CN107914895B - A kind of geostationary orbit spacecraft potential controlling apparatus and method - Google Patents
A kind of geostationary orbit spacecraft potential controlling apparatus and method Download PDFInfo
- Publication number
- CN107914895B CN107914895B CN201710805623.XA CN201710805623A CN107914895B CN 107914895 B CN107914895 B CN 107914895B CN 201710805623 A CN201710805623 A CN 201710805623A CN 107914895 B CN107914895 B CN 107914895B
- Authority
- CN
- China
- Prior art keywords
- spacecraft
- inductive switch
- photoelectron
- capacitor
- photoelectron device
- 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.)
- Active
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/52—Protection, safety or emergency devices; Survival aids
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Health & Medical Sciences (AREA)
- Critical Care (AREA)
- Emergency Medicine (AREA)
- General Health & Medical Sciences (AREA)
- Elimination Of Static Electricity (AREA)
Abstract
The invention discloses a kind of geostationary orbit spacecraft potential controlling apparatus and methods, control spacecraft current potential by inductive switch, capacitor, photoelectron device and connection circuit.Wherein, capacitor one end is extremely connected with the time of photoelectron device, the capacitor other end is connected with the electronic receipt end of photoelectron device, and the time of photoelectron device is extremely connected with spacecraft, and the electronic receipt end of photoelectron device is connected by inductive switch with spacecraft；The inductive switch is light sensation inductive switch, and when there is illumination, inductive switch closure, when no light, inductive switch is disconnected.The present invention has the advantages that significantly reducing the complexity of current potential active control technology, and weight is small, low in energy consumption, structure is simple, spacecraft is influenced small.
Description
Technical field
The present invention relates to geostationary orbit spacecraft space environmental effect protection technology fields, and in particular to a kind of earth
Geo-stationary orbit spacecraft potential controlling apparatus and its method.
Background technique
In space, usually using the plasma apart from spacecraft infinite point as " 0 current potential " reference point, work as spacecraft
In orbit at shadow region, electrostatic charge product occurs for the environmental interactions such as spacecraft and space plasma and high energy electron
Tired, spacecraft entirety current potential can be increased relative to " 0 current potential " to negative potential.In-orbit measured data shows severe in GEO substorm etc.
Under environmental condition, for spacecraft entirety current potential up to volts up to ten thousand, this has seriously affected the in-orbit safe and stable operation of spacecraft.
In response to the above problems, in practice it has proved that be effective way of reduction spacecraft entirety current potential using current potential active control technology
Diameter.A variety of current potential active control technologies have been developed both at home and abroad, and have obtained practical application, have achieved good result.It uses at present
Current potential active control technology be that spacecraft and empty that is, to spatial emission charged particle line, is made using open method
Between establish access between plasma " 0 current potential ", to reduce spacecraft current potential, and charged particle mainly relies on ionized gas
Working medium or liquid metal obtain, and weight, volume, the power consumption of current current potential active control technology are larger, and control system is more
It is complicated.
Summary of the invention
In view of this, the present invention provides a kind of geostationary orbit spacecraft potential controlling apparatus and its method, it is local
When ball geo-stationary orbit spacecraft operates in shadow region, can to geostationary orbit spacecraft realize it is closed, without working medium and from
The current potential active control of adaptation.
Technical scheme is as follows:
Geostationary orbit spacecraft potential controlling apparatus of the invention includes inductive switch, capacitor, photoelectron emissions
Device and connection circuit；
Wherein, capacitor one end is extremely connected with the time of photoelectron device, and the capacitor other end and photoelectron are sent out
The electronic receipt end of injection device is connected, and the time of photoelectron device is extremely connected with spacecraft, photoelectron device
Electronic receipt end is connected by inductive switch with spacecraft；The inductive switch is light sensation inductive switch, and when there is illumination, induction is opened
It closes and closes, when no light, inductive switch is disconnected.
Preferably, capacitor is supercapacitor.
Further, photoelectron device includes photoelectric tube and the LED light source for irradiating photoelectric tube.
