closed-loop path, and produce induction field.Itself just has very high speed the high-temperature plasma that laser ablation ejects, and receives in induction field that Lorentz force quickens once more and outwards ejection, produces a thrust pulse.
As shown in Figure 4, the another kind of pulse laser plasma electrically mixing micro propulsion device that the embodiment of the invention provides comprises: power-supply system, control logic circuit, pulse laser ablation device, place electromagnetic field acceleration channel and anode 4 between solid propellant 1 (can add spring and give thrust), field coil 15, the N utmost point 17 and the S utmost point 16 between the N utmost point 17 and the S utmost point 16.Wherein, the pulse laser ablation device comprises pulse optical fiber 2 and focus lamp 10.Pulse optical fiber 2 is connected with focus lamp 10 through optical fiber 3.Control logic circuit produces and is used for the control signal that control impuls optical fibre laser 22 produces pulse signal.Pulse optical fiber 22 receives control signal, produces corresponding high-frequency impulse laser according to control signal.The working procedure of above device is following: laser incident in the S utmost point 16 slits, near propellant surface, focus on, and propellant agent is ablated, thereby produce high temperature, plasma at a high speed.High temperature, plasma jet at a high speed get into the electromagnetic field acceleration channel.In acceleration channel, owing to the constraint effect of radial magnetic field to electronics, the axial motion of the electronics in the plasmoid receives the inhibition in magnetic field, is bound in the closed loop drift motion (as shown in Figure 5) of making hoop in the acceleration channel; The electronics of toroidal drift and anode 4 between form electric field.On the other hand; Because the quality of ion is far longer than the quality of electronics; So the magnetic field in the acceleration channel effectively fetters electronical line shaft almost not influence of motion to axial ion in the time of motion; The ion that ionization produces obtains quickening under the effect of acceleration channel internal electric field and outwards ejection once more, produces thrust.Certainly the propellant agent 1 in the present embodiment also can adopt gas, liquid or lotion.When propellant agent 1 is gas, liquid or lotion, can adopt the storage bottle of storage gas or liquid propellant, the storage bottle is pushed to the propellant agent of storage under the slit through a pipeline or is pushed on the transparent substrates layer.
As shown in Figure 6, the embodiment of the invention also provides a kind of pulse laser plasma electrically to mix little propulsion method, comprising:
Step S1, through high-frequency impulse laser ablation propellant agent, produce high temperature, high speed plasma; And
Step S2, said high temperature, high speed plasma are quickened once more through electric field or magnetic field.
This method can be implemented to pulse laser plasma electrically mixing micro propulsion device shown in Figure 4 through Fig. 1, repeats no more here.
Below in conjunction with specific impulse with push away the usefulness that merit is recently explained the pulse laser plasma electrically mixing micro-thruster that the embodiment of the invention provides.Specific impulse be defined as I
Sp=v/g (1), wherein, the jet velocity of the plasma that v produces for ablating, visible by following formula (1), jet velocity is high more, and specific impulse is just high more.Specific impulse is high more, and the quality that produces the propellant agent that identical momentum consumes is just low more, and satellite is also just long more in the propellant agent that the carries equal in quality time in orbit.In general; Specific impulse height is relevant with the temperature of ablated plasma air mass, and the gas blowing temperature of general chemical rocket is at several thousand K, and laser is at several ten thousand K; And general PPT or Hall adopt the temperature of the plasma of electrion also to have only K up to ten thousand when advancing; Well below laser ablation,, just can obtain the specific impulse of 500-1000s so directly adopt laser as the plasma generation source.So the present invention adopts high-frequency impulse laser ablation propellant agent, produce the high speed plasma.Because the jet velocity of the plasma that produces is very high, specific impulse is also very high so, thereby the quality that produces the propellant agent that identical momentum consumes is just very low, and satellite is also just very long in the propellant agent that the carries equal in quality time in orbit.In addition; The speed of high speed plasma is quickened and can also be further improved at electromagnetic field; Thereby specific impulse is further enhanced; The quality that produces the propellant agent that identical momentum consumed is further reduced, and satellite further obtained prolonging in the propellant agent that the carries equal in quality time in orbit.
