CN203819503U - Space fragment removing apparatus - Google Patents
Space fragment removing apparatus Download PDFInfo
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- CN203819503U CN203819503U CN201320528508.XU CN201320528508U CN203819503U CN 203819503 U CN203819503 U CN 203819503U CN 201320528508 U CN201320528508 U CN 201320528508U CN 203819503 U CN203819503 U CN 203819503U
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Abstract
The utility model discloses a space fragment removing apparatus comprising a satellite bearing platform. The satellite bearing platform is provided with by an electric field device or a magnetic field device or a combination of the electric field device and the magnetic field device removing space fragments. With low position detection precision of space fragments, micro space fragments can be effectively removed; solar energy can be well utilized to generate; self-bring energy can be reduced; an operation state of space fragments can be predicated in advance, thereby favoring automatic control of the space fragment removing apparatus; a direction of the electric field can be changed by the controller based on space fragment positions and operation directions; continuous high voltage bearing of an operation platform charge device can be further reduced; an absorbing action of high voltage electrodes to plasmas in surrounding environment can be decreased, thereby preventing plasma shielding surrounding the high voltage electrodes; and the space fragment removing apparatus is simply structured with low cost and great impulse effect.
Description
Technical field
The utility model belongs to space technology field, relates in particular to a kind of device of removing space debris.
Background technology
Space debris, specially refers to waste and derivant thereof that the mankind produce in space activity.Space debris has multiple source.No one can enough exact number that empties a fragment.The mankind can only carry out tracking and monitoring to 10 centimetres of above fragments of diameter at present, and by April, 2013, this class fragment has more than 16649.Wherein, carry out two countries of the United States, Russia that the space operation time grows, the space debris producing accounts for 29.7% and 37.6% of sum, and what China produced accounts for 22.5%.Being less than the fragment of 1 centimetre has tens million ofly and even several hundred million according to estimates, and spacecraft cannot be avoided and its collision at all, can only deal with by the protective capacities of strengthening self.
Space debris particularly micro space debris (1 centimetre following), due to One's name is legion, widely distributed, is difficult to effectively monitoring and follows the tracks of, and its pollution that space environment is caused has threatened the safety of spacecraft in-orbit.How effectively to slow down and remove micro space debris and just becoming current focus and the Disciplinary Frontiers of research in the world.
The method and apparatus of removing space debris in prior art is mainly to remove space debris by pulse type laser.The basic thought of this technology is to utilize high energy pulse laser beam irradiation fractal surfaces, produces and is similar to rocket-propelled " hot material jet ", reduces perigee altitude for fragment provides certain speed negative increment, reaches the object that shortens fragment orbital life.Document " the mechanical behavior pre-test of space debris is removed in light laser " (Peng Yufeng, contain rosy clouds of dawn etc., application laser, 2004.24 (1): 24-26) theory that paired pulses formula laser is removed space debris technology has been carried out initial analysis, has calculated to remove in the ideal case near-earth orbit (LEO) and be less than the required laser parameter of 10cm space debris.Utilize the application force of pulse type laser to change space debris orbit; What pulse type laser was removed fragment Technology Need is point-to-point thrust, and this just means fragment position sensing very high with the accuracy requirement that aims at transmitting, therefore, almost cannot effectively remove micro space debris (1 centimetre following).
Utility model content
The technical problems to be solved in the utility model is to provide a kind of device of removing space debris, and this device, without very high to the accuracy requirement of space debris position sensing, can be removed micro space debris (1 centimetre following) effectively.
With regard to removing the method for space debris, for solving the problems of the technologies described above, the utility model provides a kind of method of removing space debris, to applying electromagnetic force at the space debris of original track operation; Described electromagnetic force comprises the combination of electric field force or magnetic field force or electric field force and magnetic field force; The combination of described electric field force and magnetic field force is first space debris to be applied to electric field force again space debris to be applied to magnetic field force, or first space debris is applied to magnetic field force and again space debris is applied to electric field force, or when being applied to electric field force, space debris also space debris is applied to magnetic field force; Size and/or the direction of space debris speed under the effect of electromagnetic force change; Space debris after change speed is changed into new-track operation under gravitational effect; Space debris is at least low at the perigee altitude of original track than this space debris at the perigee altitude of new-track; Under the effect of the space debris moving at new-track at atmospherical drag, finally crash into earth dense atmosphere.
Angle between the direction of the direction of described electric field force and space debris speed is more than or equal to 63.4 ° and be less than or equal to 243.4 °.
Angle between the direction of the direction of described electric field force and space debris speed is more than or equal to 150 ° and be less than or equal to 160 °.
Electric field force in described electromagnetic force is Pulse Electric field force.
The method that the utility model is removed space debris has following beneficial effect with respect to prior art.
1, the technical program is due to the technological means having adopted apply electromagnetic force at the space debris of original track operation, space debris is conventionally with negative charge, so, size and/or the direction of space debris speed under the effect of electromagnetic force change, and the space debris after change speed is changed into new-track operation under gravitational effect; Space debris is at least low at the perigee district of original track height than this space debris at the perigee altitude of new-track; Under the effect of the space debris moving at new-track at atmospherical drag, finally crash into earth atmosphere.Again because electromagnetic force is realized by Electric and magnetic fields, and Electric and magnetic fields can produce in a big way, space debris is compared with Electric and magnetic fields, comparing with a large space like a spherula, because the quantity of space debris is a lot, so space debris is easy to enter the sphere of action of Electric and magnetic fields.Use the method without very high to the accuracy requirement of space debris position sensing, can effectively remove micro space debris (1 centimetre following).
2, the technical program is owing to having adopted angle between the direction of electric field force and the direction of space debris speed to be more than or equal to 63.4 ° and be less than or equal to the technological means of 243.4 °, so, can guarantee that space debris moves to the earth's core direction.
3, the technical program is owing to having adopted angle between the direction of electric field force and the direction of space debris speed to be more than or equal to 150 ° and be less than or equal to the technological means of 160 °, so, can guarantee that space debris moves to the earth's core direction more significantly.
