CN110510154A - A kind of earth magnetism accumulation of energy low earth orbital fragment, which leaves the right or normal track, delivers rail appearance coupling method of adjustment - Google Patents
A kind of earth magnetism accumulation of energy low earth orbital fragment, which leaves the right or normal track, delivers rail appearance coupling method of adjustment Download PDFInfo
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Abstract
It leaves the right or normal track the embodiment of the invention discloses a kind of earth magnetism accumulation of energy low earth orbital fragment and delivers rail appearance coupling method of adjustment, include the following steps: step 100, by entire earth magnetism accumulation of energy low orbit Periodic decomposition be cumulative segmental arc and release can segmental arc, and on three axis of spacecraft configure momenttum wheel energy absorption device；Step 200 determines cumulative segmental arc when spacecraft carries out accumulation of energy accumulation around orbital plane y-axis and orbital plane z-axis and release can segmental arc respectively；Step 300, after determining cumulative segmental arc, for the accumulation of energy target of different orbital coordinate system Y-axis or Z axis, the operation that leaves the right or normal track of space junk is completed based on earth magnetism accumulation of energy low earth orbital fragment Re-orbit control method；Step 400 is released and can be unloaded by the magnetic moment of generation to the momenttum wheel energy absorption device of three axis of spacecraft after segmental arc determining.
Description
Technical field
It leaves the right or normal track technical field the present embodiments relate to space junk, and in particular to a kind of earth magnetism accumulation of energy low earth orbital is broken
Piece, which leaves the right or normal track, delivers rail appearance coupling method of adjustment.
Background technique
The space trash of 10cm diameter can bring to spacecraft and astronaut and seriously threaten, Hubble Telescope,
Space shuttle and international space station are by the shock of space debris；Become increasingly active as mankind's space is movable and
The probability that Kessler effect space trash threatens quicklys increase, and (Kessler effect: due to the shock of space debris, leads
Cause the generation of more space debris).
The threat of space debris is further aggravated in Kessler effect, such as 2009, the discarded Comos satellite of Russia and
The Iridum satellite in the U.S. bumps against, and generates more than 2000 a space debris, if cannot active effective removing existing space fragment,
Space junk still can persistently be significantly increased, this will seriously affect the space development process of the mankind.
In-orbit at present nearly more than 20000 are greater than the space junk of 10cm, have nearly 70% to be distributed in 500km~1000km not
With on the LEO at inclination angle, these fragments in many decades as only by the atmospheric drag decaying orbit altitude of itself, all can not
Into earth atmosphere, rail space junk distribution low compared to geostationary orbit (36000km, track is unique, scarcity of resources)
It dissipates, have both high threat and low value feature more quantity, although can actively remove, remove the efficiency of low orbit space debris
It is but difficult to solve with economy problems.
The more excellent mode of space junk processing is the orbit altitude by artificially changing its operation, and by the near-earth of its track
Point height is reduced to 200km hereinafter, fragment is made to be influenced to be reduced rapidly semi-major axis of orbit and crashed into big by earth atmosphere resistance
Gas-bearing formation is burnt.
In the various methods proposed at present, it is the most mature that the method that leaves the right or normal track is pulled using the active of chemistry/electric thrust, but expend
It is high；The passive drop rail mode that air bag resistance sail/smearing foam etc. increases area-mass ratio is installed on fragment, is left the right or normal track although eliminating
Propulsive working medium consumption, but need to consume mounting material, and the time needed for fragment drop rail also counts in terms of year, this is undoubtedly significantly greatly increased
The probability of secondary collision.
In addition, the positive development in various countries is without working medium consumption-type defragmentation method, some methods while it is contemplated that very well, but
It is difficult to realize, for example clears up fragment using ground/space-based superlaser, the basic principle is that making to burn by superlaser calcination
It burning product and sharply expands away from fragment, fragment obtains recoil amount and drops rail, though this method has theoretical a possibility that realizing, such as
The problems such as what generates expected recoil amount, and how effective calcination and non-demolition generate new fragment group is difficult to solve, therefore mesh
Before be only used for remove 10cm speck body below.
Become rail in the method that leaves the right or normal track in no working medium consumption-type, electronic rope system is presently considered to be feasibility and realizability highest
A kind of mode, electronic rope system passes through the rope institute that is powered by the charged particle of collection space in the earth magnetic field in low rail space
The Ampere force being subject to carries out orbit adjusting, and only power consumption is consumed without working medium, and whether electronic rope system efficiency is dependent on rope
It is scale, the enormousness of thousands of rice to tens of kms makes rope system very prominent in spatial stability reliability of operation problem
Out.
