CN107914895A - 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
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- CN107914895A CN107914895A CN201710805623.XA CN201710805623A CN107914895A CN 107914895 A CN107914895 A CN 107914895A CN 201710805623 A CN201710805623 A CN 201710805623A CN 107914895 A CN107914895 A CN 107914895A
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- 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
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- 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
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Abstract
The invention discloses a kind of geostationary orbit spacecraft potential controlling apparatus and method, and spacecraft current potential is controlled by inductive switch, capacitor, photoelectron device and connection circuit.Wherein, capacitor one end is with being extremely connected 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, during no light, inductive switch disconnects.The advantage of the invention is that：The complexity of current potential active control technology is significantly reduced, and weight is small, low in energy consumption, simple in structure, spacecraft is influenced small.
Description
Technical field
The present invention relates to geostationary orbit spacecraft space environmental effect protection technology field, and in particular to a kind of earth
Geo-stationary orbit spacecraft potential controlling apparatus and its method.
Background technology
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 interaction such as spacecraft and space plasma and high energy electron
Tired, spacecraft entirety current potential can be raised 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.
For the above problem, in practice it has proved that be the effective way for reducing spacecraft entirety current potential using current potential active control technology
Footpath.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.Use at present
Current potential active control technology be to use open method, i.e., to spatial emission charged particle line, make spacecraft with it is empty
Between establish path between plasma " 0 current potential ", so as 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.
The content of the invention
In view of this, it is local the present invention provides a kind of geostationary orbit spacecraft potential controlling apparatus and its method
When ball geo-stationary orbit spacecraft operates in shadow region, geostationary orbit spacecraft can be realized it is closed, without working medium and from
The current potential active control of adaptation.
Technical scheme is as follows：
The geostationary orbit spacecraft potential controlling apparatus of the present invention includes inductive switch, capacitor, photoelectron emissions
Device and connection circuit；
Wherein, with being extremely connected the time of photoelectron device, the capacitor other end is sent out with photoelectron for capacitor one end
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, sensing is opened
Close and close, during no light, inductive switch disconnects.
It is preferred that capacitor is ultracapacitor.
Further, photoelectron device includes photoelectric tube and irradiates the LED light source of photoelectric tube.
A kind of geostationary orbit spacecraft potential control method of the present invention, using device of the present invention to spacecraft
Current potential is controlled, and is comprised 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 electric charge that spacecraft is accumulated in space environment causes occur internal electric field in photoelectron device；
By photoelectron device internal electric field, the electric charge that spacecraft is accumulated in space environment is filled from photoelectron emissions
The cathode put is launched into the receiving terminal of photoelectron device, and stores in the capacitor, thus avoid spacecraft current potential to
Negative potential declines, while photoelectron device internal electric field tapers into；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, close inductive switch, capacitor into
Row electric discharge, by the electric charge of storage by Spacecraft Launch into space；Step 2-3 is repeated, is realized to geostationary orbit
The continuous control of spacecraft current potential.
It is preferred that 1-3 minutes before geostationary orbit spacecraft enters earth's shadow area, inductive switch is disconnected, is opened
Photoelectron device.
Beneficial effect：
(1) the device of the invention need not additionally carry working medium, therefore light-weight, and the influence to spacecraft weight is small；No
Spacecraft surface texture need to be changed, avoid the trouble brought to spacecraft entirety thermal control etc..
(2) the device of the invention uses the ultracapacitor that the prior art can be realized, meets that GEO geostationary orbits navigate
Control of Electric potentials of its device in whole 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；
Brief description of the drawings
Fig. 1 is a kind of geostationary orbit spacecraft potential controlling apparatus schematic diagram of the present invention；
Wherein, 1- spacecrafts, 2- photoelectron devices, 3- inductive switches, 4- capacitors.
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 with being extremely connected 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
Put 2 electronic receipt end by inductive switch 3 with spacecraft 1 to be connected, the inductive switch 3 is light sensation inductive switch, is there is illumination
When, inductive switch closure, during no light, inductive switch disconnects.Capacitor 4 uses ultracapacitor, and capacitance is more than hundred methods.
When the spacecraft operates in solar irradiation area, photoelectron device 2 is closed, and inductive switch 3 closes；
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 is：
It is numerous for the influence factor of the spacecraft charged effect of period generation in orbit, in theory using Mott-
Spacecraft total current is described in Smith and Langmuir current balance equations：
I=Ie+Ii+Is+Ib+Ic+Ipho (1)
I in formula --- spacecraft total current；
Ie--- the electronic current on spacecraft surface is incided, the electricity that generally spacecraft is absorbed from space plasma
Electron current；
Ii--- incide the gas 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 that spacecraft is relative to space infinite point plasma when equation (1) reaches balance
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, spacecraft entirety current potential differ for positive several volts to tens volts.