A kind of geostationary orbit spacecraft potential control method of the invention, using device of the present invention to spacecraft
Current potential is controlled, comprising the following steps:
Step 1, when spacecraft operates in solar irradiation area, photoelectron device is closed, inductive switch closure；
Step 2, when geostationary orbit spacecraft enters earth's shadow area, inductive switch is disconnected, opens photoelectron hair
Injection device；
The charge that spacecraft is accumulated in space environment leads to occur internal electric field in photoelectron device；
By photoelectron device internal electric field, the charge that spacecraft is accumulated in space environment is filled from photoelectron emissions
The cathode set is launched into the receiving end of photoelectron device, and stores in the capacitor, thus avoid spacecraft current potential to
Negative potential decline, while photoelectron device internal electric field gradually becomes smaller；When photoelectron device internal electric field disappears, boat
Its device current potential reaches low potential equilibrium state, realizes the control to spacecraft current potential；
Step 3, after spacecraft runs out shadow region, close photoelectron device, be closed inductive switch, capacitor into
Row electric discharge, by the charge of storage through Spacecraft Launch into space；Step 2-3 is repeated, is realized to geostationary orbit
The continuous control of spacecraft current potential.
Preferably, disconnecting inductive switch 1-3 minutes before geostationary orbit spacecraft enters earth's shadow area, open
Photoelectron device.
The utility model has the advantages that
(1) the device of the invention does not need additionally to carry working medium, therefore light-weight, and the influence to spacecraft weight is small；No
Spacecraft surface texture need to be changed, avoided to the brings such as spacecraft entirety thermal control trouble.
(2) supercapacitor that the device of the invention uses the prior art may be implemented meets GEO geostationary orbit boat
Control of Electric potentials of its device in entire earth shadow region；
(3) the photoelectron device small power consumption that the device of the invention uses, it is only necessary to consume the use of high-brightness LED work
Electricity, total power consumption can be controlled in several watts；
(4) the method for the invention control process is simple, reduces the complexity of current potential active control technology；
Detailed description of the invention
Fig. 1 is a kind of geostationary orbit spacecraft potential controlling apparatus schematic diagram of the invention；
Wherein, 1- spacecraft, 2- photoelectron device, 3- inductive switch, 4- capacitor.
Specific embodiment
The present invention will now be described in detail with reference to the accompanying drawings and examples.
The present invention provides a kind of geostationary orbit spacecraft potential controlling apparatus, including inductive switch 3, capacitor 4,
Photoelectron device 2 and connection circuit；
Wherein, 4 one end of capacitor is extremely connected with the time of photoelectron device 2,4 other end of capacitor and photoelectron
The electronic receipt end of emitter 2 is connected, and the time of photoelectron device 2 is extremely connected with spacecraft 1, photoelectron emissions dress
It sets 2 electronic receipt end to be connected by inductive switch 3 with spacecraft 1, the inductive switch 3 is light sensation inductive switch, is there is illumination
When, inductive switch closure, when no light, inductive switch is disconnected.Capacitor 4 uses supercapacitor, and capacitor is greater than hundred methods.
When the spacecraft operates in solar irradiation area, photoelectron device 2 is closed, and inductive switch 3 is closed；
Inductive switch 3 disconnects when the spacecraft operates in shadow region, while photoelectron device 2 is opened.
The principle of spacecraft control of Electric potentials proposed by the present invention are as follows:
It is numerous for the influence factor of the spacecraft charged effect of period generation in orbit, theoretically use Mott-
Spacecraft total current is described in Smith and Langmuir current balance equation:
I=Ie+Ii+Is+Ib+Ic+Ipho (1)
I in formula --- spacecraft total current；
Ie--- it is incident on the electronic current on spacecraft surface, generally the electricity that absorbs from space plasma of spacecraft
Electron current；
Ii--- it is incident on the ionic current on spacecraft surface；
Is--- secondary electron electric current；
Ib--- backscattered electron electric current；
Ipho--- photoemission current；
Ic--- dielectric material leakage current.
The current potential of spacecraft is when equation (1) reaches balance, and spacecraft is relative to space infinite point plasma
Relative potentials.From equation (1) it can be seen that Ie、Ii、Is、IbAnd IcThe sum of each electric current is the space incident electronic current of spacecraft,
The height and polarities of potentials of the current potential of spacecraft depend on both space incident electronic current and photoemission current difference
Size and polarity.Under the illumination condition of 1 solar constant, photoemission current is typically larger than spacecraft surfacing at present
Space incident electronic current, several volts that spacecraft entirety current potential is positive are differed to tens volts.
