CN109901232A - Generation method, storage medium and the system of space junk space-based optic observation task - Google Patents
Generation method, storage medium and the system of space junk space-based optic observation task Download PDFInfo
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Abstract
The invention discloses a kind of generation methods of space junk space-based optic observation task, comprising: obtains attitude maneuver angle and booting duration collection；The element for being unsatisfactory for observation star attitude maneuver restriction and environmental constraint is concentrated into deletion to attitude maneuver angle and booting duration；Constitute an element combinations collection；Objective function is consumed according to observation whole effect, task total time and total resources, the element combinations is obtained and observation whole effect, task total time corresponding to each element combinations and total resources is concentrated to consume；Summation is weighted to observation whole effect, task total time corresponding to each element combinations and total resources consumption, obtains the corresponding target value of each element combinations and using element combinations corresponding to maximum target value as the GEO fragment space-based optic observation task under posture collaboration.The invention also discloses a kind of storage medium and systems.The present invention fills up the blank of GEO fragment space-based optic observation mission planning.
Description
Technical field
The present invention relates to space-based optic observation technical fields, and in particular to a kind of space junk space-based optic observation task
Generation method, storage medium and system.
Background technique
As solar-system operation is increasingly frequent, space debris population is quicklyd increase, and is caused and is seriously threatened to space safety.?
Solution and grasp space junk can provide support for space situation awareness, space resources exploitation, in-orbit service etc..Space-based optics is seen
Survey means are in fragment observation because it is influenced small, observation scope is big, observes timeliness height, accuracy of observation height etc. by earth atmosphere
Advantage is at home and abroad widely used.
Mission planning model determines the reasonability of observation program.Existing spacecraft mission planning research is directed to mostly to be led
Navigate position location satellite, remote sensing satellite, over the ground reconnaissance satellite development, the correlative study of the mission planning of rarely found space-based fragment observation.
Summary of the invention
An object of the present invention is to provide a kind of generation method of GEO fragment space-based optic observation task, to fill up
The blank of GEO fragment space-based optic observation mission planning.
The second object of the present invention is to provide a kind of storage mediums.
The third object of the present invention is to provide a kind of generation systems of GEO fragment space-based optic observation task.
One of in order to achieve the above object, the present invention is realized using technical solution:
A kind of generation method of GEO fragment space-based optic observation task, the generation method include the following steps:
Obtaining observation star corresponding to each time point can observe that attitude maneuver angle and booting when each fragment are held
The continuous time, and then obtain attitude maneuver angle and booting duration collection；
It will be unsatisfactory for observing the element of star attitude maneuver restriction and environmental constraint from described to attitude maneuver angle
It concentrates and deletes with the booting duration, attitude maneuver angle and booting duration collection after being deleted；
Satisfaction observation star, which is found out, from the attitude maneuver angle after deletion and the duration concentration that is switched on observes a fragment every time
And all elements combine when meeting the constraint of the adjacent time interval of attitude maneuver twice, constitute an element combinations collection；
Objective function is consumed according to observation whole effect, task total time and total resources, the element combinations is obtained and concentrates often
Observation whole effect, task total time corresponding to a element combinations and total resources consumption；
Summation is weighted to observation whole effect, task total time corresponding to each element combinations and total resources consumption,
Obtain the corresponding target value of each element combinations and using element combinations corresponding to maximum target value as under posture collaboration
GEO fragment space-based optic observation task.
Further, each element of the attitude maneuver angle and booting duration collection includes available machine time, fragment, appearance
The motor-driven angle of state and booting duration.
Further, the observation star attitude maneuver restriction are as follows:
Wherein,WithRespectively i-th observes j-th of GEO fragment angle motor-driven along x, y and z axes；
θx_min、θy_minAnd θz_minRespectively lower limit of the observation star along the motor-driven angle of x, y and z axes；θx_max、θy_maxAnd θz_maxRespectively see
Star is surveyed along the upper limit of the motor-driven angle of x, y and z axes；θi,jThe synthesis posture adjustment angle, θ of j-th of GEO fragment is observed for i-thmaxTo see
Survey the synthesis posture adjustment angle upper limit of star.Further, the environmental constraint include SAA range constraint, gas light constraint, too
Sunlight constraint, moonlight constraint, angle of reflection constraint and the constraint of ground shadow.
