CN106683955A - Zero-power-consumption adaptive potential controller for spacecraft and manufacturing method for potential controller - Google Patents
Zero-power-consumption adaptive potential controller for spacecraft and manufacturing method for potential controller Download PDFInfo
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- CN106683955A CN106683955A CN201510765428.XA CN201510765428A CN106683955A CN 106683955 A CN106683955 A CN 106683955A CN 201510765428 A CN201510765428 A CN 201510765428A CN 106683955 A CN106683955 A CN 106683955A
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- tungsten filament
- spacecraft
- emitter
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- needle point
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01J—ELECTRIC DISCHARGE TUBES OR DISCHARGE LAMPS
- H01J1/00—Details of electrodes, of magnetic control means, of screens, or of the mounting or spacing thereof, common to two or more basic types of discharge tubes or lamps
- H01J1/02—Main electrodes
- H01J1/30—Cold cathodes, e.g. field-emissive cathode
- H01J1/304—Field-emissive cathodes
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05F—SYSTEMS FOR REGULATING ELECTRIC OR MAGNETIC VARIABLES
- G05F1/00—Automatic systems in which deviations of an electric quantity from one or more predetermined values are detected at the output of the system and fed back to a device within the system to restore the detected quantity to its predetermined value or values, i.e. retroactive systems
- G05F1/10—Regulating voltage or current
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01J—ELECTRIC DISCHARGE TUBES OR DISCHARGE LAMPS
- H01J9/00—Apparatus or processes specially adapted for the manufacture, installation, removal, maintenance of electric discharge tubes, discharge lamps, or parts thereof; Recovery of material from discharge tubes or lamps
- H01J9/02—Manufacture of electrodes or electrode systems
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Physics & Mathematics (AREA)
- Electromagnetism (AREA)
- General Physics & Mathematics (AREA)
- Radar, Positioning & Navigation (AREA)
- Automation & Control Theory (AREA)
- Elimination Of Static Electricity (AREA)
- Cold Cathode And The Manufacture (AREA)
Abstract
The invention discloses a zero-power-consumption adaptive spacecraft potential control method. According to the method, based on a field emission principle of a metal material, a metal sharp point is glued with carbon nanotubes to form a dual sharp-shaped electric field enhancement structure; based on the field emission performance of the carbon nanotubes, an electronic field emitter is manufactured; and when a relatively high potential difference exists between the spacecraft and space plasmas, the emitter can automatically emit electrons so as to lower the potential difference between the spacecraft and space plasmas to realize spacecraft potential control. The invention discloses a zero-power-consumption adaptive potential controller structure for the spacecraft and a manufacturing method for the potential controller structure. Compared with the existing spacecraft potential control method, the potential controller used in method disclosed by the invention has the advantages of simple structure, zero power consumption, capability of automatically regulating to emit current, and the like, and can be used in potential control of various kinds of low-track spacecrafts.
Description
Technical field
The invention belongs to spacecraft space environmental protection technical field, specifically, the present invention relates to a kind of
Spacecraft idle self adaptation potentiometric controller, and constitute the field emitter and their system of controller
Make method.
Background technology
With the development of space technology, the reliability requirement more and more higher to spacecraft, some space safeties
Hidden danger also gradually has emerged out.Because spacecraft and space plasma interact meeting therebetween
The shell of high potential difference is produced, many potential safety hazards are produced to spacecraft.With high energy solar battery array
Use, the potential difference in its shell is substantially increased, electric discharge risk more increases.At present, some are special,
Important spacecraft, such as ISS international space stations and Russian's Mir space station, all apply actively
Control of Electric potentials technology is guaranteeing smoothly completing for important operation in space environment.Active potential control technology
Refer to：Outside space plasma install one with the Plasma contact device being spatially connected, to space
One low-energy plasma beam of plasma emission makes spacecraft and space making up the electronics that it is filled with
The potential difference of plasma is in all the time poised state, so as to realize the active potential control of spacecraft.But
It is that this method needs to expend certain energy, and needs the corollary systems such as monitoring, control.