Show to restrict system with comparable safety coefficient in spite of multiple theoretical researches and space test, but also has miserable
Dysmenorrhea is gone through, the SED-2 in the U.S. (emit within 1994, rope system expansion 19.7km) expansion of rope system only 4 days just by space junk/micrometeor
Cutting illustrates that the space safety problem of rope system is to be resolved, in this regard, the method to leave the right or normal track using earth magnetism accumulation of energy low earth orbital fragment
It solves, but when leaving rail using earth magnetism accumulation of energy progress space junk, inevitably introduces the magnetic torque in other directions,
It when the accumulation of additional magnetic torque is excessive, then needs specially to be unloaded, so that accumulation of energy-is released and can act duration and be interrupted.
Summary of the invention
It leaves the right or normal track for this purpose, the embodiment of the present invention provides a kind of earth magnetism accumulation of energy low earth orbital fragment and delivers rail appearance coupling adjustment side
Method, with solve in the prior art when additional magnetic torque accumulate it is excessive when, then need specially to be unloaded so that accumulation of energy-release it is active
The problem of being interrupted as duration.
To achieve the goals above, embodiments of the present invention provide the following technical solutions:
A kind of earth magnetism accumulation of energy low earth orbital fragment, which leaves the right or normal track, delivers rail appearance coupling method of adjustment, includes the following steps:
Entire earth magnetism accumulation of energy low orbit Periodic decomposition for cumulative segmental arc and is released energy segmental arc by step 100, and in spacecraft
Momenttum wheel energy absorption device is configured on three axis；
Step 200 determines cumulative segmental arc of the spacecraft around orbital plane y-axis and the progress accumulation of energy accumulation of orbital plane z-axis when respectively
It can segmental arc with releasing；
Step 300, after determining the cumulative segmental arc, for the accumulation of energy target of different orbital coordinate system Y-axis or Z axis,
The operation that leaves the right or normal track of space junk is completed based on earth magnetism accumulation of energy low earth orbital fragment Re-orbit control method；
Step 400, release described in the determination can be after segmental arc, to the momenttum wheel suction of three axis of spacecraft by way of generating magnetic moment
Energy device is unloaded.
As preferably scheme of the invention a kind of, the cumulative segmental arc of the spacecraft around orbital plane y-axis in the step 200
With it is described release can segmental arc it is symmetrical with 180 ° of ascending node angular distance u within an orbital period.
As a kind of preferably scheme of the invention, the energy segmental arc of releasing is near 0 °, 90 °, 180 °, 270 ° of ascending node angular distance
Symmetrical expansion, is set as Δ u0、Δuπ,The symmetrical angle of spread of four angles is corresponded respectively to away from value, it is clear that Δ u0=
Δuπ,
As a kind of preferably scheme of the invention, before the orbital period starts, measurement, which obtains, also remains in Space Vehicle System
Some determines under posture that the spinning momentum of three axis is respectively under respective carter coordinate systemAnd the rotation of three axis
The storage capacity of momentum is respectivelyAnd it is allocated.
Include the following steps: as one kind preferably scheme, method of the distribution of the invention
Step 211 generates magnetic moment size by international geomagnetic reference field IGRF geomagnetic model and spacecraft, uses following formula
Adjustable strategies carry out simulation calculation:
Wherein, Cmd_mx、Cmd_my、Cmd_mzIt indicates under geomagnetic coordinate system, the magnetic moment size that the expectation of all directions is adjusted
Component, | m | indicate producible total magnetic moment size,In-orbit in-flight for spacecraft, current time spacecraft substar is corresponding
Geographic latitude, u indicate spacecraft current flight ascending node angular distance；
In 0-90 ° of ascending node angular distance, 90 ° -180 °, 180 ° -270 °, 270 ° -360 ° any one quadrant areas, it is
Parabolic curve, therefore there are a value, in 0-90 ° of quadrant, the torque of orbital coordinate system Y-axis is in uaWithTwo points
It is upper equal, and the u in this sectionaAnd ubIt corresponds；
Step 212, in 0-90 ° of quadrant, for arbitrary uaU corresponding with itsb, calculate in ascending node angular distance from uaIt arrivesCumulant on inherent orbital coordinate system X and Z axis
Step 213 judges whetherAnd simultaneously K is
Default conservative coefficient, and 0.5 < k < 0.95；
If be not able to satisfy, u is adjustedaAnd ub, so that the condition meets；
Step 214, when the conditions are met exports uaAnd ub, then Δ u0=ua,Thus the orbital period is obtained
Interior, releasing energy segmental arc isRemaining is accumulation of energy segmental arc.