The definition that pushes away the merit ratio is as follows, that is: C
m=F/P; Wherein, the thrust of F for producing, P is an input electric power, and is visible, under the same electrical power, C
mBe worth greatly more, thrust F is just big more.Have only the microsatellite about 100kg for weight, can only produce the electric power of 100w, if it is lower than more to push away merit, the thrust of generation is just more little, can not accomplish the tasks higher to rate request such as satellite orbit maintenance and quick posture adjustment.
The parameter that table 1 has provided the present invention and traditional propeller compares.
The various propulsion device parameters of table 1 relatively
The data of table 1 show, the pulse laser plasma electrically mixing micro propulsion device that adopts the embodiment of the invention to provide obtains specific impulse and pushes away merit than all is superior to greatly existing P PT propelling, Hall propelling and simple laser ablation and advances.
The pulse laser plasma electrically mixing micro propulsion device and the method that provide according to the embodiment of the invention; Utilize high-frequency impulse laser that propellant agent is ablated; The high temperature, the high speed plasma that produce quicken in electric field or magnetic field once more, thereby obtain higher specific impulse.The high-frequency impulse laser that the present invention adopts, it is higher that it can reach specific power, can make propellant agent plasmaization more fully, thereby can produce higher specific impulse.The present invention adopts solid-state working medium as propellant agent, and stable performance, easy storage, safe and reliable have alleviated structure weight greatly.The present invention adopts the propellant agent scope wide, can use various metals, nonmetal working medium and contain ability working medium; The plasma temperature of laser ablation product is high simultaneously, and degree of ionization is higher, obtains more easily in the electric field quickening, and can realize higher specific impulse and push away the merit ratio.Advantages such as pulse laser plasma electrically mixing micro propulsion device provided by the invention is simple in structure, control is flexible can better satisfy the complex tasks such as attitude control, track maintenance, formation flight of microsatellite.
The research of Push Technology and the development of using following space technology are significant; For at orbit aerocraft, due to its life-span, propellant agent exhausted fully often, for long lifetime, big capacity commercial satellite; In light weight, powerful microsatellite; And survey of deep space and astronavigation astrovehicle, the present invention is through the application of twice acceleration, the working life that can improve propellant agent greatly.
The foregoing description is a preferred implementation of the present invention; But mode of execution of the present invention is not restricted to the described embodiments; Other any do not deviate from change, the modification done under spirit of the present invention and the principle, substitutes, combination, simplify; All should be the substitute mode of equivalence, be included within protection scope of the present invention.
Claims (11)
1. a pulse laser plasma electrically mixing micro propulsion device is characterized in that, comprising:
Pulse laser ablation device, propellant supply equipment and plasma accelerating unit;
The said pulse laser ablation device propellant agent that said propellant supply equipment provides of ablating produces the high speed plasma; Said plasma accelerating unit quickens said high speed plasma once more.
2. pulse laser plasma electrically mixing micro propulsion device according to claim 1 is characterized in that said plasma accelerating unit comprises:
By the discharge channel that anode and negative electrode are formed, energy-storage capacitor, be used for low-voltage DC supply is converted into the power supply change-over device of HVDC; Said propellant agent places said discharge channel; The spout that the high-frequency impulse laser that said pulse laser ablation device produces has through said anode is radiated on the said propellant agent or through the transparent substrates layer that is arranged between anode and the negative electrode and is radiated on the said propellant agent, thereby between said anode and said negative electrode, produces plasma slab; Said power supply change-over device is connected with said energy-storage capacitor, receives the high voltage direct current that said power supply change-over device produces; Said energy-storage capacitor and said discharge channel and said plasma slab constitute the closed-loop path.
3. pulse laser plasma electrically mixing micro propulsion device according to claim 2 is characterized in that said propellant supply equipment comprises:
Solid propellant and spring, said spring is connected with said solid propellant, is used for said solid propellant is pushed to the laser focal spot that is positioned under the said spout.