4, the technical program is the technological means of Pulse Electric field force owing to having adopted the electric field force in electromagnetic force, and Pulse Electric field force has very large impact effect to space debris, so, can further improve the action effect to space debris.
With regard to removing the device of space debris, for solving the problems of the technologies described above, the utility model provides a kind of device of removing space debris, comprises Piggybacking platform; Described Piggybacking platform is provided with removes the electric field arrangement of space debris or the combination of magnetic field device or electric field arrangement and magnetic field device.
The electric field arrangement of described removing space debris comprise two space certain distances, mutually in the face of and the netted capacitor board that is parallel to each other; Described two netted capacitor boards are connected with positive pole and the negative electricity of direct supply respectively; The magnetic field device of described removing space debris comprise two space certain distances, mutually in the face of and the tabular magnet that is parallel to each other; Wherein, the S utmost point of a tabular magnet and the N utmost point of another tabular magnet are faced mutually; The electric field arrangement of described removing space debris and the combination of magnetic field device are: described electric field arrangement and described magnetic field device phase juxtaposition, be the outside that two tabular magnet of described magnetic field device are positioned at a netted capacitor board of described electric field arrangement, described two tabular magnet are parallel to each other and perpendicular to described netted capacitor board; Electric wireline in described electric field arrangement is vertical with the magnetic line of force in described magnetic field device; Or described electric field arrangement and described magnetic field device intersect to be put, i.e. two of described magnetic field device tabular magnet both sides between two netted capacitor boards of described electric field arrangement, described two netted capacitor boards are respectively perpendicular to described two tabular magnet; Electric wireline in described electric field arrangement is vertical with the magnetic line of force in described magnetic field device.
Described two netted capacitor boards are connected with positive pole and the negative electricity of direct supply respectively by electric field pulse device; " U " shape iron core that two opposing faces of tabular magnet in described magnetic field device bend by inward at both ends is fixedly connected with; On described " U " shape iron core, be wound with coil; The two ends of described coil are connected with positive pole and the negative electricity of described power supply respectively; Described power supply is solar cell or solar storage battery.
Described electric field pulse device comprises the first aerotron and the second aerotron; The base stage of the first aerotron is electrically connected with the collecting electrode of the second aerotron; The base stage of described the second aerotron is electrically connected with one end of one end of resistance and the first electric capacity; The other end of described resistance is electrically connected with emitter, one end of the second electric capacity and the positive pole of power supply of the first aerotron; The other end of described the second electric capacity is just electrically connected one end of polar curve circle with emitter and the step-up transformer of the negative pole of power supply, the second aerotron; The other end of described the first electric capacity is electrically connected with the collecting electrode of the first aerotron and the other end of the first polar curve circle of step-up transformer; The two ends of described step-up transformer secondary coil are electrically connected with described two netted capacitor boards respectively.
The device of described removing space debris is provided with controller and space debris detection device; The signal output part of described space debris detection device is electrically connected with the signal input part of described controller; Between described two netted capacitor boards, be electrically connected by short circuiting switch; The signal input part of described short circuiting switch is electrically connected with the signal output part of described controller; Between described two netted capacitor boards and described electric field pulse device, be electrically connected by the first electrode converting switch device, or, between described electric field pulse device and power supply, be electrically connected by the first electrode converting switch device; Described first signal input part of electrode converting switch device and the signal output part of described controller are electrically connected; Described two tabular magnet and described " U " shape iron core are made by soft iron or silicon steel material respectively; Described coil two ends are connected with positive pole and the negative electricity of direct supply respectively by the second electrode converting switch device; Described second signal input part of electrode converting switch device and the signal output part of described controller are electrically connected.
The device that the utility model is removed space debris has following beneficial effect with respect to prior art.
1, the technical program is owing to having adopted Piggybacking platform, Piggybacking platform is provided with removes the electric field arrangement of space debris or the technological means of magnetic field device or electric field arrangement and magnetic field device combination, space debris is conventionally with negative charge, so, size and/or the direction of space debris speed under the effect of electric field arrangement and/or magnetic field device change, and the space debris after change speed is changed into new-track operation under gravitational effect; Space debris is at least low at the perigee altitude of original track than this space debris at the perigee altitude of new-track; Under the effect of the space debris moving at new-track at atmospherical drag, finally crash into earth atmosphere.Again because electromagnetic force is realized by Electric and magnetic fields, and Electric and magnetic fields can produce in a big way, space debris is compared with Electric and magnetic fields, comparing with a large space like a spherula, because the quantity of space debris is a lot, so space debris is easy to enter the sphere of action of Electric and magnetic fields.Use the method without very high to the accuracy requirement of space debris position sensing, can effectively remove micro space debris (1 centimetre following).
2, the technical program due to adopted the electric field arrangement of removing space debris comprise two space certain distances, mutually in the face of and the netted capacitor board that is parallel to each other, two technological means that netted capacitor board is connected with positive pole and the negative electricity of direct supply respectively, so, there is beneficial effect simple in structure, easy to manufacture.When adopted the magnetic field device of removing space debris comprise two space certain distances, mutually in the face of and the tabular magnet that is parallel to each other; Wherein, the technological means that the S utmost point of a tabular magnet and the N utmost point of another tabular magnet are faced mutually, similarly, has beneficial effect simple in structure, easy to manufacture.When having adopted electric field arrangement and magnetic field device phase juxtaposition, two netted capacitor boards of electric field arrangement are respectively perpendicular to two tabular magnet of described magnetic field device, electric wireline in electric field arrangement and the magnetic line of force in described magnetic field device intersect vertical technological means, not only have simple in structure, beneficial effect easy to manufacture, and, can give full play to electric field force and magnetic field force advantage separately, more advantageously remove space debris.Put when having adopted electric field arrangement and magnetic field device to intersect, two netted capacitor boards of electric field arrangement are respectively perpendicular to two tabular magnet of magnetic field device, electric wireline in electric field arrangement and the crossing vertical technological means of magnetic line of force in magnetic field device, not only there is above-mentioned technique effect, and, also help electric field arrangement and magnetic field device are combined compactly, be convenient to the device of removing space debris to send into space.