One, when the operation of geostationary orbit spacecraft has solar irradiation area, photoelectron device 2 is closed, inductive switch 3
Closure, 4 both ends equipotential of capacitor, capacitor 4 do not charge, capacitor 4 and 2 electronic receipt end connecting pin of photoelectron device
Current potential is U1, spacecraft current potential is U2, wherein U1=U2；
Two, inductive switch 3 disconnects when geostationary orbit spacecraft enters shadow region, while photoelectron device 2 is beaten
It opens, after spacecraft enters shadow region, without illumination, then photoemission current IphoIt is 0.Due to lacking photoemission current
Ipho, it is incident on the electronic current I on spacecraft surfaceeIn the highest flight, spacecraft current potential U2Change to higher negative potential, that is, navigates
Its device current potential U2Decline, 2 both ends of photoelectron device generate appearance potential difference Δ U at this time inside photoelectron device 2
Electric field E, E=Δ U/L, wherein L is the distance at 2 both ends of photoelectron device；
Whole process statement are as follows:
U2↓ → Δ U=U1-U2> 0 → E=Δ U/L
In shadow region, the self adaptive control to spacecraft current potential is realized by electric field E: under the action of electric field E, photoelectron
The photoelectron that 2 cathode of emitter generates, is launched into 2 receiving end of photoelectron device and is stored in capacitor 4.Equation
(1) become:
I=Ie+Ii+Is+Ib+Ic+Ibeam (3)
I in formulabeamElectric current is generated for photoelectron device 2, works as IbeamWhen being gradually increased, then spacecraft current potential U2It can be by
Gradually stop decline even gradually rising, so that spacecraft current potential be avoided to decline to higher negative potential；
In the process, IbeamIt will not increase always, IbeamVariation be dynamic process, due to IbeamPresence, capacitor
Device 4 is electrically charged, and then U1Decline, Δ U decline, whole process statement are as follows:
Ibeam> Ie→U2↑ and U1↓→ΔU↓ (4)
When Δ U decline to a certain extent, E field 0, IbeamIt will become 0, U1=U2, spacecraft current potential reaches equilibrium-like
State；Due to being incident on the electronic current I on spacecraft surfaceeLasting variation, by electric field E realize to spacecraft current potential in shade
The process of the self adaptive control in area persistently occurs, and spacecraft current potential keeps the dynamic equilibrium of low potential.
The present invention is used for the whole star control of Electric potentials of GEO track (geostationary orbit) spacecraft, GEO Orbital Space Vehicle is in-orbit
During operation, when annual spring and fall equinoxes will experience earth's shadow area twice, 72 minutes or so every time.Therefore, existing super
Under the value that capacitor C is able to satisfy, according to U=Q/C, so that it may control spacecraft current potential in earth's shadow area in reduced levels.
3. geostationary orbit spacecraft leaves shadow region when being received again by solar irradiation, according to formula (1) spacecraft electricity
Position U2It will increase, and be closed inductive switch 3 at this time, and close photoelectron device 2, being stored in charge in capacitor 4 will be with
Photoemission current IphoIt is launched into space, capacitor 4 completes electric discharge, until U1=U2, it is restored into shadow region
Level before.
Apparatus of the present invention are in area of illumination, inductive switch closure, capacitor both ends equipotential, when entering earth's shadow area
Or 1-3 minutes before disconnection inductive switches, open photoelectron device；In shadow region, if capacitor both ends appearance potential is poor,
It then will form photoelectricity electron current inside photoelectron device, spacecraft can pass through photoelectron current storage from Spatial absorptive charge
In the capacitor, as long as photoelectricity electron current and capacitor are sufficiently large, so that it may guarantee spacecraft current potential during the operation of earth's shadow area
Reduced levels are controlled in, guarantee spacecraft safety.