4. pulse laser plasma electrically mixing micro propulsion device according to claim 2 is characterized in that said propellant supply equipment comprises:
Be used to store the storage bottle of gas, lotion or liquid propellant, said storage bottle is pushed to gas, lotion or the liquid propellant stored under the said spout through a pipeline or is pushed on the said transparent substrates layer.
5. pulse laser plasma electrically mixing micro propulsion device according to claim 1 is characterized in that said plasma accelerating unit comprises:
Electromagnetic field acceleration channel and anode between magnetic pole, field coil, the magnetic pole; Said propellant agent places said electromagnetic field acceleration channel; The slit that the high-frequency impulse laser that said pulse laser ablation device produces has through magnetic pole is radiated on the said propellant agent, thereby between said magnetic pole, produces the high speed plasma; Electronics in the said high speed plasma and said anode constitute electric field.
6. pulse laser plasma electrically mixing micro propulsion device according to claim 5 is characterized in that said propellant supply equipment comprises:
Solid propellant and spring, said spring is connected with said solid propellant, is used for said solid propellant is pushed to the laser focal spot that is positioned under the said slit.
7. pulse laser plasma electrically mixing micro propulsion device according to claim 5 is characterized in that said propellant supply equipment comprises:
Be used to store the storage bottle of gas, lotion or liquid propellant, said storage bottle is pushed directly to laser focal spot that is positioned under the said slit or the laser focal spot that is pushed to said transparent substrates laminar surface through a pipeline with the propellant agent of storing.
8. according to each described pulse laser plasma electrically mixing micro propulsion device of claim 1 to 7, it is characterized in that said pulse laser ablation device comprises:
Pulse optical fiber and focus lamp, the laser that said pulse optical fiber produces shines on the said propellant agent through said focus lamp.
9. according to each described pulse laser plasma electrically mixing micro propulsion device of claim 1 to 7, it is characterized in that:
Also comprise control logic circuit, produce the working signal that is used to control said pulse laser ablation device generation pulse signal.
10. a pulse laser plasma electrically mixes little propulsion method, it is characterized in that, comprising:
Through high-frequency impulse laser ablation propellant agent, produce high temperature, high speed plasma; And
Through electric field or magnetic field said high temperature, high speed plasma are quickened once more.
11. method according to claim 10 is characterized in that:
Said propellant agent comprises solid, gas, liquid or lotion.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010249177 CN102374146B (en) | 2010-08-09 | 2010-08-09 | Pulse laser plasma electricity hybrid micro-propulsion unit and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010249177 CN102374146B (en) | 2010-08-09 | 2010-08-09 | Pulse laser plasma electricity hybrid micro-propulsion unit and method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102374146A true CN102374146A (en) | 2012-03-14 |
| CN102374146B CN102374146B (en) | 2013-04-03 |
Family
ID=45793220
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201010249177 Active CN102374146B (en) | 2010-08-09 | 2010-08-09 | Pulse laser plasma electricity hybrid micro-propulsion unit and method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102374146B (en) |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103073370A (en) * | 2012-12-28 | 2013-05-01 | 中国科学技术大学 | Nitrine type high-molecular sensitized high-energy ablator, preparation method thereof and target belt made from ablator |