3, the technical program is owing to having adopted two technological means that netted capacitor board is connected with positive pole and the negative electricity of direct supply respectively by electric field pulse device, so, can further improve the action effect to space debris.Adopt continuous impulse voltage power supply mode, the one, can alleviate report control platform charging unit and continue to bear high-tension load; The 2nd, can effectively slow down the adsorption of high-field electrode to surrounding environment applying plasma, avoid forming plasma shield (be Debye shielding, avoid making the electric field action of high-field electrode apart within being only confined to very short distance) around it.Again because " U " shape iron core that has adopted two opposing faces of tabular magnet in magnetic field device to bend by inward at both ends is fixedly connected with, on " U " shape iron core, be wound with coil, the technological means that the two ends of coil are connected with positive pole and the negative electricity of power supply respectively, so, can realize the control to magnetic field; Also the technological means of solar cell or solar storage battery owing to having adopted power supply, so, can make full use of solar electrical energy generation, save and carry the energy.
4, the technical program is owing to having adopted electric field pulse device to comprise two aerotrons; The base stage of the first aerotron is electrically connected with the collecting electrode of the second aerotron; The base stage of the second aerotron is electrically connected with one end of one end of resistance and the first electric capacity; The other end of resistance is electrically connected with emitter, one end of the second electric capacity and the positive pole of power supply of the first aerotron; The other end of the second electric capacity is just electrically connected one end of polar curve circle with emitter and the step-up transformer of the negative pole of power supply, the second aerotron; The other end of the first electric capacity is electrically connected with the collecting electrode of the first aerotron and the other end of the first polar curve circle of step-up transformer; The two ends of step-up transformer secondary coil respectively with described two technological means that netted capacitor board is electrically connected, so, there is the beneficial effect of simple in structure, low cost of manufacture and pulsating effect better effects if.
5, the technical program is owing to having adopted the device of removing space debris to be provided with controller and space debris detection device, the technological means that the signal output part of space debris detection device is electrically connected with the signal input part of controller, so, can look-ahead go out the running state of space debris, the automatic control of removing space debris device for realizing provides favourable condition.Be electrically connected by short circuiting switch owing to having adopted between two netted capacitor boards again, the signal input part of short circuiting switch is electrically connected with the signal output part of described controller, between two netted capacitor boards and electric field pulse device, be electrically connected by the first electrode converting switch device, the technological means that first signal input part of electrode converting switch device and the signal output part of described controller are electrically connected, so, not only controller can change according to the direction of the position of space debris and operation the direction of electric field, and, can also alleviate further report control platform charging unit and continue to bear high-tension load, more effectively slow down the adsorption of high-field electrode to surrounding environment applying plasma, avoid forming plasma shield (be Debye shielding, avoid making the electric field action of high-field electrode apart within being only confined to very short distance) around it.When having adopted two tabular magnet and " U " shape iron core to be made by soft iron or silicon steel material respectively, coil two ends are connected with positive pole and the negative electricity of direct supply respectively by the second electrode converting switch device, the technological means that second signal input part of electrode converting switch device and the signal output part of controller are electrically connected, similarly, controller can change according to the direction of the position of space debris and operation the direction in magnetic field.
Brief description of the drawings
Fig. 1 is method of the present utility model is removed space debris general plotting schematic diagram by electromagnetic force.
Fig. 2 is method of the present utility model is removed space debris the first embodiment schematic diagram by electric field force.
Fig. 3 is method of the present utility model is removed space debris the second embodiment schematic diagram by electric field force.
Fig. 4 is method of the present utility model is removed the third embodiment of space debris schematic diagram by electric field force.
Fig. 5 is method of the present utility model is removed space debris embodiment schematic diagram by magnetic field force.
Fig. 6 is the apparatus structure schematic diagram (electric field arrangement is only shown) that the utility model is removed space debris.
Fig. 7 is the schematic diagram that the utility model is removed device (electric field) the first removing space debris state of space debris.
Fig. 8 is the schematic diagram that the utility model is removed device (electric field) the second removing space debris state of space debris.
Fig. 9 is the schematic diagram that the utility model is removed device (magnetic field) the first removing space debris state of space debris.
Figure 10 is the schematic diagram that the utility model is removed device (magnetic field) the second removing space debris state of space debris.
Figure 11 is that the utility model is removed electric field arrangement and the juxtaposed structural representation of magnetic field device in the device of space debris.
Figure 12 is that the utility model is removed electric field arrangement and magnetic field device in the device of space debris and handed over the structural representation of putting.
Figure 13 is the schematic diagram that the utility model is removed electric field pulse device circuit structure in the device of space debris.
Figure 14 is the schematic diagram that the device middle controller of the utility model removing space debris is electrically connected with each parts.
Figure 15 is the space debris corresponding relation schematic diagram of life-span (year) and orbit altitude (km) in-orbit.
Figure 16 is space debris velocity increment schematic vector diagram.
Figure 17 is space debris velocity angle and the schematic diagram that is related to that falls rail height.
Figure 18 is space debris surface charging suspended voltage and relation (d=1cm) schematic diagram that falls rail height.
Figure 19 is poor relation (d=1cm) schematic diagram with falling rail height of space debris migration potential.
Figure 20 is space debris diameter and the schematic diagram that is related to that falls rail height.
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, the utility model is described in further detail.
As shown in Figures 1 to 5, a kind of method of removing space debris that the utility model embodiment provides, to applying electromagnetic force F at the space debris 2 of original track operation; Described electromagnetic force F comprises electric field force F
eor magnetic field force F
mor electric field force F
ewith magnetic field force F
mcombination; Described electric field force F
ewith magnetic field force F
mcombination be first space debris 2 to be applied to electric field force F
eagain space debris 2 is applied to magnetic field force F
m, or first space debris 2 is applied to magnetic field force F
magain space debris 2 is applied to electric field force F
e, or space debris 2 is applied to electric field force F
etime also space debris is applied to magnetic field force F
m; Size and/or the direction of space debris 2 speed V under the effect of electromagnetic force F change; Space debris 2 after change speed, under the effect of the earth 1 gravitation, leaves original track and moves to new-track, and the perigee altitude of new-track is less than the perigean height of original track; Space debris 2 in new-track operation finally crashes in earth dense atmosphere 1 under the effect of atmosphere 3 resistances.