First, 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；
2nd, inductive switch 3 disconnects when geostationary orbit spacecraft enters shadow region, while photoelectron device 2 is beaten
Open, after spacecraft enters shadow region, without illumination, then photoemission current IphoFor 0.Due to lacking photoemission current
Ipho, incide the electronic current I on spacecraft surfaceeIn the highest flight, spacecraft current potential U2Change to higher negative potential, that is, navigate
Its device current potential U2Decline, 2 both ends of photoelectron device will appear from potential difference Δ U at this time, and the inside of photoelectron device 2 produces
Electric field E, E=Δ U/L, wherein, L is the distance at 2 both ends of photoelectron device；
Whole process is expressed as：
U2↓ → Δ U=U1-U2＞ 0 → E=Δs 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 produces, is launched into 2 receiving terminal of photoelectron device and is stored in capacitor 4.Equation
(1) it is changed into：
I=Ie+Ii+Is+Ib+Ic+Ibeam (3)
I in formulabeamElectric current is produced for photoelectron device 2, works as IbeamGradually during increase, then spacecraft current potential U2Can be by
Gradually stop declining even gradually rising, so as to avoid spacecraft current potential to higher negative potential declining；
In the process, IbeamIt will not increase always, IbeamChange be dynamic process, due to IbeamPresence, capacitance
Device 4 is electrically charged, and then U1Decline, Δ U declines, and whole process is expressed as：
Ibeam＞ Ie→U2↑ and U1↓→ΔU↓ (4)
When Δ U decline to a certain extent, E field 0, IbeamIt will be changed into 0, U1=U2, spacecraft current potential reaches equilibrium-like
State；Due to inciding the electronic current I on spacecraft surfaceeLasting change, 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 tracks (geostationary orbit) spacecraft, GEO Orbital Space Vehicles are in-orbit
During operation, during 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 capacitance C can meet, according to U=Q/C, it is possible to being controlled spacecraft current potential in reduced levels in earth's shadow area.
3. geostationary orbit spacecraft leaves shadow region when being received again by solar irradiation, according to formula (1) spacecraft electricity
Position U2Will rise, close inductive switch 3 at this time, close photoelectron device 2, being stored in electric charge among capacitor 4 will be with
Photoemission current IphoIt is launched into space, capacitor 4 completes electric discharge, until U1=U2, return 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 disconnect inductive switch in 1-3 minutes before, open photoelectron device；In shadow region, if capacitor both ends appearance potential is poor,
Photoelectricity electron current then can be formed inside photoelectron device, spacecraft can pass through photoelectron current storage from Spatial absorptive electric charge
In the capacitor, as long as photoelectricity electron current and capacitance are sufficiently large, so that it may ensure spacecraft current potential during earth's shadow area is run
Reduced levels are controlled in, ensure spacecraft safety.
Situation of the apparatus and method of the present invention in earth's shadow area is illustrated with example below：
Capacitor 4 selects the K2 series supers capacitor 4 of Maxwell companies of U.S. production, and capacitance size C is 3400F；Light
Electron emitting device 2 includes photoelectric tube and irradiates the LED light source of photoelectric tube, wherein, the time extremely GaAs of photoelectric tube: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 electrons
Current density is also only nA/cm2Magnitude, with current density 10nA/cm2With spacecraft total surface area 100m2Calculate, in 72 minutes,
Spacecraft absorbs total electricity Q and is no more than 44C, is calculated with this electricity, according to U=Q/C, therefore when the capacitance size C of capacitor 4 is
During 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 is controlled in reduced levels in earth's shadow area.
The method being controlled using device of the present invention to geostationary orbit spacecraft current potential, including following step
Suddenly：
Step 1, when spacecraft operates in solar irradiation area, photoelectron device 2 is closed, and inductive switch 3 closes；
Step 2, when geostationary orbit spacecraft enters earth's shadow area, inductive switch 3 is disconnected, opens photoelectron hair
Injection device 2；
The electric charge that spacecraft is accumulated in space environment causes internal electric field occur in photoelectron device 2；
By 2 internal electric field of photoelectron device, the electric charge that spacecraft is accumulated in space environment is from photoelectron emissions
The cathode of device 2 is launched into the receiving terminal of photoelectron device 2, and is stored in capacitor 4, so as to avoid spacecraft electric
Position declines to negative potential, while 2 internal electric field of photoelectron device tapers into；2 internal electric field of photoelectron device disappears
During 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, closes inductive switch 3, capacitor
4 discharge, by the electric charge of storage by 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, during control, 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, ensures first
When entering shadow region, the control of Electric potentials to spacecraft can be also realized.
In conclusion the foregoing is merely a prefered embodiment of the invention, it is not intended to limit the scope of the present invention.
Within the spirit and principles of the invention, any modification, equivalent replacement, improvement and so on, should be included in the present invention's
Within protection domain.
Claims (5)
1. a kind of geostationary orbit spacecraft potential controlling apparatus, it is characterised 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, during no light, inductive switch disconnects.
A kind of 2. geostationary orbit spacecraft potential controlling apparatus as claimed in claim 1, it is characterised in that the capacitance
Device (4) is ultracapacitor.
A kind of 3. geostationary orbit spacecraft potential controlling apparatus as claimed in claim 1, it is characterised in that the photoelectricity
Sub- emitter (2) includes photoelectric tube and irradiates the LED light source of photoelectric tube.
4. a kind of geostationary orbit spacecraft potential control method, it is characterised in that using such as any rights of claim 1-3
It is required that the device is controlled spacecraft current potential, comprise the following steps：
Step 1, when spacecraft operates in solar irradiation area, photoelectron device (2) is closed, inductive switch (3) closure；
Step 2, when geostationary orbit spacecraft enters earth's shadow area, inductive switch (3) is disconnected, opens photoelectron emissions
Device (2)；
The electric charge that spacecraft is accumulated in space environment causes internal electric field occur in photoelectron device (2)；
By photoelectron device (2) internal electric field, the electric charge that spacecraft is accumulated in space environment is filled from photoelectron emissions
The cathode for putting (2) is launched into the receiving terminal of photoelectron device (2), and is stored in capacitor (4), so as to avoid space flight
Device current potential declines to negative potential, while photoelectron device (2) internal electric field tapers into；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, after spacecraft runs out shadow region, photoelectron device (2), closure inductive switch (3), capacitor are closed
(4) discharge, by the electric charge of storage by 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, it is characterised in that same in the earth
Walk Orbital Space Vehicle to enter before earth's shadow area 1-3 minutes, disconnect inductive switch (3), open photoelectron device (2).
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Cited By (1)
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