| CN103423116A (en) * | 2013-07-26 | 2013-12-04 | 西北工业大学 | Liquid working media laser plasma micro propulsion and target supply device |
| CN103912466A (en) * | 2014-04-10 | 2014-07-09 | 王文东 | Electric hydrodynamic force propeller |
| CN104349569A (en) * | 2014-10-30 | 2015-02-11 | 北京大学 | Plasma lens-based laser ion accelerating system and accelerating method thereof |
| CN105781920A (en) * | 2016-04-28 | 2016-07-20 | 中国人民解放军国防科学技术大学 | Magnetic plasma thrustor supported through lasers |
| CN105952603A (en) * | 2016-04-28 | 2016-09-21 | 中国人民解放军国防科学技术大学 | Laser ablation pulsed plasma thruster |
| CN105966641A (en) * | 2016-05-31 | 2016-09-28 | 南昌理工学院 | Throwing beam rocket propulsion system |
| CN107416759A (en) * | 2017-03-21 | 2017-12-01 | 东南大学 | A kind of nanojet microdriver, its preparation method and its application |
| CN107725298A (en) * | 2017-09-30 | 2018-02-23 | 北华航天工业学院 | Optical-fiber laser self-propelled universe bareboat propulsion system |
| CN108275288A (en) * | 2017-12-19 | 2018-07-13 | 上海空间推进研究所 | Nontoxic double mode micromass culture system and its working method |
| CN108869220A (en) * | 2018-06-07 | 2018-11-23 | 西安空间无线电技术研究所 | A kind of propulsion device and propulsion method for Spatial kinematics |
| CN111076937A (en) * | 2019-12-09 | 2020-04-28 | 北京理工大学 | System and method for testing ablation quality of energetic working medium pulse plasma thruster |
| CN112555114A (en) * | 2020-12-01 | 2021-03-26 | 中国人民解放军战略支援部队航天工程大学 | Electromagnetic combined vector accelerating spray pipe for laser ablation propulsion |
| CN112943571A (en) * | 2021-03-08 | 2021-06-11 | 中国科学院合肥物质科学研究院 | High specific impulse and high power space propeller based on compact ring plasma |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6373023B1 (en) * | 1999-03-02 | 2002-04-16 | General Dynamics (Ots) Aerospace, Inc. | ARC discharge initiation for a pulsed plasma thruster |
| US6530212B1 (en) * | 2000-02-25 | 2003-03-11 | Photonic Associates | Laser plasma thruster |
| WO2005003557A1 (en) * | 2003-06-25 | 2005-01-13 | Design Net Engineering, Llc | Laser propulsion thruster |
| CN101737201A (en) * | 2008-11-04 | 2010-06-16 | 中国科学院物理研究所 | Laser propulsion device |
-
2010
- 2010-08-09 CN CN 201010249177 patent/CN102374146B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6373023B1 (en) * | 1999-03-02 | 2002-04-16 | General Dynamics (Ots) Aerospace, Inc. | ARC discharge initiation for a pulsed plasma thruster |
| US6530212B1 (en) * | 2000-02-25 | 2003-03-11 | Photonic Associates | Laser plasma thruster |
| WO2005003557A1 (en) * | 2003-06-25 | 2005-01-13 | Design Net Engineering, Llc | Laser propulsion thruster |
| CN101737201A (en) * | 2008-11-04 | 2010-06-16 | 中国科学院物理研究所 | Laser propulsion device |
Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103073370A (en) * | 2012-12-28 | 2013-05-01 | 中国科学技术大学 | Nitrine type high-molecular sensitized high-energy ablator, preparation method thereof and target belt made from ablator |
| CN103423116A (en) * | 2013-07-26 | 2013-12-04 | 西北工业大学 | Liquid working media laser plasma micro propulsion and target supply device |
| CN103912466A (en) * | 2014-04-10 | 2014-07-09 | 王文东 | Electric hydrodynamic force propeller |
| CN103912466B (en) * | 2014-04-10 | 2016-06-22 | 西安若水电气设备有限公司 | A kind of electrical fluid power propeller |
| CN104349569A (en) * | 2014-10-30 | 2015-02-11 | 北京大学 | Plasma lens-based laser ion accelerating system and accelerating method thereof |
| CN104349569B (en) * | 2014-10-30 | 2017-09-19 | 北京大学 | A kind of lasing ion acceleration system and its accelerated method based on plasmonic lenses |
| CN105952603B (en) * | 2016-04-28 | 2018-07-24 | 中国人民解放军国防科学技术大学 | Laser ablation pulses plasma thruster |
| CN105781920A (en) * | 2016-04-28 | 2016-07-20 | 中国人民解放军国防科学技术大学 | Magnetic plasma thrustor supported through lasers |
| CN105952603A (en) * | 2016-04-28 | 2016-09-21 | 中国人民解放军国防科学技术大学 | Laser ablation pulsed plasma thruster |