As can be seen from Figure 2, when starting, hypothesis space fragment 2 makes uniform circular motion at original track, when under the effect at electric field force Fe, angle between the direction of the direction of this electric field force Fe and space debris 2 running velocitys is greater than direction deflection the earth's core one side of 90 ° and electric field force Fe, the size and Orientation of space debris 2 speed all changes, under gravitational effect, space debris 2 leaves original track to overhead nearer elliptical orbit operation.Because overhead nearlyer atmosphere is denser, the atmospherical drag of space debris flight is also just larger, so space debris 2 can constantly reduce at the effect lower railway height of atmosphere 3 resistances, finally crashes in earth dense atmosphere 1.
As can be seen from Figure 3, when starting, hypothesis space fragment 2 makes uniform circular motion at original track, when under the effect at electric field force Fe, the direction that angle between the direction of the direction of this electric field force Fe and space debris 2 running velocitys equals 90 ° and electric field force Fe deviates from the earth's core, the size and Orientation of space debris 2 speed all changes, under gravitational effect, the orbital eccentricity of space debris 2 increases and forms elliptical orbit, elliptical orbit perigee altitude is less than original track height, and space debris 2 atmospherical drag in region, elliptical orbit perigee increases.Space debris 2 finally crashes in earth dense atmosphere 1 under the effect of atmosphere 3 resistances.
As can be seen from Figure 4, when starting, hypothesis space fragment 2 makes uniform circular motion at original track, when under the effect at electric field force Fe, angle between the direction of the direction of this electric field force Fe and space debris 2 running velocitys equals the direction of 90 ° and electric field force Fe and points to the earth's core, the size and Orientation of space debris 2 speed all changes, under gravitational effect, the orbital eccentricity of space debris 2 increases and forms elliptical orbit, elliptical orbit perigee altitude is less than original track height, and space debris 2 atmospherical drag in region, elliptical orbit perigee increases.Space debris 2 finally crashes in earth dense atmosphere 1 under the effect of atmosphere 3 resistances.
As can be seen from Figure 5, when starting, hypothesis space fragment 2 makes uniform circular motion at original track, when under the effect at magnetic field force Fm, angle between the direction of the direction of this magnetic field force Fm and space debris 2 running velocitys equals the direction of 90 ° and magnetic field force Fm and points to the earth's core, the direction of space debris 2 speed changes, under gravitational effect, the orbital eccentricity of space debris 2 increases and forms elliptical orbit, elliptical orbit perigee altitude is less than original track height, and space debris 2 atmospherical drag in region, elliptical orbit perigee increases.Space debris 2 finally crashes in earth dense atmosphere 1 under the effect of atmosphere 3 resistances.
When can be generalized to space debris 2 and start, above analysis makes the situation of oval variable-speed motion at original track.
After deliberation find, when space debris flies in space plasma environment conventionally with negative charge.Produce an artificial electric field by design, in the time that flying over artificial electric field, charging space fragment produces the effect of electric field force, space debris is slowed down, thereby reduce the orbit of space debris, make it directly crash into that atmospheric envelope burns or accelerate to crash into atmospheric envelope because atmospherical drag increases, reaching the object of removing space debris.
Feature of the present utility model is according to space debris charged build-in attribute in place plasma environment, utilize the untouchable and directivity of electric field or magnetic fields, charged object in certain area is applied to electric field force and/or magnetic field force effect, make it obtain certain velocity increment (being generally negative increment) and then change orbit, and without the prior state of the each small fragment of accurate tracking.
Because earth atmosphere is around overhead more eminence is thinner, more weak to the resistance of space debris in-orbit, space debris in-orbit the life-span longer.On the contrary, if orbit altitude reduce, because of atmospherical drag increase, space debris in-orbit the life-span can greatly shorten, as shown in figure 15.Generally, on the track that is overhead highly less than 2000km, atmospherical drag plays a role clearly, so the object that the utility model is removed is mainly the micro space debris that is overhead highly less than 2000km.
To space debris, the charged situation in natural environment is illustrated below.
Space plasma is the important component part of space environment, is almost full of whole solar-terrestrial physics, and around the earth, most orbital environment is all in plasmoid.Overhead highly be less than the orbital region of 2000km and substantially overlapping in the earth ionosphere of plasmoid.Ionosphere is to act on upper atmosphere by sun high-energy electromagnetic radiation, cosmic ray and precipitate particles, makes it to produce ionization and the very low quasi-neutral plasma region of the energy being made up of electronics, ion and neutral ion of generation, and temperature is 180 ~ 3000K.The density of space plasma, component, energy change with height.Exemplary electronic density when table 1 has provided the inherent solar activity of 60 ~ 2000km altitude range peak is with the changing value of height, and its peak concentration generally appears at highly about 300km place.
Exemplary electronic density when table 1 solar activity peak, electron energy are with the changing value of height
| Overhead height/km | Density of electrons/cm-3 |
| 60 | 2 10 2 |
| 85 | 1 10 4 |
| 140 | 2 10 5 |
| 200 | 5 10 5 |
| 300 | 2 10 6 |
| 400 | 1.5 10 6 |
| 500 | 1 10 6 |
| 600 | 6 10 5 |
| 700 | 4 10 5 |
| 800 | 3 10 5 |
| 900 | 2 10 5 |
| 1000 | 1 10 5 |
| 2000 | 2.5 10 4 |
When space debris flies in space plasma environment, surface can be accumulated a certain amount of negative charge conventionally, and space environment presents negative potential.Research shows, in Low Earth Orbit (LEO) (LEO, orbit altitude is less than 2000km) environment, negative electricity is filled on space object surface, and current potential is generally at a few volt to tens volts, upper kilovolt of Gao Shikeda.
Improve as the one of present embodiment, the angle between the direction of described electric field force and the direction of space debris speed is more than or equal to 63.4 ° and be less than or equal to 243.4 °.