Further, the observation whole effect is obtained using following formula:
Wherein, V is observation whole effect；VjFor the observation efficiency of j-th of GEO fragment；ηjAnd SNRjRespectively j-th of GEO is broken
The value and observation signal-to-noise ratio of piece；τ1For the value and the weight ratio of observation signal-to-noise ratio of fragment；WithRespectively
Observation frequency, the total arc length of observation and observation segmental arc total linear spacing in j-th of GEO fragment a cycle；τ2、τ3And τ4It Wei not fragment
Weight coefficient corresponding to observation frequency, the total arc length of observation and observation segmental arc total linear spacing in a cycle.
Further, the task total time is obtained using following formula:
Wherein, Δ T is task total time, and I is observation frequency；WithRespectively last time is seen
It surveys camera available machine time, observation camera booting duration and observes the camera available machine time for the first time.
Further, the wastage in bulk or weight resource is obtained using following formula:
Wherein, Δ E is wastage in bulk or weight resource；WithRespectively i-th observe j-th of GEO fragment when along x-axis,
Y-axis and the motor-driven angle of z-axis；Δeg_attFor the resource of every motor-driven 1 ° of consumption；
In order to achieve the above object two, the present invention is realized using technical solution:
A kind of storage medium, the storage medium are stored with computer program instructions, by executing the computer program
Instruction, realizes generation method described above.
In order to achieve the above object three, the present invention is realized using technical solution:
A kind of generation system of GEO (geostationary orbit) fragment space-based optic observation task, the generation system include
It obtains module, removing module, element combinations collection and constitutes module, objective function module and weighted sum module；
The acquisition module, when can observe each fragment for obtaining observation star corresponding to acquisition each time point
Attitude maneuver angle and the booting duration, and then obtain attitude maneuver angle and booting duration collection to the removing module；
The removing module will be unsatisfactory for the element of observation star attitude maneuver restriction and environmental constraint from described
Concentrate the attitude maneuver angle deleted, after being deleted and booting duration collection to institute at attitude maneuver angle and booting duration
It states element combinations collection and constitutes module；
The element combinations collection constitutes module, for concentrating and finding out from the attitude maneuver angle after deletion and the duration that is switched on
Meet all elements when observation star observes a fragment every time and meets the constraint of the adjacent time interval of attitude maneuver twice to combine, structure
The objective function module is given at an element combinations collection；
The objective function module is obtained for consuming objective function according to observation whole effect, task total time and total resources
Observation whole effect, task total time corresponding to each element combinations and total resources is concentrated to consume described add to the element combinations
Weigh summation module；
The weighted sum module, for observation whole effect, task total time corresponding to each element combinations and always
Resource consumption is weighted summation, obtains the corresponding target value of each element combinations and by element corresponding to maximum target value
It combines as the GEO fragment space-based optic observation task under posture collaboration.
Further, the observation star attitude maneuver restriction are as follows:
Wherein,WithRespectively i-th observes j-th of GEO fragment angle motor-driven along x, y and z axes；
θx_min、θy_minAnd θz_minRespectively lower limit of the observation star along the motor-driven angle of x, y and z axes；θx_max、θy_maxAnd θz_maxRespectively see
Star is surveyed along the upper limit of the motor-driven angle of x, y and z axes；θi,jThe synthesis posture adjustment angle, θ of j-th of GEO fragment is observed for i-thmaxTo see
Survey the synthesis posture adjustment angle upper limit of star；
The environmental constraint includes SAA range constraint, gas light constraint, sunlight constraint, moonlight constraint, angle of reflection
Constraint and ground shadow constraint.
Beneficial effects of the present invention:
1, the present invention considers a variety of constraints for influencing space-based optic observation, with observe efficiency is more excellent, task total time compared with
Short, less consumption resource is optimization aim, with the pose adjustment angle of the GEO fragment, observation star observed every time, observes camera
Available machine time and duration are decision variable, realize setting for the GEO fragment space-based optic observation task under posture collaboration
Meter.
2, the present invention considers observation active constraint, resource uses the constraints such as constraint, time window constraint and environmental constraints
Condition covers all constraints in need of consideration of GEO fragment space-based optic observation experimental design, more comprehensively substantially.
Detailed description of the invention
Fig. 1 is the generation method flow diagram of the GEO fragment space-based optic observation task under posture collaboration.
