CN109901232B - Space debris space-based optical observation task generation method, storage medium and system - Google Patents
Space debris space-based optical observation task generation method, storage medium and system Download PDFInfo
- Publication number
- CN109901232B CN109901232B CN201811649815.7A CN201811649815A CN109901232B CN 109901232 B CN109901232 B CN 109901232B CN 201811649815 A CN201811649815 A CN 201811649815A CN 109901232 B CN109901232 B CN 109901232B
- Authority
- CN
- China
- Prior art keywords
- observation
- total
- time
- fragment
- attitude
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Landscapes
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
- Studio Devices (AREA)
Abstract
The invention discloses a method for generating a space debris space-based optical observation task, which comprises the following steps: obtaining an attitude maneuvering angle and a starting duration set; elements which do not meet the observation star attitude maneuver restriction constraint and the environmental constraint condition are intensively deleted from the attitude maneuver angle and the starting duration; forming an element combination set; obtaining the total observation efficiency, the total task time and the total resource consumption corresponding to each element combination in the element combination set according to the total observation efficiency, the total task time and the total resource consumption objective function; and carrying out weighted summation on the total observation efficiency, the total task time and the total resource consumption corresponding to each element combination to obtain a target value corresponding to each element combination, and taking the element combination corresponding to the maximum target value as the GEO fragment space-based optical observation task under attitude coordination. The invention also discloses a storage medium and a system. The method fills the blank of GEO fragment space-based optical observation task planning.
Description
Technical Field
The invention relates to the technical field of space-based optical observation, in particular to a method, a storage medium and a system for generating a space debris space-based optical observation task.
Background
With the increasing frequency of space activities, the number of space fragments is rapidly increased, and the space safety is seriously threatened. Understanding and mastering the space debris can provide support for space situation awareness, space resource development, on-orbit service and the like. The space-based optical observation means is widely applied at home and abroad in debris observation due to the advantages of small influence of earth atmosphere, large observation range, high observation timeliness, high observation precision and the like.
The mission planning model determines the rationality of the observation scenario. Most of the existing spacecraft task planning research is carried out on navigation positioning satellites, remote sensing satellites and ground reconnaissance satellites, and the related research of the task planning of space-based debris observation is rare.
Disclosure of Invention
One of the purposes of the present invention is to provide a method for generating a GEO-fragment space-based optical observation task, so as to fill up the blank of GEO-fragment space-based optical observation task planning.
It is a second object of the present invention to provide a storage medium.
The third object of the present invention is to provide a system for generating GEO-fragmented space-based optical observation tasks.
In order to achieve one of the purposes, the invention adopts the technical scheme to realize that:
a method for generating a GEO fragment space-based optical observation task comprises the following steps:
acquiring a gesture dynamic angle and a starting duration time when the observation star corresponding to each time point can observe each fragment, and further acquiring a gesture dynamic angle and a starting duration time set;
deleting elements which do not meet the observation star attitude maneuver restriction constraint and the environmental constraint condition from the pair of attitude maneuver angles and the starting duration set to obtain a deleted attitude maneuver angle and starting duration set;
finding out all element combinations which meet the condition that the observation star observes one fragment each time and meets the condition that the time interval of two adjacent attitude maneuvers is constrained from the deleted attitude maneuvering angle and the startup duration set to form an element combination set;
obtaining the total observation efficiency, the total task time and the total resource consumption corresponding to each element combination in the element combination set according to the total observation efficiency, the total task time and the total resource consumption objective function;
and carrying out weighted summation on the total observation efficiency, the total task time and the total resource consumption corresponding to each element combination to obtain a target value corresponding to each element combination, and taking the element combination corresponding to the maximum target value as the GEO fragment space-based optical observation task under attitude coordination.
Further, each element of the gestural maneuver angle and boot duration set includes a boot time, a fragment, a gestural maneuver angle, and a boot duration.