Present embodiment is owing to having adopted angle between the direction of electric field force and the direction of space debris speed to be more than or equal to 63.4 ° and be less than or equal to the technological means of 243.4 °, so, can guarantee that space debris moves to the earth's core direction.
As the further improvement of present embodiment, the angle between the direction of described electric field force and the direction of space debris speed is more than or equal to 150 ° and be less than or equal to 160 °.
Further improve the electric field force F in described electromagnetic force F as present embodiment
eit is Pulse Electric field force.
Utilize artificial electric field arrangement to remove the effect analysis of space debris.
(being preferably pulse) electromotive force that artificial electric field arrangement produces acts on electronegative space debris, is equivalent to space debris to apply a momentum, makes the certain velocity increment of the instantaneous acquisition of space debris.It is also that space debris obtains certain energy that space debris obtains velocity increment.
If carried charge is
qspace debris mobile electric potential difference in electric field be Δ
v p, artificial electric field to the acting size of space debris is
(1)
Wherein, carried charge
qcan try to achieve by following formula is approximate
(2)
In formula, permittivity of vacuum
,
dfor fragment diameter,
v ffor the floating potential after space debris surface charging.Wushu (2) substitution formula (1)
(3)
Artificial electric field is converted to the kinetic energy of space debris to space debris institute work, have
(4)
In formula,
be the velocity increment that artificial electric field action rear space fragment obtains.Bringing formula (3) into above formula has
(5)
Have for diameter of Spherical Volume fragment
(6)
In formula,
for space debris density, generally desirable
.
(6) are brought into (5) can be obtained
(7)
The object of artificial electric field is to reduce the orbit altitude of space debris, and orbit altitude only depends on semi-major axis and the eccentricity of track.From track dynamics knowledge, semi-major axis of orbit and the eccentricity transient change under Impulse is
(8)
(9)
In formula,
,
,
,
be respectively semi-major axis of orbit, eccentricity, true neargrazing angle, eccentric anomaly,
for space debris mean angular velocity of satellite motion,
,
be respectively under artificial electric field action space debris orbital drive to the velocity increment of horizontal generation, as shown in figure 16.
Perigee of orbit height again
r p for
(10)
If the preliminary orbit of space debris be circular orbit (
e=0), (8) and (9) can further be reduced to
(11)
(12)
And space debris mean angular velocity of satellite motion is
(13)
In formula, Gravitational coefficient of the Earth
.
As shown in figure 16, by angle
θbe called the velocity angle of velocity increment and space debris orbital velocity, velocity increment can be expressed as at component laterally and radially
(14)
(15)
If space debris preliminary orbit is circular orbit, convolution (10), (11) and (12) can obtain, and before and after pulse voltage effect, the change amount of space debris perigee track is
(16)
Bringing formula (14) and (15) into above formula can obtain
(17)
Formula (17) is the model of evaluating artificial electric field space manipulation effect according to (Δ
r p with the relation in life-span in-orbit can be referring to Figure 15).Convolution (7) can be found out, affects artificial electric field manipulation effect (Δ
r p ) principal element be:
Velocity angle
θ
Space debris surface charging suspended voltage
v f
The electric potential difference Δ that space debris moves in artificial electric field
v p
Space debris diameter
d
Impact below in conjunction with concrete each factor of case analysis on manipulation effect.In case analysis, get the plasma parameter in general cycle of solar activity in table 2.
The plasma characteristics of LEO track upper ionized layer under the general periodic condition of table 2 solar activity
| Parameter | Symbol | Numerical value |
| Orbit altitude | h | 320km |
| Electrons/ions density | 1×10 5cm -3 | |
| Electrons/ions temperature | About 1000K | |
| Electronics heating power speed | About 200km/s | |
| Ion heating power speed | 1.1km/s | |
| Orbital velocity | 7.7km/s |
Velocity angle
θto manipulation effect Δ
r p impact analysis
1) theoretical analysis
According to formula (17), suppose other parameter constants, only velocity angle
θas variable, space debris orbit altitude change amount Δ
r p there is periodic variation with the change of θ.Two ends are asked
θpartial derivative, and make it equal 0,
, can obtain
(18)
So, work as velocity angle
θwhile meeting above formula, Δ
r p get extreme value.
Easily know according to formula (7), on LEO track centimetre or grade space object, the velocity increment obtaining
generally much smaller than its track speed
v 0, there is following relation
Δ
v<<
na=
v 0 (19)
Now, requirement
(20)
So
, formula (18) can be reduced to
(21)
Solve, velocity angle
θ=153.4 ° or 333.4 °, now, Δ
r p get extreme value.This conclusion is significant in the time determining steer direction, can be for the direction of control capacitance plate in the improvement of Figure 17, and make the direction of its electric field line and the heading of fragment meet the best deceleration effect of formula (21)
.
2) case analysis
[case 1]if on the circular orbit of the space debris that diameter is 1cm in 320km height, table 3 is correlated inputs parameters.As calculated, velocity angle
θwith space debris orbit altitude change amount Δ
r p between relation as shown in figure 17.Can find out in the time that velocity angle is 155 ° of left and right, fall be about-280m of rail height maximum, now report control platform, in the best use of position, has best manipulation effect.This has also verified the conclusion of theoretical analysis above.
Table 3 case input parameter
| Orbit altitude/km | Space debris diameter/cm | Space debris migration potential is poor/V | Charging potential/V |
| 320 | 1 | -10 8 | -0.28 |
Δ
r p impact analysis
1) theoretical analysis
According to formula (17), suppose other parameter constants, only space debris surface charging suspended voltage
v fas variable, and formula (20) establishment, space debris orbit altitude change amount Δ
r p with
v frelation can be reduced to
(22)
, Δ
r p with
v fsquare root be approximated to direct ratio.