Specific embodiment
Further details of explanation and illustration is done to technical solution of the present invention below according to the drawings and specific embodiments.
The present embodiment is optimized according to objective function (including observation whole effect, task total time and total resources consume), i.e.,
Make observe whole effect it is more excellent, task total time is shorter and wastage in bulk or weight resource is less, in conjunction with constraint condition observe active constraint, resource
Using constraint, time window constraint and environmental constraints, decision variable is obtainedθi,jIndicate that i-th is seen
Star is observed when surveying j-th of GEO fragment needs to carry out posture motor-driven angle, includingWherein,For
The angle motor-driven along x-axis,For the angle motor-driven along y-axis,For the angle motor-driven along z-axis；With
The available machine time and booting duration of observation camera, as GEO fragment space-based when respectively i-th observes j-th of GEO fragment
Optical observation task, with reference to Fig. 1, which includes the following steps:
Step 1: the attitude maneuver angle that obtains observation star corresponding to each time point when can observe each fragment and
It is switched on the duration, and then obtains attitude maneuver angle and booting duration collection.
The attitude maneuver angle of the present embodiment and each element of booting duration collection include available machine time, fragment, posture
Motor-driven angle and booting duration.
Step 2: by being unsatisfactory for observing the element of star attitude maneuver restriction and environmental constraint from described to posture
Motor-driven angle and booting duration concentrate the attitude maneuver angle deleted, after being deleted and booting duration collection.
The observation star attitude maneuver restriction of the present embodiment are as follows:
Wherein,WithRespectively i-th observes j-th of GEO fragment angle motor-driven along x, y and z axes；
θx_min、θy_minAnd θz_minRespectively lower limit of the observation star along the motor-driven angle of x, y and z axes；θx_max、θy_maxAnd θz_maxRespectively see
Star is surveyed along the upper limit of the motor-driven angle of x, y and z axes；θi,jThe synthesis posture adjustment angle, θ of j-th of GEO fragment is observed for i-thmaxTo see
Survey the synthesis posture adjustment angle upper limit of star.
Under normal conditions, observation star simultaneously to three axis carry out it is motor-driven, if the group that motor-driven axis can be carried out be combined into X, Y,
Z, XZ, then:
The environmental constraint of the present embodiment include SAA range constraint, gas light constraint, sunlight constraint, moonlight constraint,
Angle of reflection constraint and ground shadow constraint.
1, SAA range constraint
The region SAA has a significant impact to instrument and observed result, camera is observed during executing observation mission, into SAA
It should be at shutdown off-position when region.That is:
Wherein,Substar warp, the latitude of observation star, { SAA when respectively i-th is observedareaBe
The region SAA.
2, gas light constrains
Substar earth's surface light conditions and camera off-axis angle have a significant impact to observed result, and Ying Jinliang is in substar earth's surface
Dark situation is carried out, and off-axis angle (angle that camera optical axis faces side with certain altitude atmosphere) should be greater than certain value.That is:
Wherein,Substar warp, the latitude of observation star when respectively i-th is observed,It is i-th
Camera off-axis angle, γ are observed when secondary observationminFor the minimal off-axis angle not influenced by veiling glare.
3, sunlight constrains
It need to fully consider the constraint condition of sunlight.That is:
Wherein,To observe the angle between camera optical axis and sunlight, α when i-th observationsun_minFor can not
By the angle between the sunlight the smallest observation camera optical axis influenced and the sun.
4, moonlight constrains
It need to fully consider the constraint condition of moonlight.That is:
Wherein,To observe the angle between camera optical axis and moonlight, α when i-th observationmoon_minFor can not
By the angle between the moonlight the smallest observation camera optical axis influenced and the moon.
5, angle of reflection constrains
Angle of reflection (angle between the sun-GEO fragment and GEO fragment-camera) is to observe the main of GEO fragment brightness to determine
Determine factor, with the operation of satellite, angle of reflection real-time change and variation range are very big (0 °~180 °), in experimental design, need
Fully consider the constraint condition of angle of reflection.That is:
Wherein,To observe angle of reflection of the star to j-th of GEO fragment, α when i-th observationecho_maxFor that can meet
Observe the maximum reflection angle of brightness requirement.
6, shadow constrains
Earth umbra, penumbra are affected to test, in experimental design, need to fully consider the constraint condition of ground shadow.