Illustrate device and method of the present invention the earth's shadow area the case where with example below:
Capacitor 4 selects the K2 series super capacitor 4 of U.S. Maxwell company production, and capacitance size C is 3400F；Light
Electron emitting device 2 includes photoelectric tube and the LED light source for irradiating photoelectric tube, wherein the time of photoelectric tube extremely GaAs:Cs-O
Material, its average emitted current density is 53.8mA/W/cm after tested2, cathode material diameter 17.5mm；LED light source selects state
Blue-ray LED, wavelength 450nm are produced, luminous intensity reaches 1.2W/cm2.Its maximum photoelectricity electron current is up to 155mA；
In earth's shadow area, and under the most severe condition of space, GEO geostationary orbit spacecraft space incident electron
Current density is also only nA/cm2Magnitude, with current density 10nA/cm2With spacecraft total surface area 100m2It calculates, in 72 minutes,
Spacecraft absorbs total electricity Q and is no more than 44C, with the calculating of this electricity, according to U=Q/C, therefore when the capacitance size C of capacitor 4 is
When 3400F, the current potential that capacitor 4 receives photoelectric current one end can only decline 0.13V, using the method for the invention that spacecraft is electric
Position controls in earth's shadow area in reduced levels.
The method that geostationary orbit spacecraft current potential is controlled using device of the present invention, including following step
It is rapid:
Step 1, when spacecraft operates in solar irradiation area, photoelectron device 2 is closed, and inductive switch 3 is closed；
Step 2, when geostationary orbit spacecraft enters earth's shadow area, inductive switch 3 is disconnected, opens photoelectron hair
Injection device 2；
The charge that spacecraft is accumulated in space environment leads to internal electric field occur in photoelectron device 2；
By 2 internal electric field of photoelectron device, the charge that spacecraft is accumulated in space environment is from photoelectron emissions
The cathode of device 2 is launched into the receiving end of photoelectron device 2, and is stored in capacitor 4, to avoid spacecraft electric
Position declines to negative potential, while 2 internal electric field of photoelectron device gradually becomes smaller；2 internal electric field of photoelectron device disappears
When mistake, spacecraft current potential reaches low potential equilibrium state, realizes the control to spacecraft current potential；
Step 3, after spacecraft runs out shadow region, photoelectron device 2 is closed, is closed inductive switch 3, capacitor
4 discharge, by the charge of storage through Spacecraft Launch into space；Step 2-3 is repeated, is realized to Geo-synchronous rail
The continuous control of road spacecraft current potential.
In addition, in control process, in order to which the control of Electric potentials in the spacecraft in shadow region is better achieved, in Geo-synchronous
Orbital Space Vehicle enters before earth's shadow area 1-3 minutes, disconnects inductive switch 3, opens photoelectron device 2, guarantees first
When entering shadow region, it is also able to achieve the control of Electric potentials to spacecraft.
In conclusion the above is merely preferred embodiments of the present invention, being not intended to limit the scope of the present invention.
All within the spirits and principles of the present invention, any modification, equivalent replacement, improvement and so on should be included in of the invention
Within protection scope.
Claims (5)
1. a kind of geostationary orbit spacecraft potential controlling apparatus, which is characterized in that including inductive switch (3), capacitor
(4), photoelectron device (2) and connection circuit；
Wherein, capacitor (4) one end is extremely connected with the time of photoelectron device (2), capacitor (4) other end and photoelectricity
The electronic receipt end of sub- emitter (2) is connected, and the time of photoelectron device (2) is extremely connected with spacecraft (1), photoelectricity
The electronic receipt end of sub- emitter (2) is connected by inductive switch (3) with spacecraft (1)；The inductive switch (3) is light sensation
Inductive switch, when there is illumination, inductive switch closure, when no light, inductive switch is disconnected.
2. a kind of geostationary orbit spacecraft potential controlling apparatus as described in claim 1, which is characterized in that the capacitor
Device (4) is supercapacitor.
3. a kind of geostationary orbit spacecraft potential controlling apparatus as described in claim 1, which is characterized in that the photoelectricity
Sub- emitter (2) includes photoelectric tube and the LED light source for irradiating photoelectric tube.