The present invention proposes a kind of idle self adaptation spacecraft potential control method.It and current active are electric
Position control method has similarity, is all to realize control of Electric potentials by outwards transmitting charged particle, but
There is difference, the method need not be monitored to spacecraft current potential, but when spacecraft current potential reaches one
When determining degree, independently start launching electronics, and electron stream size and current potential difference correlation, in addition, the method
Electron emission is driven using the voltage difference between spacecraft and extraneous plasma, without the need for consuming on spacecraft
The energy, structure is also significantly simpler than active potential control device.
The content of the invention
In space spacecraft charging can be possible to cause electric discharge phenomena, cause Spacecraft Material, device to damage
Ruin.Therefore, the potential control method of spacecraft is significant to ensureing the in-orbit safety of spacecraft.Boat
Its device control of Electric potentials at present method be mainly active potential control method, its need to spacecraft electricity
Position is monitored, it is found that current potential exceedes after safety value, and evoked potential control device, potential controlling apparatus lead to
Cross ionized gas and launch the modes such as charged particle stream, with space plasma charge-exchange is carried out, from
And reduce the purpose of spacecraft current potential.
The present invention proposes a kind of satellite field emission emitter for the demand of spacecraft control of Electric potentials.It
Spacecraft current potential need not be monitored, but when spacecraft current potential reaches certain numerical value, be opened automatically
Beginning launching electronics, after spacecraft current potential is reduced launching electronics are automatically stopped again.The transmitting of the method electronics
It is to be driven by the potential difference between spacecraft and space plasma, therefore need not consumes on spacecraft
The energy.
The invention provides a kind of spacecraft idle self adaptation potentiometric controller, the controller can be extensive
It is applied to the control of Electric potentials of low orbit spacecraft.
Additionally, present invention provides constituting the projectile configuration and its manufacture method of controller, the method
It is simple and efficient, it is obtained in that high-quality active potential control device.
Present invention employs following technical scheme：
A kind of spacecraft idle self adaptation potentiometric controller, field emission of the device based on metal material
Principle is realizing the control of Electric potentials to spacecraft.The controller is mainly by an Electron field emitters group
Into：CNT is pasted in metal tip and constitutes dual pointed electric-field-enhancement structure, using CNT
Field emission performance, make emitter.
Wherein, metal tip is tip curvature radius in micron-sized tungsten filament needle point.
Wherein, tungsten filament needle point be after tungsten filament is disconnected at the liquid level when corroding in sodium hydroxide solution,
What shearing was obtained.
A kind of manufacture method of satellite field emission emitter, comprises the steps：
1) metal tip is prepared
The tungsten filament of below diameter 1.5mm is vertically put into sodium hydroxide solution, is put into depth 1cm,
A spun gold annulus is placed immediately below tungsten filament, circle ring center is on tungsten filament vertical line, with tungsten filament vertical range
0.5-1cm, with tungsten filament as positive electrode, spun gold annulus is negative electrode, is powered, and voltage is 10-12V, electricity
Flow for 0.5A-0.1A, after tungsten filament is corroded and is disconnected at sodium hydroxide solution liquid level, take out tungsten filament,
And the tungsten filament of 1cm length is cut, in tungsten filament gap, tip curvature radius is defined in micron-sized pin
Point；
2) CNT is pasted on metal tip
Tungsten filament is pasted onto into one end of movable mechanism, in its tip end surface one layer of conductive adhesive is coated,
Single-wall carbon nanotube array or single pipe powder are pasted onto into the other end of travel mechanism, are utilized
Needle point near CNT, is judged whether needle point contacts upper CNT by travel mechanism by electrical circuit,
After contact is upper, move backward needle point away from CNT, CNT is stained with needle point, obtain
Single emitter.
Wherein, a diameter of 0.8mm to 1.2mm of tungsten filament, the concentration of NaOH is 1mol/L.
A kind of active potential control device of spacecraft, by some above-mentioned emitters are arranged together transmitting is formed
Volume array, spacing 0.5cm-2cm between emitter.