As a kind of preferably scheme of the invention, in the accumulation of energy segmental arc, if the X-axis rotation of having deposited at current time is moved
AmountZ axis spinning momentum is depositedOccur OrIt is then transferred to immediately and releases energy segmental arc, and measure current ascending node angular distance unow, judge unowPlace
Quadrant, and substitute ub, while u is updated according to calculated valuea, so that changing and update accumulation of energy segmental arc in the orbital period/release can segmental arc
Range.
As preferably scheme of the invention a kind of, the cumulative segmental arc of the spacecraft around orbital plane Z axis in the step 200
Energy segmental arc is released within an orbital period using ascending node angular distance as standard asymmetric distribution with described.
As a kind of preferably scheme of the invention, before the orbital period starts, measurement, which obtains, remains in Space Vehicle System
Certain determines under posture that three axis spinning momentums under respective carter coordinate system are respectivelyAnd the rotation of three axis
The storage capacity of momentum is respectivelyThen it is allocated according to following sub-step:
Step 221, primary condition are accumulation of energy segmental arc, use the adjustable strategies of following formula:
Wherein, Cmd_mx、Cmd_my、Cmd_mzIt indicates under geomagnetic coordinate system, the magnetic moment size that the expectation of all directions is adjusted
Component, | m | indicate producible total magnetic moment size；
Measurement current time has deposited X-axis spinning momentumY-axis spinning momentum is depositedOccurOrIt is then transferred to immediately and releases energy segmental arc
Step 222, release can segmental arc continue toAnd simultaneously Wherein
τ is to preset to deposit energy coefficient, general 0.05 < τ < 0.3.
Embodiments of the present invention have the advantages that
The present invention is by setting accumulation of energy segmental arc and releases energy segmental arc, so that the additional force as caused by the complexity of earth magnetism distribution
Square accumulation can discharge in time, while the earth magnetism characteristic distributions that are utilized of also maximal efficiency complete high efficiency energy storage, so that low orbit
The efficiency and economy problems of space debris be improved significantly.
Detailed description of the invention
It, below will be to embodiment party in order to illustrate more clearly of embodiments of the present invention or technical solution in the prior art
Formula or attached drawing needed to be used in the description of the prior art are briefly described.It should be evident that the accompanying drawings in the following description is only
It is merely exemplary, it for those of ordinary skill in the art, without creative efforts, can also basis
The attached drawing of offer, which is extended, obtains other implementation attached drawings.
Fig. 1 is the flow chart for the space junk Re-orbit control method that the embodiment of the present invention 1 provides；
Fig. 2 is the schematic diagram at the orbital flight inclination angle of the embodiment of the present invention 1.
Fig. 3 is magnetic torque and accumulation under the orbital coordinate system under the embodiment of the present invention 2 uses formula (1) and formula (3) tactful
Magnetic torque schematic diagram；
Fig. 4 is calculating accumulation magnetic torque of the embodiment of the present invention 2 using formula (4) strategy under different geomagnetic models；
Fig. 5 is the flow chart for delivering rail appearance coupling method of adjustment that the embodiment of the present invention 2 provides；
Specific embodiment
Embodiments of the present invention are illustrated by particular specific embodiment below, those skilled in the art can be by this explanation
Content disclosed by book is understood other advantages and efficacy of the present invention easily, it is clear that described embodiment is the present invention one
Section Example, instead of all the embodiments.Based on the embodiments of the present invention, those of ordinary skill in the art are not doing
Every other embodiment obtained under the premise of creative work out, shall fall within the protection scope of the present invention.
Embodiment 1:
As depicted in figs. 1 and 2, the present invention provides a kind of earth magnetism accumulation of energy low earth orbital fragment Re-orbit control methods, lead to
It crosses spacecraft crawl space junk and carries out earth magnetism accumulation of energy, the earth magnetism accumulation of energy includes the following steps:
Step 10, the orbital flight inclination angle according to the spacecraft, determine accumulation of energy direction；
When the orbital flight inclination angle of spacecraft is greater than set angle, accumulation of energy accumulation is carried out around orbital plane y-axis；
When orbital flight inclination angle is less than set angle, accumulation of energy accumulation is carried out around orbital plane z-axis.
Wherein, accumulation of energy accumulation in the present embodiment, refer specifically to it is lasting accelerated in a preset direction, need to hold
Continuous generates magnetic torque in preset direction, as time goes by, so that the speed in the direction is continuously increased.