2) case analysis
Velocity angle is got 155 °, other parameters with
[case 1]unanimously, Figure 18 is space debris orbit altitude change amount Δ
r p with space debris surface charging suspended voltage
v fbetween relation.As can be seen from the figure be the space debris of 1cm magnitude for diameter, when space debris surface charging suspended voltage be-when 0.1V just can obtain-172m rail effect falls, when space debris surface charging suspended voltage be-when 1V can obtain-544m rail effect falls, and reach-10 at solar activity peak load conditions when space debris surface charging suspended voltage
3that when V, can obtain 17.2km falls rail effect.
The poor Δ of space debris migration potential
v pto manipulation effect Δ
r p impact analysis
1) theoretical analysis
With space debris surface charging suspended voltage
v fto manipulation effect Δ
r p impact similar, from formula (22), Δ
r p with the poor Δ of space debris migration potential
v psquare root be approximated to direct ratio.
2) case analysis
Velocity angle is got 155 °, other parameters with
[case 1]unanimously, Figure 19 is space debris orbit altitude change amount Δ
r p with the poor Δ of space debris migration potential
v pbetween relation.As can be seen from the figure be the space debris of 1cm magnitude for diameter, reach-10 when space debris migration potential is poor
5rail effect falls in can obtain when V magnitude-9m, reaches-10 when space debris migration potential is poor
6rail effect falls in can obtain when V-29m, reaches-10 when space debris migration potential is poor
7rail effect falls in can obtain when V-91m, reaches-10 when space debris migration potential is poor
8rail effect falls in can obtain when V-288m, reaches-10 when space debris migration potential is poor
9rail effect falls in can obtain when V-912m, reaches-10 when space debris migration potential is poor
10rail effect falls in can obtain when V-2885m.
Space debris diameter
dto manipulation effect Δ
r p impact analysis
1) theoretical analysis
According to formula (17), suppose other parameter constants, only space debris diameter
das variable, with space debris surface charging suspended voltage
v fto manipulation effect Δ
r p impact similar, from formula (22), Δ
r p with
dbe approximated to inverse ratio,
dless Δ
r p larger, that is to say that the less manipulation effect of space debris size is better.
2) case analysis
Velocity angle is got 155 °, other parameters with
[case 1]unanimously, Figure 20 is space debris orbit altitude change amount Δ
r p with space debris diameter
dbetween relation.As can be seen from the figure reach-10 when space debris migration potential is poor
8when V magnitude, rail effect falls in can obtain-29m of the space debris that is 10cm for diameter, rail effect falls in can obtain-288m of the space debris that is 1cm for diameter, rail effect falls in can obtain-2884m of the space debris that is 1mm for diameter, and rail effect falls in can obtain-28.8km of the space debris that is 0.1mm for diameter.
Situation while it is pointed out that above-mentioned case mainly for the general cycle of solar activity, if at solar activity peak load conditions, space debris surface charging suspended voltage
v f3 orders of magnitude that will approximately rise, and above-mentioned result of falling rail height also will improve 1 ~ 2 order of magnitude.
As shown in Fig. 6 to Figure 12, the utility model provides a kind of device 4 of removing space debris, comprises Piggybacking platform 41; Described Piggybacking platform 41 is provided with removes the electric field arrangement 42(of space debris referring to Fig. 6, Fig. 7 and Fig. 8) or magnetic field device 43(referring to Fig. 9 and Figure 10) or the combination (referring to Figure 11 and Figure 12) of electric field arrangement 42 and magnetic field device 43.
Improve as the one of the present embodiment, as shown in Fig. 6 to Figure 12, the electric field arrangement 42 of described removing space debris comprise two space certain distances, mutually in the face of and the netted capacitor board 421 that is parallel to each other; Described two netted capacitor boards 421 are connected (referring to Fig. 6, Fig. 7 and Fig. 8) with positive pole and the negative electricity of direct supply 44 respectively; The magnetic field device 43 of described removing space debris comprise two space certain distances, mutually in the face of and the tabular magnet 431 that is parallel to each other; Wherein, the S utmost point of a tabular magnet 431 and the N utmost point of another tabular magnet 431 are mutually in the face of (referring to Fig. 9 and Figure 10); The electric field arrangement 42 of described removing space debris and the combination of magnetic field device 43 are: described electric field arrangement 42 and described magnetic field device 43 phase juxtapositions, and two netted capacitor boards 421 of described electric field arrangement 42 are respectively perpendicular to two tabular magnet 431 of described magnetic field device 43; Electric wireline in described electric field arrangement 42 and the magnetic line of force in described magnetic field device 43 intersect vertical (referring to Figure 11); Or described electric field arrangement 42 and described magnetic field device 43 intersects to be put, two netted capacitor boards 421 of described electric field arrangement 42 are respectively perpendicular to two tabular magnet 431 of described magnetic field device 43; Electric wireline in described electric field arrangement 42 and magnetic line of force crossing vertical (referring to Figure 12) in described magnetic field device 43.As can be seen from Figure 6, two netted capacitor boards 421 are connected with Piggybacking platform 41 by mechanical support structure 5 respectively, between two netted capacitor boards 421, also can be connected to keep relative geometry position by insulator, the plate face size of two netted capacitor boards 421 can be the even thousands of sq ms of tens sq ms.The shape of two netted capacitor boards 421 can be that rectangle is square circular or oval.Mesh area on described netted capacitor board 421 can be 1 sq cm to 1 sq m.Equally, for being connected of magnetic field device 43 and Piggybacking platform 41, and the combination of electric field arrangement 42 and magnetic field device 43 can be connected with reference to said structure with being connected of Piggybacking platform 41.
Adopt netted capacitor board, can allow micro space debris 2 pass through smoothly and capacitor board not caused to damage; In the time meeting with large scale fragment, to hide, in order to avoid capacitor board or satellite body are damaged.
Further improve as present embodiment, as shown in Fig. 6 to Figure 10, described two netted capacitor boards 421 are connected (referring to Fig. 6, Fig. 7 and Fig. 8) with positive pole and the negative electricity of direct supply 44 respectively by electric field pulse device 45; " U " shape iron core 433 that two opposing faces of tabular magnet 431 in described magnetic field device 43 bend by inward at both ends is fixedly connected with; On described " U " shape iron core 433, be wound with coil 432; The two ends of described coil 432 are connected (referring to Fig. 9 and Figure 10) with positive pole and the negative electricity of described power supply 44 respectively; Described power supply 44 is solar cell or solar storage battery.