The manufacture method of the active potential control device of a kind of spacecraft, after prepared by single emitter, in metal
Equally spacedly make on flat board or conducting polymer plate and make depth for 5mm, the aperture battle array of a diameter of 1mm
Row, the tungsten filament needle point for being stained with CNT is put into aperture one by one, and is fixed with conductive glue.
Wherein, array of orifices is the aperture of 8 × 8 arrangements.
Wherein, the thickness of substrate is 6mm to 10mm.
Wherein, the spacing of aperture is selected between 1mm-20mm.
The method increases structure using metal needle point and CNT two-stage physical dimension, prepares field emission
Body, the field that can reduce emitter causes the voltage of current emission, so as to realize the electricity under low voltage difference
Son transmitting.Spacecraft potentiometric controller is prepared using the emitter, space flight can be worked as without the need for additional power source
Device and extraneous plasma are present after certain voltage difference, and electron emission is carried out automatically, reduce spacecraft with sky
Between plasma potential it is poor.Compared with other spacecraft potentiometric controllers, with simple structure, idle,
Adaptive advantage.
Description of the drawings
Fig. 1 is the SEM shape appearance figures of the tungsten filament point that chemical corrosion method is obtained in prior art；
Fig. 2 is by being pasted onto on tungsten point the SEM shape appearance figures for pasting CNT in projectile configuration of the invention；
Fig. 3 is the preparation process schematic diagram that the emitter of the present invention prepares tungsten filament point by corrosion.
Wherein, 1.1 is spun gold annulus；1.2 is tungsten filament；1.3 is container；1.4- sodium hydroxide solutions.
Fig. 4 is the process schematic for launching the stickup CNT on metal tip in preparation of the present invention.
In figure：The fixing end of 2.1- travel mechanisms；The mobile terminal of 2.2- travel mechanisms；2.3- conducting resinls；
2.4- tungsten filament needle points；2.5- ammeters；2.6- power supplys；2.7- CNTs.
Fig. 5 is to be stained with CNT process schematic on metal tip in transmitting preparation of the invention.
In figure：3.1- tungsten filament needle points are near CNT；3.2- tungsten filament needle points touch CNT；
3.3- tungsten filament needle points paste single-root carbon nano-tube from CNT.
Fig. 6 is using metal tip composition potentiometric controller (emitter array) for being stained with CNT.
Wherein：4.1- is stained with the tungsten filament needle point of CNT；4.2- metal substrates.
Specific embodiment
Below in conjunction with the accompanying drawings to the present invention spacecraft field emission emitter, the manufacture method of emitter,
The spacecraft active potential control device and its manufacture method that emitter is constituted is further described.
There is the method for obtaining tungsten filament point by chemical attack, the chemistry that it is obtained is rotten in prior art
The pattern of erosion tungsten filament point is referring to Fig. 1.Fig. 1 gives the SEM shape appearance figures of tungsten filament point.The projectile configuration of the present invention
In, based on the field-emission principles of metal material, paste CNT in metal tip and constitute dual point
Shape electric-field-enhancement structure, using the field emission performance of CNT, makes emitter, and metal tip is
Tip curvature radius in micron-sized tungsten filament needle point, tungsten filament needle point be by tungsten filament in sodium hydroxide solution
After disconnecting at liquid level during corrosion, what shearing was obtained, the pattern of its dual needle point is referring to Fig. 2.
Fig. 3 is the preparation process schematic diagram that the emitter of the present invention prepares tungsten filament point by corrosion.First, make
Metal needle point.(diameter of tungsten filament 1.1 can change, typically in 0.8mm extremely to take the tungsten filament 1.1 of diameter 1mm
Between 1.2mm), during it to be vertically put into the sodium hydroxide solution 1.4 of 1mol/L.The NaOH of solution
Content can change in container 1.3.The depth of the insertion solution of tungsten filament 1.1 is 1cm (can change).