According to traversal 100-1000km orbit altitude, under different orbit inclination angles, stored using two different modes
The efficiency calculation that can be accumulated, comparison efficiencies obtain the separation at its inclination angle on optimized angle, and set angle is preferably
49.14°。
The current flight attitude of step 20, the measurement spacecraft, parameter include the height h of spacecraft, orbit inclination angle,
The component in earth's magnetic field of the geographic logitude and latitude, spacecraft current location of spacecraft substar under geomagnetic coordinate system
The magnetic moment for being connected in spaceborne quadrature coil is generated direction, magnetic by the flight attitude for adjusting the spacecraft
The accumulative rotation of square is associated with away from direction with the flight attitude of spacecraft, and keeps the flight attitude after association；
Wherein, the generation of magnetic moment is realized with the electric current for being connected in spaceborne quadrature coil generation, with spacecraft
Posture it is unrelated, it is being instantaneously an orthogonality relation that the torque direction for generating magnetic moment and accumulation is not also identical.
Associated process is it is to be understood that spacecraft may require that an attitude angle when executing specific tasks, in order in spy
Fixed orbital plane generates specific accumulating rate, needs the direction by the delivery mechanism being connected with spacecraft to be aligned, in addition strong magnetic
Square generating means (quadrature coil) and spacecraft are connected, the resolving strategy that strong magnetic moment generates again and earth magnetism field distribution strong correlation, because
This needs to carry out prepackage adjustment according to spacecraft attitude, and three above needs are determined relativeness before delivery.
Step 30 generates strong magnetic momentFor vector；
When carrying out accumulation of energy accumulation around orbital plane Y-axis, magnetic momentThe strategy such as following formula of generation:
When carrying out accumulation of energy accumulation around orbital plane Z axis, magnetic momentThe tactful following formula of generation:
Wherein, Cmd_mx、Cmd_my、Cmd_mzIt indicates under geomagnetic coordinate system, the magnetic moment size that the expectation of all directions is adjusted
Component, | m | indicate producible total magnetic moment size,In-orbit in-flight for spacecraft, current time spacecraft substar is corresponding
Geographic latitude, u indicate spacecraft current flight ascending node angular distance；
Step 40, the lasting angular motion magnitude and the spacecraft for accelerating rotation to be crawled fragment end and to detect its accumulation
The relative linear velocity Δ V for being crawled fragment end, calculate present combination body flying speed V and relative linear velocity Δ V difference V-
Whether Δ V meets the requirement that leaves the right or normal track；
Step 50, when difference V- Δ V satisfaction leave the right or normal track require when, then choose described in be crawled it is described opposite after the rotation of fragment end
The direction of linear velocity Δ V is parallel with the direction of assembly flying speed V, and at the time of contrary, discharge be crawled it is broken
Piece completes momentum-exchange；If conditions are not met, thening follow the steps 30.
Wherein, momentum-exchange is that the Rotary kinetic energy of system is converted to translation energy, and space junk or target obtain offtrack relocity
Increment leaves existing track and burns into atmosphere.
The embodiment of the present invention 1 using magnet in terrestrial space magnetic field by the torque of turn, (such as compass works as magnetic
When the direction of body and size obtain actively effective control, then can constantly accelerate turn), it is broken that space has been grabbed in spacecraft
When piece or target, by constantly accelerating rotation to be crawled fragment end, so that the space junk being crawled rotates with, unclamping
Moment, system Rotary kinetic energy is converted to translation energy, and space junk or target obtain offtrack relocity increment, leave existing track simultaneously
Into atmosphere.
The embodiment of the present invention 1 can leave the right or normal track and become without the in-orbit delivery of working medium consumption-type, low cost rail, without consuming working medium meaning
Taste can long-term in-orbit flight and development task, the space junk/target for implementing big quantity leaves the right or normal track operation, so that low orbit
The efficiency and economy problems of space debris be improved significantly.
The embodiment of the present invention 1 also has the advantages that in flexible face/face outside deliver, and fragment leave the right or normal track it is anti-used dynamic
Amount can be used for delivering the vehicle out-driving without working medium consumption of primary.The controllability of this method is high, deliver ability to system scale according to
Rely property low, also with the energy in earth's magnetic field, but the requirement to scale is few, so that the controllability implemented improves, what is be subject to is outer
The probability that portion threatens then is effectively reduced.
Embodiment 2:
For the embodiment of the present invention 1, further, the basic representation for the rotating torque that magnet receives in magnetic field
Are as follows:
L=m × B (4)
In the formula (4), L is magnetic force moment vector, and m is the magnetic moment vector that spacecraft carries, and B is the magnetic strength in terrestrial space magnetic field
Answer strength vector.