Further, the observation star attitude maneuver restriction constraint is:
wherein the content of the first and second substances,
and
the maneuvering angles of the jth GEO fragment along the x axis, the y axis and the z axis are respectively observed for the ith time; thetax_min、θy_minAnd thetaz_minRespectively the lower limits of maneuvering angles of the observation star along the x, y and z axes; thetax_max、θy_maxAnd thetaz_maxThe upper limits of maneuvering angles of the observation star along the x axis, the y axis and the z axis respectively; thetai,jFor the ith observation of the synthetic attitude-adjusting angle theta of the jth GEO fragmentmaxIs the upper limit of the synthetic attitude adjusting angle of the observation star. Further, the environmental constraints include SAA area constraints, ground-atmosphere light constraints, sunlight constraints, moonlight constraints, reflection angle constraints, and ground shadow constraints.
Further, the observed total efficiency is obtained by using the following formula:
wherein V is the observed total potency; vjis the observed efficiency of the jth GEO fragment etajAnd SNRjThe value and the observed signal-to-noise ratio of the jth GEO fragment are respectively; tau is1The weight ratio of the value of the fragment to the observed signal-to-noise ratio;
and
respectively the observation times, the total observation arc length and the total observation interval of the jth GEO fragment in one period; tau is2、τ3And τ4Respectively the number of observations in one period of the fragments,And observing the weight coefficients corresponding to the total arc length and the total interval of the arc sections.
Further, the total task time is obtained by the following formula:
wherein, the delta T is the total time of the task, and the I is the observation frequency;
and
the last observation camera boot time, the observation camera boot duration, and the first observation camera boot time, respectively.
Further, the total consumed resources are obtained by using the following formula:
wherein, Delta E is total consumption resource;
and
the motorized angles along the x axis, the y axis and the z axis are respectively used for observing the jth GEO fragment for the ith time; Δ eg_attResources consumed for 1 ° per maneuver;
in order to achieve the second purpose, the invention adopts the technical scheme to realize that:
a storage medium storing computer program instructions which, when executed, implement the generation method described above.
In order to achieve the third purpose, the invention adopts the technical scheme to realize that:
a generating system of a GEO (geostationary orbit) fragment space-based optical observation task comprises an acquisition module, a deletion module, an element combination set forming module, an objective function module and a weighted summation module;
the acquisition module is used for acquiring the attitude dynamic angle and the starting duration time when the observation satellite corresponding to each time point can observe each fragment, and further acquiring an attitude dynamic angle and a starting duration time set which are sent to the deletion module;
the deleting module is used for deleting the elements which do not meet the observation star attitude maneuver restriction constraint and the environmental constraint condition from the pair of attitude maneuver angles and the starting duration in a centralized manner to obtain a deleted attitude maneuver angle and starting duration set which is sent to the element combination set forming module;
the element combination set forming module is used for finding out all element combinations which meet the condition that an observation star observes one fragment each time and meets the condition that the time interval of two adjacent attitude maneuvers is constrained from the deleted attitude maneuver angle and the deleted startup duration set to form an element combination set to the objective function module;
the objective function module is used for obtaining the weighted summation module of the total observation efficiency, the total task time and the total resource consumption corresponding to each element combination in the element combination set according to the objective function of the total observation efficiency, the total task time and the total resource consumption;
and the weighted summation module is used for carrying out weighted summation on the total observation efficiency, the total task time and the total resource consumption corresponding to each element combination to obtain a target value corresponding to each element combination and taking the element combination corresponding to the maximum target value as the GEO fragment space-based optical observation task under the posture coordination.