A spun gold annulus 1.2 (can also be other inert metals, such as platinum) is placed immediately below tungsten filament 1.1,
Circle diameter is 15mm (can change).Annulus is that 1cm (can be with apart from tungsten filament bottom vertical interval
Change).With tungsten filament 1.1 as positive electrode, spun gold annulus 1.2 is negative electrode, is applied using constant pressure stabilized current supply
Plus 12V constant voltages, electric current is 0.5A (can change).Treat tungsten filament 1.1 from sodium hydroxide solution 1.4
After rupturing at liquid level, tungsten filament is extracted at once.The one end for having needle point is cut off from tungsten filament, is cut
The length of tungsten filament 1.1 is 1cm (can change).See Fig. 3
Secondly, CNT 2.7 is pasted on tungsten filament needle point 2.4.It is removable in a travel mechanism
End 2.2, fixed tungsten filament, tungsten filament needle point 2.4 points to travel mechanism's other end, i.e. fixing end 2.1.Moving
Motivation structure fixing end 2.1 first pastes conducting resinl 2.3, it is ensured that tungsten point moving direction is just to conducting resinl 2.3.
The fixing end 2.1 of travel mechanism and movable terminal ensure electric insulation.Travel mechanism two is terminated into ammeter 2.5
With power supply 2.6.Slow mobile travel mechanism so that tungsten filament is near conducting resinl 2.3.When ammeter 2.5 shows
When being shown with numerical value, illustrate that needle point is contacted with conducting resinl 2.3.Reverse movement tungsten filament so as to away from conduction
Glue 2.3.Change conducting resinl into single-wall carbon nanotube array (or the single being pasted onto on adhesive tape
Pipe powder), mobile travel mechanism so that tungsten filament needle point is near CNT.When ammeter shows electricity
During stream, illustrate that needle point contacts and be stained with CNT, pointing backwards is moved, obtaining tip has carbon to receive
The metal needle point of mitron.See Fig. 4 and Fig. 5.
3rd, it is regular on metal substrate 4.2 or conducting polymer plate to stamp depth for 5mm diameters
For the array of orifices of 1mm, such as aperture of 8 × 8 arrangements.The thickness of substrate is 6mm to 10mm.Between hole
Away from typically can selecting between 1mm-20mm.The tungsten filament needle point 4.1 for being stained with CNT is put into one by one
In aperture, and fixed with conductive glue.See Fig. 6.Complete the preparation of potentiometric controller.
Although giving detailed description to specific implementation of the patent mode above and illustrating, should refer to
Bright, we can carry out various equivalent changes to above-mentioned embodiment according to the conception of patent of the present invention
And modification, the function produced by it still without departing from specification and accompanying drawing covered it is spiritual when, all should
Within the protection domain of this patent.
Claims (10)
1. a kind of spacecraft field emission emitter, based on the field-emission principles of metal material, in gold
CNT is pasted on category tip and constitute dual pointed electric-field-enhancement structure, cause to send out using the field of CNT
Performance is penetrated, emitter is made.
2. emitter as claimed in claim 1, wherein, metal tip is tip curvature radius in micron
The tungsten filament needle point of level.
3. emitter as claimed in claim 1, wherein, tungsten filament needle point is in NaOH by tungsten filament
After disconnecting at liquid level when corroding in solution, what shearing was obtained.
4. a kind of manufacture method of spacecraft field emission emitter, comprises the steps：
1) metal tip is prepared
The tungsten filament of below diameter 1.5mm is vertically put into sodium hydroxide solution, is put into depth 1cm,
A spun gold annulus is placed immediately below tungsten filament, circle ring center is on tungsten filament vertical line, with tungsten filament vertical range
0.5-1cm, with tungsten filament as positive electrode, spun gold annulus is negative electrode, is powered, and voltage is 10-12V, electricity
Flow for 0.5A-0.1A, after tungsten filament is corroded and is disconnected at sodium hydroxide solution liquid level, take out tungsten filament,
And the tungsten filament of 1cm length is cut, in tungsten filament gap, tip curvature radius is defined in micron-sized pin
Point；
2) CNT is pasted on metal tip
Tungsten filament is pasted onto into one end of movable mechanism, in its tip end surface one layer of conductive adhesive is coated,
Single-wall carbon nanotube array or single pipe powder are pasted onto into the other end of travel mechanism, are utilized
Needle point near CNT, is judged whether needle point contacts upper CNT by travel mechanism by electrical circuit,
After contact is upper, move backward needle point away from CNT, CNT is stained with needle point, obtain
Single emitter.