Such as: it is within an orbital period, while carrying out accumulation of energy accumulation around orbital coordinate system Y-axis, around X in lower Fig. 3
Axis, Y-axis, the magnetic torque of Z axis and magnetic torque cumulant, the left, center, right of Fig. 3 respectively indicate X-axis, Y-axis, Z axis magnetic torque, Fig. 3
Left, center, right respectively indicate X-axis, Y-axis, the magnetic torque cumulant of Z axis.
Theoretically, it can only be accumulated in Y-axis, it is dip-dip line in corresponding diagram that other, which are 0, but when actual conditions, is used
Formula (1), corresponding is dip-IGRF line, and using formula (3), corresponding is IGRF-IGRF line, in addition to having magnetic around Y-axis desired
Torque accumulation is outer, the magnetic torque accumulation of different depths also occurs in other two axis.
As shown in figure 4, within an orbital period, while carrying out accumulation of energy accumulation about the z axis, around X-axis, Y-axis, Z axis magnetic
Torque cumulant, theoretically dipole line, X-axis, Y-axis accumulation are almost 0, and actual conditions are IGRF lines, are had obvious tired
Product.
In this regard, solving the problems, such as the accumulation of the magnetic torque in other directions using rail appearance coupling method of adjustment is delivered.
Rail appearance coupling method of adjustment is delivered as shown in figure 5, providing a kind of earth magnetism accumulation of energy low earth orbital fragment and leaving the right or normal track, including
Following steps:
Entire earth magnetism accumulation of energy low orbit Periodic decomposition for cumulative segmental arc and is released energy segmental arc by step 100, and in spacecraft
Momenttum wheel energy absorption device is configured on three axis；
Step 200 determines cumulative segmental arc of the spacecraft around orbital plane y-axis and the progress accumulation of energy accumulation of orbital plane z-axis when respectively
It can segmental arc with releasing；
In the first aspect of the step 200, spacecraft can segmental arc around the cumulative segmental arc of orbital plane y-axis and described release
It is symmetrical with 180 ° of ascending node angular distance u within an orbital period；
The energy segmental arc of releasing is set as Δ u in 0 ° of ascending node angular distance, 90 °, 180 °, 270 ° of symmetrical expansion nearby0、Δ
uπ,The symmetrical angle of spread of four angles is corresponded respectively to away from value, it is clear that Δ u0=Δ uπ,
Before the orbital period starts, measurement, which obtains, also to be remained under some determination posture of Space Vehicle System, and respective carter is sat
Mark system under three axis spinning momentums be respectivelyAnd the storage capacity of the spinning momentum of three axis is respectivelyAnd it is allocated, including following sub-step:
Step 211 generates magnetic moment size by international geomagnetic reference field IGRF geomagnetic model and spacecraft, uses following formula
Adjustable strategies carry out simulation calculation:
Wherein, Cmd_mx、Cmd_my、Cmd_mzIt indicates under geomagnetic coordinate system, the magnetic moment size that the expectation of all directions is adjusted
Component, | m | indicate producible total magnetic moment size,In-orbit in-flight for spacecraft, current time spacecraft substar is corresponding
Geographic latitude, u indicate spacecraft current flight ascending node angular distance；
In 0-90 ° of ascending node angular distance, 90 ° -180 °, 180 ° -270 °, 270 ° -360 ° any one quadrant areas, it is
Parabolic curve, therefore there are a value, in 0-90 ° of quadrant, the torque of orbital coordinate system Y-axis is in uaWithTwo points
It is upper equal, and the u in this sectionaAnd ubIt corresponds；
Step 212, in 0-90 ° of quadrant, for arbitrary uaU corresponding with itsb, calculate in ascending node angular distance from uaIt arrivesCumulant on inherent orbital coordinate system X and Z axis
Step 213 judges whetherAnd simultaneously K is
Default conservative coefficient, and 0.5 < k < 0.95；
If be not able to satisfy, u is adjustedaAnd ub, so that the condition meets.