Further, the observation star attitude maneuver restriction constraint is:
wherein the content of the first and second substances,
and
the maneuvering angles of the jth GEO fragment along the x axis, the y axis and the z axis are respectively observed for the ith time; thetax_min、θy_minAnd thetaz_minRespectively the lower limits of maneuvering angles of the observation star along the x, y and z axes; thetax_max、θy_maxAnd thetaz_maxThe upper limits of maneuvering angles of the observation star along the x axis, the y axis and the z axis respectively; thetai,jFor the ith observation of the synthetic attitude-adjusting angle theta of the jth GEO fragmentmaxThe upper limit of the synthetic attitude adjusting angle of the observation star;
the environmental constraints include SAA area constraints, ground gas light constraints, sunlight constraints, moonlight constraints, reflection angle constraints, and ground shadow constraints.
The invention has the beneficial effects that:
1. the invention considers various constraints influencing the space-based optical observation, takes the optimization goals of better observation efficiency, shorter total task time and less resource consumption, and takes GEO fragments observed each time, the attitude adjustment angle of an observation star, the starting time and the duration of an observation camera as decision variables, thereby realizing the design of the GEO fragment space-based optical observation task under the attitude coordination.
2. The invention considers the constraint conditions of observation activity constraint, resource use constraint, time window constraint, environment constraint and the like, basically covers all the constraints needing to be considered in the design of the GEO fragment space-based optical observation test, and is relatively comprehensive.
Drawings
Fig. 1 is a schematic flow chart of a method for generating a GEO-fragment space-based optical observation task under posture coordination.
Detailed Description
The technical solution of the present invention is explained and explained in further detail below with reference to the accompanying drawings and the detailed description.
The embodiment is optimized according to the objective function (including the total observed efficiency, the total task time and the total resource consumption), namely, the activity constraint and the resource use constraint are observed in combination with the constraint conditions, namely, the total observed efficiency is better, the total task time is shorter and the total consumed resources are lessTime window constraint and environment constraint to obtain decision variables
θi,jThe angle for observing that the star needs to maneuver the attitude when the ith observation is carried out on the jth GEO fragment is shown, comprising
Wherein the content of the first and second substances,
for the motorized angle along the x-axis,
for the angle maneuvered along the y-axis,
is motorized angle along the z-axis;
and
referring to fig. 1, the generation method includes the following steps:
step one, acquiring the attitude dynamic angle and the starting duration when the observation satellite corresponding to each time point can observe each fragment, and further acquiring an attitude dynamic angle and a starting duration set.
Each element of the gestural maneuver angle and boot duration set of the present embodiment includes boot time, fragments, gestural maneuver angle, and boot duration.
And step two, deleting the elements which do not meet the observation star attitude maneuver restriction constraint and the environmental constraint condition from the pair of attitude maneuver angles and the startup duration set to obtain the deleted attitude maneuver angle and startup duration set.
The constraint of the attitude maneuver limit of the observation satellite in the embodiment is as follows:
wherein the content of the first and second substances,
and
the maneuvering angles of the jth GEO fragment along the x axis, the y axis and the z axis are respectively observed for the ith time; thetax_min、θy_minAnd thetaz_minRespectively the lower limits of maneuvering angles of the observation star along the x, y and z axes; thetax_max、θy_maxAnd thetaz_maxThe upper limits of maneuvering angles of the observation star along the x axis, the y axis and the z axis respectively; thetai,jFor the ith observation of the synthetic attitude-adjusting angle theta of the jth GEO fragmentmaxIs the upper limit of the synthetic attitude adjusting angle of the observation star.
In general, the observation stars do not maneuver the three axes simultaneously, and if the combination of axes capable of maneuvering is X, Y, Z, XZ, then:
the environmental constraints of the present embodiment include SAA area constraint, earth-atmosphere light constraint, sunlight constraint, moonlight constraint, reflection angle constraint, and ground shadow constraint.
1. SAA region constraints
The SAA area has great influence on instruments and observation results, and an observation camera is in a power-off state when entering the SAA area during the observation task. Namely:
wherein the content of the first and second substances,
are respectively asSum-satellite Point-meridian, latitude of the Observation Star at the ith observation { SAAareaIs the SAA area.