Further improve as present embodiment, as shown in figure 13, described electric field pulse device 45 comprises two aerotron Q1 and Q2; The first aerotron Q1 is positive-negative-positive aerotron, and the second aerotron Q2 is NPN type aerotron.The base stage of the first aerotron Q1 is electrically connected with the collecting electrode of the second aerotron Q2; Described the second base stage of aerotron Q2 and one end of resistance R and the first capacitor C 1(chemical capacitor) one end (positive pole) be electrically connected; Emitter, the second capacitor C 2(chemical capacitor of the other end of described resistance R and the first aerotron Q1) one end (positive pole) and the positive pole of power supply 44 be electrically connected; The other end (negative pole) of described the second capacitor C 2 is just electrically connected one end of polar curve circle with emitter and the step-up transformer L of the negative pole of power supply 44, the second aerotron Q2; The other end (negative pole) of described the first capacitor C 1 is electrically connected with the other end of the collecting electrode of the first aerotron Q1 and the first polar curve circle of step-up transformer L; The two ends of described step-up transformer L secondary coil are electrically connected with described two netted capacitor boards 421 respectively.
Also further improve as present embodiment, as shown in Fig. 6 to Figure 10 and Figure 14, the device 4 of described removing space debris is provided with controller 6 and space debris detection device 46; The signal output part of described space debris detection device 46 is electrically connected with the signal input part of described controller 6; Between described two netted capacitor boards 421, be electrically connected by short circuiting switch 47; The signal input part of described short circuiting switch 47 is electrically connected with the signal output part of described controller 6; Between described two netted capacitor boards 421 and described electric field pulse device 45, be electrically connected by the first electrode converting switch device 48, or, between described electric field pulse device 45 and power supply 44, be electrically connected (electric field pulse device 45 now can be switching pulse device) by the first electrode converting switch device 48; The signal input part of described the first electrode converting switch device 48 is electrically connected with the signal output part of described controller 6; Described two tabular magnet 431 and described " U " shape iron core 433 are made by soft iron or silicon steel material respectively; Described coil two ends are connected with positive pole and the negative electricity of direct supply 44 respectively by the second electrode converting switch device 49; The signal input part of described the second electrode converting switch device 49 is electrically connected with the signal output part of described controller 6.
As can be seen from Figure 7 the device of, removing space debris is with speed V
zconter clockwise moves around the earth's core, and the device of removing space debris has an electric field arrangement.Electronegative space debris is with speed V
0cw moves around the earth's core.In the time that space debris detection device detects space debris left side is sudden from figure, space debris detection device sends signal to controller.In the time that space debris flies into the netted capacitor board in left side in figure, controller sends control signal to the first electrode converting switch device.Under the effect of the first electrode converting switch device, in figure, the netted capacitor board in left side is with positive charge, and in figure, the netted capacitor board on right side is with negative charge, between two netted capacitor boards, form electric field, and under the effect of electric field pulse device, the electric field of formation is impulse electric field.Space debris speed under the effect of impulse electric field reduce and the figure that flies out in the netted capacitor board on right side.Now, controller sends control signal to the first electrode converting switch device, and the first electrode converting switch device is in off-state.Controller sends control signal to short circuiting switch, short circuiting switch closure, two netted capacitor board electric discharges.Controller sends control signal to short circuiting switch again, and short circuiting switch disconnects.Space debris after flying out is partial to the earth's core operation under gravitational effect, finally crashes into earth atmosphere under the effect of atmospherical drag.
As can be seen from Figure 8 the device of, removing space debris is with speed V
zconter clockwise moves around the earth's core, and the device of removing space debris has an electric field arrangement.Electronegative space debris is with speed V
0also conter clockwise moves around the earth's core.When space debris detection device detects space debris right side from figure when sudden, space debris detection device sends signal to controller.In the time that space debris flies into the netted capacitor board on right side in figure, controller sends control signal to the first electrode converting switch device.Under the effect of the first electrode converting switch device, in figure, the netted capacitor board on right side is with positive charge, and in figure, the netted capacitor board in left side is with negative charge, between two netted capacitor boards, form electric field, and under the effect of electric field pulse device, the electric field of formation is impulse electric field.Space debris speed under the effect of impulse electric field reduce and the figure that flies out in left side netted capacitor board.Now, controller sends control signal to the first electrode converting switch device, and the first electrode converting switch device is in off-state.Controller sends control signal to short circuiting switch, short circuiting switch closure, two netted capacitor board electric discharges.Controller sends control signal to short circuiting switch again, and short circuiting switch disconnects.Space debris after flying out is partial to the earth's core operation under gravitational effect, finally crashes into earth atmosphere under the effect of atmospherical drag.
As can be seen from Figure 9, the device of removing space debris has a magnetic field device.Electronegative space debris is with speed V
0in paper, to paper, fly out.In the time that space debris detection device detects space debris and flies out to paper in paper, space debris detection device sends signal to controller.In the time that space debris flies in figure between two tabular magnet, controller sends control signal to the second electrode converting switch device.Under the effect of the second electrode converting switch device, in figure, the tabular magnet in left side is the N utmost point, and in figure, the tabular magnet on right side is the S utmost point, between two tabular magnet, forms magnetic field.The direction of space debris speed under the effect in magnetic field flies out between two tabular magnet to the earth's core deflection and from figure.Now, controller sends control signal to the second electrode converting switch device, and the second electrode converting switch device is in off-state.Magnetic field between two tabular magnet disappears.Space debris after flying out is partial to the earth's core operation under gravitational effect, finally crashes into earth atmosphere under the effect of atmospherical drag.