Step 214, when the conditions are met exports uaAnd ub, then Δ u0=ua,Thus the orbital period is obtained
Interior, releasing energy segmental arc isRemaining is accumulation of energy segmental arc；
In the accumulation of energy segmental arc, if current time has deposited X-axis spinning momentumIt is dynamic Z axis rotation has been deposited
AmountOccurOrIt is then transferred to immediately and releases energy segmental arc, and
Measure current ascending node angular distance unow, judge unowThe quadrant at place, and substitute ub, while u is updated according to calculated valuea, to change
Become and update accumulation of energy segmental arc in the orbital period/release can segmental arc range；
In the second aspect of the step 200, spacecraft can segmental arc around the cumulative segmental arc of orbital plane Z axis and described release
Using ascending node angular distance as standard asymmetric distribution within an orbital period；
Before the orbital period starts, measurement, which obtains, to be remained under certain determination posture of Space Vehicle System, respective carter coordinate
System under three axis spinning momentums be respectivelyAnd the storage capacity of the spinning momentum of three axis is respectivelyThen it is allocated according to following sub-step:
Step 221, primary condition are accumulation of energy segmental arc, use the adjustable strategies of following formula:
Wherein, Cmd_mx、Cmd_my、Cmd_mzIt indicates under geomagnetic coordinate system, the magnetic moment size that the expectation of all directions is adjusted
Component, | m | indicate producible total magnetic moment size；
Measurement current time has deposited X-axis spinning momentumY-axis spinning momentum is depositedOccurOrIt is then transferred to immediately and releases energy segmental arc；
Step 222, release can segmental arc continue toAnd simultaneously Its
Middle τ is to preset to deposit energy coefficient, general 0.05 < τ < 0.3.
Step 300, after determining the cumulative segmental arc, for the accumulation of energy target of different orbital coordinate system Y-axis or Z axis,
The operation that leaves the right or normal track of space junk is completed based on earth magnetism accumulation of energy low earth orbital fragment Re-orbit control method.
Step 400 is released described in the determination and can be filled by the magnetic moment of generation to the momenttum wheel energy-absorbing of three axis of spacecraft after segmental arc
It sets and is unloaded.
The present embodiment is by setting accumulation of energy segmental arc and releases energy segmental arc, so that being added as caused by the complexity of earth magnetism distribution
Torque accumulation can discharge in time, while the earth magnetism characteristic distributions that are utilized of also maximal efficiency complete high efficiency energy storage, so that low rail
The efficiency and economy problems of road space debris be improved significantly.
Although above having used general explanation and specific embodiment, the present invention is described in detail, at this
On the basis of invention, it can be made some modifications or improvements, this will be apparent to those skilled in the art.Therefore,
These modifications or improvements without departing from theon the basis of the spirit of the present invention are fallen within the scope of the claimed invention.
Claims (8)
1. a kind of earth magnetism accumulation of energy low earth orbital fragment, which leaves the right or normal track, delivers rail appearance coupling method of adjustment, which is characterized in that including as follows
Step:
Entire earth magnetism accumulation of energy low orbit Periodic decomposition for cumulative segmental arc and is released energy segmental arc by step 100, and in three axis of spacecraft
Upper configuration momenttum wheel energy absorption device；
Step 200 determines cumulative segmental arc when spacecraft carries out accumulation of energy accumulation around orbital plane y-axis and orbital plane z-axis respectively and releases
It can segmental arc；
Step 300, after determining the cumulative segmental arc, for the accumulation of energy target of different orbital coordinate system Y-axis or Z axis, be based on
The operation that leaves the right or normal track of earth magnetism accumulation of energy low earth orbital fragment Re-orbit control method completion space junk；
Step 400, release described in the determination can be after segmental arc, to the momenttum wheel energy-absorbing dress of three axis of spacecraft by way of generating magnetic moment
It sets and is unloaded.
2. a kind of earth magnetism accumulation of energy low earth orbital fragment according to claim 1, which leaves the right or normal track, delivers rail appearance coupling method of adjustment,
It is characterized in that, spacecraft is around the cumulative segmental arc of orbital plane y-axis and the energy segmental arc of releasing in a rail in the step 200
It is symmetrical with 180 ° of ascending node angular distance u in the road period.
3. a kind of earth magnetism accumulation of energy low earth orbital fragment according to claim 1 or 2, which leaves the right or normal track, delivers rail appearance coupling adjustment side
Method, which is characterized in that the energy segmental arc of releasing is set as Δ u in 0 ° of ascending node angular distance, 90 °, 180 °, 270 ° of symmetrical expansion nearby0、Δuπ,The symmetrical angle of spread of four angles is corresponded respectively to away from value, it is clear that Δ u0=Δ uπ,
4. a kind of earth magnetism accumulation of energy low earth orbital fragment according to claim 3, which leaves the right or normal track, delivers rail appearance coupling method of adjustment,
It is characterized in that, measurement, which obtains, also to be remained under some determination posture of Space Vehicle System, respective carter before the orbital period starts
The spinning momentum of three axis is respectively under coordinate systemAnd the storage capacity of the spinning momentum of three axis is respectivelyAnd it is allocated.