Wherein,For j-th of GEO crumb position, { umbra, penumbra } is earth umbra and penumbra region.
One is observed every time Step 3: concentrating from the attitude maneuver angle after deletion and the duration that is switched on and finding out satisfaction observation star
A fragment and meet the adjacent time interval of attitude maneuver twice constraint when all elements combine, constitute an element combinations collection.
The observation star of the present embodiment observes a fragment every time are as follows:S.t. attitude maneuver θi,jWhen, j-th of GEO
Fragment is able to enter viewing field of camera.
The pose adjustment ability for considering observation star, does following constraint to the adjacent time interval of attitude maneuver twice:
Wherein,WithRespectively i-th and i-1 times observation the observation camera available machine time, be approximately two
The time of secondary attitude maneuver, ta_minFor adjacent attitude maneuver minimum interval twice.
The pose adjustment ability for considering observation star, does following constraint to the attitude maneuver retention time:
Wherein,The booting duration that camera is observed when observing j-th of GEO fragment for i-th, is approximately posture
Motor-driven retention time, θi,jThe angle to attitude maneuver, t are needed when observing j-th of GEO fragment for i-thar_maxIndicate unit angle
Spend the maximum motor-driven retention time that can be supported.
Step 4: consuming objective function according to observation whole effect, task total time and total resources, the element combinations are obtained
Observation whole effect, task total time corresponding to each element combinations and total resources is concentrated to consume.
The present embodiment obtains observation whole effect using following formula:
Wherein, V is observation whole effect；VjFor the observation efficiency of j-th of GEO fragment；ηjAnd SNRjRespectively j-th of GEO is broken
The value and observation signal-to-noise ratio of piece；τ1For the value and the weight ratio of observation signal-to-noise ratio of fragment；WithPoint
It Wei not observation frequency, the total arc length of observation and observation segmental arc total linear spacing in j-th of GEO fragment a cycle；τ2、τ3And τ4It is not
Weight coefficient corresponding to observation frequency, the total arc length of observation and observation segmental arc total linear spacing in fragment a cycle.
Task total time is obtained using following formula:
Wherein, Δ T is task total time；I is observation frequency；WithRespectively last time is seen
It surveys camera available machine time, observation camera booting duration and observes the camera available machine time for the first time.
Total resources consumption is obtained using following formula:
Wherein, Δ E is total resources consumption；WithAlong x when respectively i-th observes j-th of GEO fragment
Axis, y-axis and the motor-driven angle of z-axis；Δeg_attFor the resource of every motor-driven 1 ° of consumption.
Step 5: adding to observation whole effect, task total time corresponding to each element combinations and total resources consumption
Power summation obtains the corresponding target value of each element combinations and assists element combinations corresponding to maximum target value as posture
GEO fragment space-based optic observation task under.
Weight corresponding to above-mentioned parameters is set according to weighting degree, observation efficiency is such as laid particular stress on, then corresponds to
Weight it is bigger than normal, conversely, then relatively small.
The present embodiment considers a variety of constraints for influencing space-based optic observation, with observe efficiency is more excellent, task total time compared with
Short, less consumption resource is optimization aim, with the pose adjustment angle of the GEO fragment, observation star observed every time, observes camera
Available machine time and duration are decision variable, realize setting for the GEO fragment space-based optic observation task under posture collaboration
Meter；Observation active constraint, resource are considered using constraint conditions such as constraint, time window constraint and environmental constraints, is covered substantially
GEO fragment space-based optic observation experimental design all constraints in need of consideration, more comprehensively.
Another embodiment gives a kind of storage medium, which is stored with computer program instructions, passes through execution
The computer program instructions realize the generation method that above-described embodiment provides.