4. a kind of geostationary orbit spacecraft potential control method, which is characterized in that using such as any right of claim 1-3
It is required that the device controls spacecraft current potential, comprising the following steps:
Step 1, when spacecraft operates in solar irradiation area, photoelectron device (2) is closed, inductive switch (3) closure；
Step 2, it when geostationary orbit spacecraft enters earth's shadow area, disconnects inductive switch (3), opens photoelectron emissions
Device (2)；
The charge that spacecraft is accumulated in space environment leads to internal electric field occur in photoelectron device (2)；
By photoelectron device (2) internal electric field, the charge that spacecraft is accumulated in space environment is filled from photoelectron emissions
The cathode for setting (2) is launched into the receiving end of photoelectron device (2), and is stored in capacitor (4), to avoid space flight
Device current potential declines to negative potential, while photoelectron device (2) internal electric field gradually becomes smaller；In photoelectron device (2)
When portion's electric field disappears, spacecraft current potential reaches low potential equilibrium state, realizes the control to spacecraft current potential；
Step 3, it after spacecraft runs out shadow region, closes photoelectron device (2), is closed inductive switch (3), capacitor
(4) it discharges, by the charge of storage through Spacecraft Launch into space；Step 2-3 is repeated, is realized to Geo-synchronous
The continuous control of Orbital Space Vehicle current potential.
5. a kind of geostationary orbit spacecraft potential control method as claimed in claim 4, which is characterized in that same in the earth
Step Orbital Space Vehicle enters before earth's shadow area 1-3 minutes, disconnects inductive switch (3), opens photoelectron device (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710805623.XA CN107914895B (en) | 2017-09-08 | 2017-09-08 | A kind of geostationary orbit spacecraft potential controlling apparatus and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710805623.XA CN107914895B (en) | 2017-09-08 | 2017-09-08 | A kind of geostationary orbit spacecraft potential controlling apparatus and method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107914895A CN107914895A (en) | 2018-04-17 |
| CN107914895B true CN107914895B (en) | 2019-03-08 |
Family
ID=61898623
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710805623.XA Active CN107914895B (en) | 2017-09-08 | 2017-09-08 | A kind of geostationary orbit spacecraft potential controlling apparatus and method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107914895B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109050994A (en) * | 2018-06-25 | 2018-12-21 | 兰州空间技术物理研究所 | A kind of electron emission type Satellite surface potential active controller of no working medium |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6220548B1 (en) * | 1998-09-14 | 2001-04-24 | The United States Of America As Represented By The Secretary Of The Navy | Deployed equipment modules for satellite architecture improvement |
| DE10318925A1 (en) * | 2003-03-05 | 2004-09-16 | Thales Electron Devices Gmbh | Propulsion device of a spacecraft and method for attitude control of a spacecraft with such a drive device |
| US7637461B1 (en) * | 2005-03-30 | 2009-12-29 | The United States Of America As Represented By The Secretary Of The Air Force | Approaches to actively protect spacecraft from damage due to collisions with ions |
| CN102774511A (en) * | 2012-08-03 | 2012-11-14 | 北京卫星环境工程研究所 | Spacecraft potential active control device based on helicon wave plasma and application thereof |
| CN104260905A (en) * | 2014-09-05 | 2015-01-07 | 兰州空间技术物理研究所 | Method for actively controlling surface electric potential of spacecraft |
| RU2612474C1 (en) * | 2015-10-13 | 2017-03-09 | Федеральное государственное унитарное предприятие "Научно-производственное объединение им. С.А. Лавочкина" | Protection method of spacecraft from static electricity and device for its implementation |
| CN106672268A (en) * | 2015-11-09 | 2017-05-17 | 北京卫星环境工程研究所 | Active space vehicle potential control system and control method based on energy conversion |
-
2017
- 2017-09-08 CN CN201710805623.XA patent/CN107914895B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6220548B1 (en) * | 1998-09-14 | 2001-04-24 | The United States Of America As Represented By The Secretary Of The Navy | Deployed equipment modules for satellite architecture improvement |