As can be seen from Figure 10, the device of removing space debris has a magnetic field device.Electronegative space debris is with speed V
0in the export-oriented paper of paper, fly into.When space debris detection device detects space debris when flying in the export-oriented paper of paper, space debris detection device sends signal to controller.In the time that space debris flies in figure between two tabular magnet, controller sends control signal to the second electrode converting switch device.Under the effect of the second electrode converting switch device, in figure, the tabular magnet in left side is the S utmost point, and in figure, the tabular magnet on right side is the N utmost point, between two tabular magnet, forms magnetic field.The direction of space debris speed under the effect in magnetic field flies into paper to the earth's core deflection and from figure between two tabular magnet.Now, controller sends control signal to the second electrode converting switch device, and the second electrode converting switch device is in off-state.Magnetic field between two tabular magnet disappears.Space debris after flying out is partial to the earth's core operation under gravitational effect, finally crashes into earth atmosphere under the effect of atmospherical drag.
As can be seen from Figure 11, space debris can first be subject to the effect of electric field force to reduce speed in electric field arrangement, then in magnetic field device, magnetic field force induced effect changes the direction of speed, finally crashes into earth atmosphere under the effect of atmospherical drag.Certainly, the first direction of magnetic field force induced effect change speed in magnetic field device of space debris, then in electric field arrangement, be subject to the effect of electric field force to reduce speed, under the effect of atmospherical drag, finally crash into earth atmosphere.
As can be seen from Figure 12,, in space debris can be subject to the effect of electric field force to reduce speed in electric field arrangement, in magnetic field device, magnetic field force induced effect changes the direction of speed, finally crashes into earth atmosphere under the effect of atmospherical drag.
Claims (5)
1. a device of removing space debris, is characterized in that: comprise Piggybacking platform; Described Piggybacking platform is provided with removes the electric field arrangement of space debris or the combination of magnetic field device or electric field arrangement and magnetic field device.
2. the device of removing according to claim 1 space debris, is characterized in that: the electric field arrangement of described removing space debris comprise two space certain distances, mutually in the face of and the netted capacitor board that is parallel to each other; Described two netted capacitor boards are connected with positive pole and the negative electricity of direct supply respectively; The magnetic field device of described removing space debris comprise two space certain distances, mutually in the face of and the tabular magnet that is parallel to each other; Wherein, the S utmost point of a tabular magnet and the N utmost point of another tabular magnet are faced mutually; The electric field arrangement of described removing space debris and the combination of magnetic field device are: described electric field arrangement and described magnetic field device phase juxtaposition, be the outside that two tabular magnet of described magnetic field device are positioned at a netted capacitor board of described electric field arrangement, described two tabular magnet are parallel to each other and perpendicular to described netted capacitor board; Electric wireline in described electric field arrangement is vertical with the magnetic line of force in described magnetic field device; Or described electric field arrangement and described magnetic field device intersect to be put, i.e. two of described magnetic field device tabular magnet both sides between two netted capacitor boards of described electric field arrangement, described two netted capacitor boards are respectively perpendicular to described two tabular magnet; Electric wireline in described electric field arrangement is vertical with the magnetic line of force in described magnetic field device.
3. the device of removing according to claim 2 space debris, is characterized in that: described two netted capacitor boards are connected with positive pole and the negative electricity of direct supply respectively by electric field pulse device; " U " shape iron core that two opposing faces of tabular magnet in described magnetic field device bend by inward at both ends is fixedly connected with; On described " U " shape iron core, be wound with coil; The two ends of described coil are connected with positive pole and the negative electricity of described power supply respectively; Described power supply is solar cell or solar storage battery.
4. the device of removing according to claim 3 space debris, is characterized in that: described electric field pulse device comprises the first aerotron and the second aerotron; The base stage of the first aerotron is electrically connected with the collecting electrode of the second aerotron; The base stage of described the second aerotron is electrically connected with one end of one end of resistance and the first electric capacity; The other end of described resistance is electrically connected with emitter, one end of the second electric capacity and the positive pole of power supply of the first aerotron; The other end of described the second electric capacity is just electrically connected one end of polar curve circle with emitter and the step-up transformer of the negative pole of power supply, the second aerotron; The other end of described the first electric capacity is electrically connected with the collecting electrode of the first aerotron and the other end of the first polar curve circle of step-up transformer; The two ends of described step-up transformer secondary coil are electrically connected with described two netted capacitor boards respectively.
5. the device of removing according to claim 4 space debris, is characterized in that: the device of described removing space debris is provided with controller and space debris detection device; The signal output part of described space debris detection device is electrically connected with the signal input part of described controller; Between described two netted capacitor boards, be electrically connected by short circuiting switch; The signal input part of described short circuiting switch is electrically connected with the signal output part of described controller; Between described two netted capacitor boards and described electric field pulse device, be electrically connected by the first electrode converting switch device, or, between described electric field pulse device and power supply, be electrically connected by the first electrode converting switch device; Described first signal input part of electrode converting switch device and the signal output part of described controller are electrically connected; Described two tabular magnet and described " U " shape iron core are made by soft iron or silicon steel material respectively; Described coil two ends are connected with positive pole and the negative electricity of direct supply respectively by the second electrode converting switch device; Described second signal input part of electrode converting switch device and the signal output part of described controller are electrically connected.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103434658A (en) * | 2013-08-28 | 2013-12-11 | 李怡勇 | Method and device for cleaning space debris |
| CN106394940A (en) * | 2016-10-25 | 2017-02-15 | 杭州电子科技大学 | Space rope net capturing system based on recombining rope system formation flying |
| CN106809405A (en) * | 2017-01-09 | 2017-06-09 | 西北工业大学 | A kind of primary and secondary star space junk removes platform and sweep-out method |
-
2013
- 2013-08-28 CN CN201320528508.XU patent/CN203819503U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103434658A (en) * | 2013-08-28 | 2013-12-11 | 李怡勇 | Method and device for cleaning space debris |
| CN103434658B (en) * | 2013-08-28 | 2015-12-23 | 李怡勇 | A kind of method and apparatus removing space debris |
| CN106394940A (en) * | 2016-10-25 | 2017-02-15 | 杭州电子科技大学 | Space rope net capturing system based on recombining rope system formation flying |
| CN106809405A (en) * | 2017-01-09 | 2017-06-09 | 西北工业大学 | A kind of primary and secondary star space junk removes platform and sweep-out method |
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