2. Restriction of earth gas light
The illumination condition of the earth surface of the satellite points and the off-axis angle of the camera have great influence on the observation result, the observation result should be developed under the condition that the earth surface of the satellite points is dark as much as possible, and the off-axis angle (the included angle between the optical axis of the camera and the adjacent edge of the atmosphere with a certain height) should be larger than a certain value. Namely:
wherein the content of the first and second substances,
respectively the sub-satellite meridian and latitude of the observation star at the ith observation,
for the i-th observation, the off-axis angle, gamma, of the cameraminIs the minimum off-axis angle unaffected by stray light.
3. Solar light confinement
The constraint conditions of sunlight need to be fully considered. Namely:
wherein the content of the first and second substances,
is an angle alpha between the optical axis of the observation camera and the sunlight during the ith observationsun_minThe angle between the optical axis of the observation camera and the sun is the smallest angle that can be unaffected by sunlight.
4. Confinement of moonlight
The constraints of the moonlight need to be fully considered. Namely:
wherein the content of the first and second substances,
is the angle between the optical axis of the observation camera and the moonlight at the ith observation, αmoon_minThe angle between the optical axis of the observation camera and the moon is the smallest possible angle that is not affected by the moon.
5. Angle of reflection constraint
The reflection angle (the included angle between the sun-GEO fragments and the GEO fragments-a camera) is a main determining factor for observing the brightness of the GEO fragments, the reflection angle changes in real time along with the operation of a satellite and has a large change range (0-180 degrees), and the constraint condition of the reflection angle needs to be fully considered during experimental design. Namely:
wherein the content of the first and second substances,
for the reflection angle, alpha, of the observation star for the jth GEO fragment at the ith observationecho_maxThe maximum reflection angle that can meet the brightness requirement of observation.
6. Ground shadow constraint
The earth's ghost and penumbra have a great influence on the test, and the constraint conditions of the earth's ghost need to be fully considered in the test design.
Wherein the content of the first and second substances,
for the jth GEO fragment position, { umbra, penumbra } are the ghost and penumbra regions of the earth.
And step three, finding out all element combinations which meet the condition that the observation star observes one fragment each time and meets the condition that the adjacent two attitude maneuver time intervals are constrained from the deleted attitude maneuver angles and the deleted startup duration time set to form an element combination set.
Observation of the present embodimentOne fragment per observation of the star is:
s.t. attitude maneuver θi,jThen the jth GEO fragment can enter the camera field of view.
Considering the attitude adjustment capability of the observation star, the following constraints are made on the time interval of two adjacent attitude maneuvers:
wherein the content of the first and second substances,
and
the starting time of the observation camera for the i-th observation and the i-1-th observation is approximate to the time of two attitude maneuvers, ta_minThe minimum time interval is formed by two adjacent attitude maneuvers.
Considering the attitude adjustment capability of the observation star, the attitude maneuver holding time is constrained as follows:
wherein the content of the first and second substances,
observing the startup duration of the camera for the ith observation of the jth GEO fragment, approximately the attitude maneuver holding time, θi,jAngle, t, required to maneuver attitude for ith observation of jth GEO fragmentar_maxRepresenting the maximum maneuver hold time that can be supported per angle.
And step four, obtaining the total observation efficiency, the total task time and the total resource consumption corresponding to each element combination in the element combination set according to the total observation efficiency, the total task time and the total resource consumption objective function.
The present embodiment obtains the observed total efficiency by using the following formula:
wherein V is the observed total potency; vjis the observed efficiency of the jth GEO fragment etajAnd SNRjThe value and the observed signal-to-noise ratio of the jth GEO fragment are respectively; tau is1The weight ratio of the value of the fragment to the observed signal-to-noise ratio;
and
respectively the observation times, the total observation arc length and the total observation interval of the jth GEO fragment in one period; tau is2、τ3And τ4The weight coefficients corresponding to the observation times, the total observation arc length and the total observation arc interval in one period of the fragments are respectively.