5. manufacture method as claimed in claim 4, wherein, a diameter of 0.8mm to 1.2mm of tungsten filament,
The concentration of NaOH is 1mol/L.
6. a kind of spacecraft idle self adaptation potentiometric controller, by some any one of claim 1-3 institutes
The emitter formation emitter array arranged together stated, spacing 0.5cm-2cm between emitter.
7. a kind of manufacture method of spacecraft idle self adaptation potentiometric controller, claim 1-3 is arbitrary
After prepared by the emitter described in, work is equally spacedly made on metal plate or conducting polymer plate deep
Spend for 5mm, the array of orifices of a diameter of 1mm, the tungsten filament needle point for being stained with CNT is put into one by one aperture
In, and fixed with conductive glue.
8. manufacture method as claimed in claim 7, wherein, array of orifices is the apertures of 8 × 8 arrangements.
9. manufacture method as claimed in claim 7, wherein, the thickness of substrate is 6mm to 10mm.
10. manufacture method as claimed in claim 7, wherein, the spacing of aperture is selected in 1mm-20mm
Between.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510765428.XA CN106683955B (en) | 2015-11-11 | 2015-11-11 | The adaptive potentiometric controller of spacecraft idle and its manufacturing method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510765428.XA CN106683955B (en) | 2015-11-11 | 2015-11-11 | The adaptive potentiometric controller of spacecraft idle and its manufacturing method |
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| Publication Number | Publication Date |
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| CN106683955A true CN106683955A (en) | 2017-05-17 |
| CN106683955B CN106683955B (en) | 2019-01-25 |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101051596A (en) * | 2006-04-07 | 2007-10-10 | 清华大学 | Carbon nano tube field transmitting electronic source and its producing method |
| WO2007142133A1 (en) * | 2006-06-06 | 2007-12-13 | Kyushu Institute Of Technology | Discharge prevention device |
| CN101540253A (en) * | 2008-03-19 | 2009-09-23 | 清华大学 | Method for preparing field-emission electron source |
| CN102781150A (en) * | 2012-07-23 | 2012-11-14 | 北京卫星环境工程研究所 | Component for autonomously controlling structural potential of spacecraft |
| CN103014826A (en) * | 2012-12-06 | 2013-04-03 | 东南大学 | Preparation method and preparation device of tungsten probe for electrical measurement of nanometer device |
| CN103770953A (en) * | 2013-12-17 | 2014-05-07 | 兰州空间技术物理研究所 | Active control device and method for spacecraft structure potential |
-
2015
- 2015-11-11 CN CN201510765428.XA patent/CN106683955B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101051596A (en) * | 2006-04-07 | 2007-10-10 | 清华大学 | Carbon nano tube field transmitting electronic source and its producing method |
| WO2007142133A1 (en) * | 2006-06-06 | 2007-12-13 | Kyushu Institute Of Technology | Discharge prevention device |
| CN101540253A (en) * | 2008-03-19 | 2009-09-23 | 清华大学 | Method for preparing field-emission electron source |
| CN102781150A (en) * | 2012-07-23 | 2012-11-14 | 北京卫星环境工程研究所 | Component for autonomously controlling structural potential of spacecraft |
| CN103014826A (en) * | 2012-12-06 | 2013-04-03 | 东南大学 | Preparation method and preparation device of tungsten probe for electrical measurement of nanometer device |
| CN103770953A (en) * | 2013-12-17 | 2014-05-07 | 兰州空间技术物理研究所 | Active control device and method for spacecraft structure potential |
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| CN106683955B (en) | 2019-01-25 |
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Granted publication date: 20190125 Termination date: 20211111 |