Another embodiment gives a kind of generation system of GEO fragment space-based optic observation task, which includes
It obtains module, removing module, element combinations collection and constitutes module, objective function module and weighted sum module.Module is obtained, is used for
When the attitude maneuver angle and booting for observation star corresponding to each time point being obtained when can observe each fragment continue
Between, and then attitude maneuver angle and booting duration collection are obtained to removing module；Removing module will be unsatisfactory for observation star posture machine
The element of dynamic restriction and environmental constraint is deleted from described concentrate to attitude maneuver angle and booting duration, is deleted
Attitude maneuver angle and booting duration collection after removing constitute module to element combinations collection；Element combinations collection constitutes module, is used for
From after deletion attitude maneuver angle and the booting duration concentrate and find out satisfaction observation star and observe a fragment every time and meet phase
All elements combine when adjacent attitude maneuver time interval twice constrains, and constitute an element combinations collection and give objective function module.Mesh
Scalar functions module obtains the element combinations for consuming objective function according to observation whole effect, task total time and total resources
Observation whole effect, task total time corresponding to each element combinations and total resources is concentrated to consume weighted sum module；Weighting is asked
And module, for observation whole effect, task total time corresponding to each element combinations and total resources consumption to be weighted and are asked
With, obtain the corresponding target value of each element combinations and using element combinations corresponding to maximum target value as posture collaboration under
GEO fragment space-based optic observation task.The observation star attitude maneuver restriction of the present embodiment are as follows:
Wherein,WithRespectively i-th observes j-th of GEO fragment angle motor-driven along x, y and z axes；
θx_min、θy_minAnd θz_minRespectively lower limit of the observation star along the motor-driven angle of x, y and z axes；θx_max、θy_maxAnd θz_maxRespectively see
Star is surveyed along the upper limit of the motor-driven angle of x, y and z axes；θi,jThe synthesis posture adjustment angle, θ of j-th of GEO fragment is observed for i-thmaxTo see
Survey the synthesis posture adjustment angle upper limit of star.
Environmental constraint includes SAA range constraint, gas light constraint, sunlight constraint, moonlight constraint, angle of reflection constraint
It is constrained with ground shadow.
Examples detailed above is merely illustrative of the technical solution of the present invention rather than is limited, although referring to most preferred embodiment
Invention is explained in detail, those skilled in the art should understand that: it still can be to skill of the invention
Art scheme is modified or replaced equivalently, and these modifications or equivalent replacement cannot also be such that modified technical solution is detached from
The spirit and scope of technical solution of the present invention.
Claims (10)
1. a kind of generation method of space junk space-based optic observation task, which is characterized in that the generation method includes as follows
Step:
When observation star corresponding to acquisition each time point can observe that attitude maneuver angle and booting when each fragment continue
Between, and then obtain attitude maneuver angle and booting duration collection；
By the element for being unsatisfactory for observation star attitude maneuver restriction and environmental constraint from described to attitude maneuver angle and opening
The machine duration concentrates the attitude maneuver angle deleted, after being deleted and booting duration collection；
From after deletion attitude maneuver angle and the booting duration concentrate and find out satisfaction observation star and observe fragment and full every time
All elements combine when the foot adjacent time interval of attitude maneuver twice constraint, constitute an element combinations collection；
Objective function is consumed according to observation whole effect, task total time and total resources, the element combinations is obtained and concentrates each member
The corresponding observation whole effect of element combination, task total time and total resources consumption；
Summation is weighted to observation whole effect, task total time corresponding to each element combinations and total resources consumption, is obtained
The corresponding target value of each element combinations is simultaneously broken as the GEO under posture collaboration using element combinations corresponding to maximum target value
Piece space-based optic observation task.
2. generation method according to claim 1, which is characterized in that the attitude maneuver angle and the duration collection that is switched on
Each element includes available machine time, fragment, attitude maneuver angle and booting duration.
3. generation method according to claim 1, which is characterized in that the observation star attitude maneuver restriction are as follows:
Wherein,WithRespectively i-th observes j-th of GEO fragment angle motor-driven along x, y and z axes；θx_min、
θy_minAnd θz_minRespectively lower limit of the observation star along the motor-driven angle of x, y and z axes；θx_max、θy_maxAnd θz_maxRespectively observe star
Along the upper limit of the motor-driven angle of x, y and z axes；θi,jThe synthesis posture adjustment angle, θ of j-th of GEO fragment is observed for i-thmaxTo observe star
The synthesis posture adjustment angle upper limit.
4. generation method according to any one of claims 1 to 3, which is characterized in that the environmental constraint packet
Include SAA range constraint, gas light constraint, sunlight constraint, moonlight constraint, angle of reflection constraint and the constraint of ground shadow.