| CN105966641A (en) * | 2016-05-31 | 2016-09-28 | 南昌理工学院 | Throwing beam rocket propulsion system |
| CN107416759A (en) * | 2017-03-21 | 2017-12-01 | 东南大学 | A kind of nanojet microdriver, its preparation method and its application |
| CN107416759B (en) * | 2017-03-21 | 2019-03-29 | 东南大学 | A kind of nanojet microdriver, preparation method and its application |
| CN107725298A (en) * | 2017-09-30 | 2018-02-23 | 北华航天工业学院 | Optical-fiber laser self-propelled universe bareboat propulsion system |
| CN108275288A (en) * | 2017-12-19 | 2018-07-13 | 上海空间推进研究所 | Nontoxic double mode micromass culture system and its working method |
| CN108275288B (en) * | 2017-12-19 | 2020-04-10 | 上海空间推进研究所 | Non-toxic dual-mode micro-propulsion system and working method thereof |
| CN108869220A (en) * | 2018-06-07 | 2018-11-23 | 西安空间无线电技术研究所 | A kind of propulsion device and propulsion method for Spatial kinematics |
| CN111076937A (en) * | 2019-12-09 | 2020-04-28 | 北京理工大学 | System and method for testing ablation quality of energetic working medium pulse plasma thruster |
| CN112555114A (en) * | 2020-12-01 | 2021-03-26 | 中国人民解放军战略支援部队航天工程大学 | Electromagnetic combined vector accelerating spray pipe for laser ablation propulsion |
| CN112555114B (en) * | 2020-12-01 | 2022-06-17 | 中国人民解放军战略支援部队航天工程大学 | Electromagnetic combined vector acceleration spray pipe for laser ablation propulsion |
| CN112943571A (en) * | 2021-03-08 | 2021-06-11 | 中国科学院合肥物质科学研究院 | High specific impulse and high power space propeller based on compact ring plasma |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102374146B (en) | 2013-04-03 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102374146B (en) | Pulse laser plasma electricity hybrid micro-propulsion unit and method | |
| EP1681465B1 (en) | Systems and methods for plasma propulsion | |
| CN201162635Y (en) | Dual-electrode solid pulsed plasma thruster | |
| CN107387347B (en) | Hollow cathode thruster for cube satellite | |
| Ziemba et al. | High power helicon thruster | |
| RU2528013C2 (en) | Electric power generation | |
| CN208221007U (en) | Parallel polar plate type laser supported pulse plasma thruster | |
| EP2853736B1 (en) | Chemical-electromagnetic hybrid propulsion system with variable specific impulse | |
| US20050279094A1 (en) | Almost-perpetual ecology system | |
| CN111173698B (en) | Liquid working medium plasma thruster based on microwave enhancement | |
| CA2538827A1 (en) | Method and device for generating alfven waves | |
| RU2635951C1 (en) | Method for creating electric propulsion thrust | |
| JP2010275929A (en) | Laser propulsion system | |
| CN105201769A (en) | Laser plasma combined propelling system | |
| RU2162958C2 (en) | Method to accelerate working medium flow in rocket engine channel | |
| RU2397363C1 (en) | Combine plasma-ion airjet engine | |
| Gorshkov et al. | Development of high power magnetoplasmadynamic thrusters in the USSR | |
| JP2017002851A (en) | Vacuum arc propeller | |
| RU2277643C1 (en) | Plasma power source | |
| KR20220123007A (en) | Ion Booster for Thrust Generation | |
| RU2374481C1 (en) | Liquid-propellant rocket engine with additional electromagnetic acceleration of working body | |
| RU2776324C1 (en) | Ramjet relativistic engine | |
| US11149635B1 (en) | Closed compressed gas power and thermal management system | |
| Bering et al. | Using VASIMR® for the proposed europa mission | |
| FI91100C (en) | Collective ion accelerator propulsion device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20181220 Address after: 215505 No. 2 Jianye Road, High-tech Industrial Park, Changshu Economic and Technological Development Zone, Suzhou City, Jiangsu Province Patentee after: SUZHOU NAFEI SATELLITE POWER TECHNOLOGY CO., LTD. Address before: No. 3, North Tu Cheng West Road, Chaoyang District, Beijing Patentee before: Institute of Microelectronics, Chinese Academy of Sciences |
|
| TR01 | Transfer of patent right |