5. a kind of earth magnetism accumulation of energy low earth orbital fragment according to claim 4, which leaves the right or normal track, delivers rail appearance coupling method of adjustment,
It is characterized in that, the method for the distribution includes the following steps:
Step 211 generates magnetic moment size by international geomagnetic reference field IGRF geomagnetic model and spacecraft, uses the adjustment of following formula
Strategy carries out simulation calculation:
Wherein, Cmd_mx、Cmd_my、Cmd_mzIt indicates under geomagnetic coordinate system, the magnetic moment size point that the expectation of all directions is adjusted
Amount, | m | indicate producible total magnetic moment size,In-orbit in-flight for spacecraft, current time spacecraft substar is corresponding
Geographic latitude, u indicate the ascending node angular distance of spacecraft current flight；
It is parabolic in 0-90 ° of ascending node angular distance, 90 ° -180 °, 180 ° -270 °, 270 ° -360 ° any one quadrant areas
Line curve, therefore there are a value, in 0-90 ° of quadrant, the torque of orbital coordinate system Y-axis is in uaWith 90 ° of-ubPhase on two points
Deng, and the u in this sectionaAnd ubIt corresponds；
Step 212, in 0-90 ° of quadrant, for arbitrary uaU corresponding with itsb, calculate in ascending node angular distance from uaTo 90 ° of-ub
Cumulant on inherent orbital coordinate system X and Z axis
Step 213 judges whetherAnd simultaneously K is default
Conservative coefficient, and 0.5 < k < 0.95；
If be not able to satisfy, u is adjustedaAnd ub, so that the condition meets.
Step 214, when the conditions are met exports uaAnd ub, then Δ u0=ua,Thus it obtains in the orbital period, releases energy
Segmental arc isRemaining is accumulation of energy segmental arc.
6. a kind of earth magnetism accumulation of energy low earth orbital fragment according to claim 5, which leaves the right or normal track, delivers rail appearance coupling method of adjustment,
It is characterized in that, in the accumulation of energy segmental arc, if current time has deposited X-axis spinning momentumZ axis rotation is deposited
MomentumOccur OrIt is then transferred to immediately and releases energy segmental arc,
And measure current ascending node angular distance unow, judge unowThe quadrant at place, and substitute ub, while u is updated according to calculated valuea, thus
Change and update accumulation of energy segmental arc in the orbital period/release can segmental arc range.
7. a kind of earth magnetism accumulation of energy low earth orbital fragment according to claim 1, which leaves the right or normal track, delivers rail appearance coupling method of adjustment,
It is characterized in that, spacecraft is around the cumulative segmental arc of orbital plane Z axis and the energy segmental arc of releasing in a rail in the step 200
Using ascending node angular distance as asymmetric distribution in the road period.
8. a kind of earth magnetism accumulation of energy low earth orbital fragment according to claim 7, which leaves the right or normal track, delivers rail appearance coupling method of adjustment,
It is characterized in that, measurement, which obtains, to be remained under certain determination posture of Space Vehicle System, and respective carter is sat before the orbital period starts
Mark is that the spinning momentum of lower three axis is respectively And the storage capacity of the spinning momentum of three axis is respectivelyThen it is allocated according to following sub-step:
Step 221, primary condition are accumulation of energy segmental arc, use the adjustable strategies of following formula:
Wherein, Cmd_mx、Cmd_my、Cmd_mzIt indicates under geomagnetic coordinate system, the magnetic moment size point that the expectation of all directions is adjusted
Amount, | m | indicate producible total magnetic moment size；
Measurement current time has deposited X-axis spinning momentumY-axis spinning momentum is depositedOccurOrIt is then transferred to immediately and releases energy segmental arc；
Step 222, release can segmental arc continue toAnd simultaneously Wherein τ is
It is default to deposit energy coefficient, general 0.05 < τ < 0.3.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111114852A (en) * | 2019-12-09 | 2020-05-08 | 上海航天控制技术研究所 | Space rolling target four-dimensional perception capturing device and method |
| CN113075592A (en) * | 2021-03-12 | 2021-07-06 | 中国科学院力学研究所 | Coaxial contra-rotating geomagnetic energy storage and release delivery ground experiment system and method |
Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3681583A (en) * | 1968-09-27 | 1972-08-01 | Tokyo Shibaura Electric Co | Device for controlling the attitude of a space satellite utilizing geomagnetic field |
| US4114841A (en) * | 1977-02-22 | 1978-09-19 | Rca Corporation | Magnetic torquing system for changing the spin rate of an orbiting satellite |
| US4489383A (en) * | 1981-10-16 | 1984-12-18 | Rca Corporation | Closed-loop magnetic roll/yaw control system for high inclination orbit satellites |
| US6942186B1 (en) * | 2001-03-07 | 2005-09-13 | Star Technology And Research, Inc. | Method and apparatus for propulsion and power generation using spinning electrodynamic tethers |
| CN101767657A (en) * | 2009-12-30 | 2010-07-07 | 哈尔滨工业大学 | Electro-dynamic tether based satellite deorbit device and method thereof |
| GB201012958D0 (en) * | 2010-08-02 | 2010-09-15 | Lockheed Martin Uk Insys Ltd | Apparatus, method and system |
| WO2011068193A1 (en) * | 2009-12-04 | 2011-06-09 | 株式会社Ihi | Method for clearing space debris |
| CN105966643A (en) * | 2016-05-20 | 2016-09-28 | 中国西安卫星测控中心 | Space debris low-cost removal method by using ground-based electromagnetic launcher |
| EP3156335A1 (en) * | 2014-06-13 | 2017-04-19 | Japan Aerospace Exploration Agency | Method and system for space debris orbit descent, and method and system for changing orbit of artificial satellite |
| CN107719708A (en) * | 2017-09-27 | 2018-02-23 | 西北工业大学深圳研究院 | A kind of capture of space junk and remove device and its method |
| CN109250158A (en) * | 2018-08-02 | 2019-01-22 | 西北工业大学 | Integrated apparatus and method are arrested in space faulty target racemization based on Multi free flying space robots |
| CN109799835A (en) * | 2019-01-17 | 2019-05-24 | 北京理工大学 | A kind of optimal method that leaves the right or normal track of rope system towing of space junk |
| CN109969433A (en) * | 2019-04-01 | 2019-07-05 | 中国人民解放军国防科技大学 | Space debris batch removing system based on low-earth orbit satellite |
-
2019
- 2019-08-21 CN CN201910774236.3A patent/CN110510154B/en active Active
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3681583A (en) * | 1968-09-27 | 1972-08-01 | Tokyo Shibaura Electric Co | Device for controlling the attitude of a space satellite utilizing geomagnetic field |
| US4114841A (en) * | 1977-02-22 | 1978-09-19 | Rca Corporation | Magnetic torquing system for changing the spin rate of an orbiting satellite |
| US4489383A (en) * | 1981-10-16 | 1984-12-18 | Rca Corporation | Closed-loop magnetic roll/yaw control system for high inclination orbit satellites |
| US6942186B1 (en) * | 2001-03-07 | 2005-09-13 | Star Technology And Research, Inc. | Method and apparatus for propulsion and power generation using spinning electrodynamic tethers |
| WO2011068193A1 (en) * | 2009-12-04 | 2011-06-09 | 株式会社Ihi | Method for clearing space debris |
| CN101767657A (en) * | 2009-12-30 | 2010-07-07 | 哈尔滨工业大学 | Electro-dynamic tether based satellite deorbit device and method thereof |
| GB201012958D0 (en) * | 2010-08-02 | 2010-09-15 | Lockheed Martin Uk Insys Ltd | Apparatus, method and system |
| EP3156335A1 (en) * | 2014-06-13 | 2017-04-19 | Japan Aerospace Exploration Agency | Method and system for space debris orbit descent, and method and system for changing orbit of artificial satellite |
| CN105966643A (en) * | 2016-05-20 | 2016-09-28 | 中国西安卫星测控中心 | Space debris low-cost removal method by using ground-based electromagnetic launcher |
| CN107719708A (en) * | 2017-09-27 | 2018-02-23 | 西北工业大学深圳研究院 | A kind of capture of space junk and remove device and its method |
| CN109250158A (en) * | 2018-08-02 | 2019-01-22 | 西北工业大学 | Integrated apparatus and method are arrested in space faulty target racemization based on Multi free flying space robots |
| CN109799835A (en) * | 2019-01-17 | 2019-05-24 | 北京理工大学 | A kind of optimal method that leaves the right or normal track of rope system towing of space junk |
| CN109969433A (en) * | 2019-04-01 | 2019-07-05 | 中国人民解放军国防科技大学 | Space debris batch removing system based on low-earth orbit satellite |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111114852A (en) * | 2019-12-09 | 2020-05-08 | 上海航天控制技术研究所 | Space rolling target four-dimensional perception capturing device and method |
| CN111114852B (en) * | 2019-12-09 | 2021-04-23 | 上海航天控制技术研究所 | Space rolling target four-dimensional perception capturing device and method |
| CN113075592A (en) * | 2021-03-12 | 2021-07-06 | 中国科学院力学研究所 | Coaxial contra-rotating geomagnetic energy storage and release delivery ground experiment system and method |
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|---|---|
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