5. generation method according to any one of claims 1 to 3, which is characterized in that the observation whole effect uses
Following formula obtains:
Wherein, V is observation whole effect；VjFor the observation efficiency of j-th of GEO fragment；ηjAnd SNRjRespectively j-th GEO fragment
Value and observation signal-to-noise ratio；τ1For the value and the weight ratio of observation signal-to-noise ratio of fragment；WithRespectively
Observation frequency, the total arc length of observation and observation segmental arc total linear spacing in j-th of GEO fragment a cycle；τ2、τ3And τ4It Wei not fragment
Weight coefficient corresponding to observation frequency, the total arc length of observation and observation segmental arc total linear spacing in a cycle.
6. generation method according to any one of claims 1 to 3, which is characterized in that the task total time uses
Following formula obtains:
Wherein, Δ T is task total time；I is observation frequency；WithRespectively last time observation phase
Machine available machine time, observation camera booting duration and observation camera available machine time first time.
7. generation method according to any one of claims 1 to 3, which is characterized in that the wastage in bulk or weight resource uses
Following formula obtains:
Wherein, Δ E is wastage in bulk or weight resource；WithRespectively i-th observe j-th of GEO fragment when along x-axis, y-axis,
The motor-driven angle with z-axis；Δeg_attFor the resource of every motor-driven 1 ° of consumption.
8. a kind of storage medium, which is characterized in that the storage medium is stored with computer program instructions, by executing the meter
Calculation machine program instruction realizes generation method described in claim 1~7 any one.
9. a kind of generation system of space junk space-based optic observation task, which is characterized in that the generation system includes obtaining
Module, removing module, element combinations collection constitute module, objective function module and weighted sum module；
The acquisition module, appearance when can observe each fragment for obtaining observation star corresponding to acquisition each time point
The motor-driven angle of state and booting duration, and then attitude maneuver angle and booting duration collection are obtained to the removing module；
The removing module will be unsatisfactory for observing the element of star attitude maneuver restriction and environmental constraint from described to appearance
The motor-driven angle of state and booting duration concentrate the attitude maneuver angle deleted, after being deleted and booting duration collection to the member
Plain combination of sets constitutes module；
The element combinations collection constitutes module, for concentrating from the attitude maneuver angle after deletion and the duration that is switched on and finding out satisfaction
All elements combine when observation star observes a fragment every time and meets the constraint of the adjacent time interval of attitude maneuver twice, constitute one
A element combinations collection gives the objective function module；
The objective function module obtains institute for consuming objective function according to observation whole effect, task total time and total resources
Stating element combinations concentrates observation whole effect, task total time corresponding to each element combinations and the total resources consumption weighting to ask
And module；
The weighted sum module, for observation whole effect, task total time corresponding to each element combinations and total resources
Consumption is weighted summation, obtains the corresponding target value of each element combinations and by element combinations corresponding to maximum target value
As the GEO fragment space-based optic observation task under posture collaboration.
10. generation system according to claim 9, which is characterized in that the observation star attitude maneuver restriction are as follows:
Wherein,WithRespectively i-th observes j-th of GEO fragment angle motor-driven along x, y and z axes；θx_min、
θy_minAnd θz_minRespectively lower limit of the observation star along the motor-driven angle of x, y and z axes；θx_max、θy_maxAnd θz_maxRespectively observe star
Along the upper limit of the motor-driven angle of x, y and z axes；θi,jThe synthesis posture adjustment angle, θ of j-th of GEO fragment is observed for i-thmaxTo observe star
The synthesis posture adjustment angle upper limit；
The environmental constraint includes SAA range constraint, gas light constraint, sunlight constraint, moonlight constraint, angle of reflection constraint
It is constrained with ground shadow.
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| CN111368455A (en) * | 2020-03-18 | 2020-07-03 | 中国人民解放军战略支援部队航天工程大学 | Sun follow-up GEO target optical observation orbit and design method thereof |
| CN111368455B (en) * | 2020-03-18 | 2023-11-28 | 中国人民解放军战略支援部队航天工程大学 | Design method of solar follow-up GEO target optical observation orbit |
| CN111581309A (en) * | 2020-03-27 | 2020-08-25 | 中国科学院西安光学精密机械研究所 | Observation method for space debris in geosynchronous orbit zone |
| CN111581309B (en) * | 2020-03-27 | 2023-02-14 | 中国科学院西安光学精密机械研究所 | Observation method for space debris of geosynchronous orbit zone |
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