| DE10318925A1 (en) * | 2003-03-05 | 2004-09-16 | Thales Electron Devices Gmbh | Propulsion device of a spacecraft and method for attitude control of a spacecraft with such a drive device |
| US7637461B1 (en) * | 2005-03-30 | 2009-12-29 | The United States Of America As Represented By The Secretary Of The Air Force | Approaches to actively protect spacecraft from damage due to collisions with ions |
| CN102774511A (en) * | 2012-08-03 | 2012-11-14 | 北京卫星环境工程研究所 | Spacecraft potential active control device based on helicon wave plasma and application thereof |
| CN104260905A (en) * | 2014-09-05 | 2015-01-07 | 兰州空间技术物理研究所 | Method for actively controlling surface electric potential of spacecraft |
| RU2612474C1 (en) * | 2015-10-13 | 2017-03-09 | Федеральное государственное унитарное предприятие "Научно-производственное объединение им. С.А. Лавочкина" | Protection method of spacecraft from static electricity and device for its implementation |
| CN106672268A (en) * | 2015-11-09 | 2017-05-17 | 北京卫星环境工程研究所 | Active space vehicle potential control system and control method based on energy conversion |
Non-Patent Citations (2)
| Title |
|---|
| 空间站带电效应分析及对策;刘业楠等;《载人航天》;20130930;第19卷(第5期);第6-12页 |
| 航天器表面充电仿真计算和电位主动控制技术;田立成等;《航天器环境工程》;20120430;第29卷(第2期);第144-149页 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107914895A (en) | 2018-04-17 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10262836B2 (en) | Energy-efficient plasma processes of generating free charges, ozone, and light | |
| CN102774511A (en) | Spacecraft potential active control device based on helicon wave plasma and application thereof | |
| CN103434658A (en) | Method and device for cleaning space debris | |
| US9554452B2 (en) | Charged particle induction from ionosphere to ground | |
| CN107914895B (en) | A kind of geostationary orbit spacecraft potential controlling apparatus and method | |
| CN107275176A (en) | A kind of power supply to the ion source system and ion gun | |
| CN103770953A (en) | Active control device and method for spacecraft structure potential | |
| US9160156B2 (en) | System for harvesting atmospheric electricity | |
| US11296620B2 (en) | Metallic glow discharge diode and triode devices with large cold cathode as efficient charge generator—a power cell | |
| CN102781150A (en) | Component for autonomously controlling structural potential of spacecraft | |
| WO2019236693A2 (en) | Electrical potential energy to electrical kinetic energy converter, ozone generator, and light emitter | |
| CN113123936B (en) | Grid accelerating micro-cathode arc propulsion system | |
| CN102548172B (en) | Static discharge protective treatment method of satellite solar cell array | |
| JPH0752900A (en) | Method and device for extracting electron from space ship | |
| CN110165787A (en) | A kind of charging unit of electret machinery antenna | |
| CN106301061A (en) | Electron gun bipolarity high voltage power supply | |
| CN206059341U (en) | A kind of power supply to the ion source system and ion source | |
| Gu et al. | Pulsed IEC neutron generator | |
| EP4272810A3 (en) | Implantable system for constant current pacing | |
| Apollonov et al. | Large-aperture CO2 amplifier | |
| WO2019226142A1 (en) | Metallic glow discharge diode and triode devices with large cold cathode as efficient charge generator - a power cell | |
| CN109050994A (en) | A kind of electron emission type Satellite surface potential active controller of no working medium | |
| Seng et al. | Current sheath formation in the plasma focus | |
| CA2954591A1 (en) | A system and method for converting harvested low voltage potential energy, or high-voltage low current energy into a higher voltage potential energy, for use as a energy source | |
| Frechette et al. | Discharge characteristics in an asymmetrically-perturbed SF/sub 6/gap |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB03 | Change of inventor or designer information | ||
| CB03 | Change of inventor or designer information |
Inventor after: Yang Shengsheng Inventor after: Shi Liang Inventor after: Jiang Jie Inventor after: Tang Daotan Inventor after: Chen Yifeng Inventor after: Zhao Chengxuan Inventor after: Qin Xiaogang Inventor after: Wang Jun Inventor before: Shi Liang Inventor before: Yang Shengsheng Inventor before: Jiang Jie Inventor before: Tang Daotan Inventor before: Chen Yifeng Inventor before: Zhao Chengxuan Inventor before: Qin Xiaogang Inventor before: Wang Jun |
|
| GR01 | Patent grant | ||
| GR01 | Patent grant |