The total time of the task is obtained by adopting the following formula:
wherein, the delta T is the total time of the task; i is the observation frequency;
and
the last observation camera boot time, the observation camera boot duration, and the first observation camera boot time, respectively.
The total resource consumption is obtained by adopting the following formula:
wherein, Δ E is the total resource consumption;
and
the motorized angles along the x axis, the y axis and the z axis are respectively used for observing the jth GEO fragment for the ith time; Δ eg_attThe resources consumed for 1 ° per maneuver.
And fifthly, carrying out weighted summation on the total observation efficiency, the total task time and the total resource consumption corresponding to each element combination to obtain a target value corresponding to each element combination, and taking the element combination corresponding to the maximum target value as the GEO fragment space-based optical observation task under the posture coordination.
And setting the weight corresponding to each parameter according to the weight bias degree, wherein if the weight bias observation efficiency is high, the corresponding weight is high, otherwise, the corresponding weight is low.
In the embodiment, multiple constraints influencing the space-based optical observation are considered, the optimization target is that the observation efficiency is better, the total time of the task is shorter, and the consumed resources are less, and the design of the space-based optical observation task of the GEO fragments under the posture coordination is realized by taking the GEO fragments observed each time, the posture adjustment angle of the observation star, and the starting time and the duration of the observation camera as decision variables; constraint conditions such as observation activity constraint, resource use constraint, time window constraint and environment constraint are considered, all constraints needing to be considered in design of the GEO fragment space-based optical observation test are basically covered, and the method is comprehensive.
Another embodiment provides a storage medium storing computer program instructions, which, by executing the computer program instructions, implement the generation method provided by the above-described embodiment.
Yet another embodiment provides a generating system of a GEO-fragment space-based optical observation task, which comprises an obtaining module, a deleting module, an element combination set forming module, an objective function module and a weighted summation module. The acquisition module is used for acquiring the attitude dynamic angle and the starting duration when the observation satellite corresponding to each time point can observe each fragment, and further acquiring an attitude dynamic angle and a starting duration set which are sent to the deletion module; the deleting module is used for deleting the elements which do not meet the observation star attitude maneuver restriction constraint and the environmental constraint condition from the pair of attitude maneuver angles and the starting duration in a centralized manner to obtain a deleted attitude maneuver angle and starting duration set which is given to the element combination set forming module; and the element combination set forming module is used for finding out all element combinations which meet the condition that the observation star observes one fragment every time and meets the adjacent two times of attitude maneuver time interval constraint from the deleted attitude maneuver angle and the deleted boot duration time set, and forming an element combination set to the objective function module. The objective function module is used for obtaining an observation total efficiency, a task total time and a total resource consumption weighted summation module corresponding to each element combination in the element combination set according to the observation total efficiency, the task total time and the total resource consumption objective function; and the weighted summation module is used for carrying out weighted summation on the total observation efficiency, the total task time and the total resource consumption corresponding to each element combination to obtain a target value corresponding to each element combination and taking the element combination corresponding to the maximum target value as the GEO fragment space-based optical observation task under the posture coordination. The constraint of the attitude maneuver limit of the observation satellite in the embodiment is as follows:
wherein the content of the first and second substances,
and
the maneuvering angles of the jth GEO fragment along the x axis, the y axis and the z axis are respectively observed for the ith time; thetax_min、θy_minAnd thetaz_minRespectively the lower limits of maneuvering angles of the observation star along the x, y and z axes; thetax_max、θy_maxAnd thetaz_maxRespectively is an observation starAn upper limit of the motorized angle along the x, y, and z axes; thetai,jFor the ith observation of the synthetic attitude-adjusting angle theta of the jth GEO fragmentmaxIs the upper limit of the synthetic attitude adjusting angle of the observation star.
The environmental constraints include SAA area constraints, ground gas light constraints, sunlight constraints, moonlight constraints, reflection angle constraints, and ground shadow constraints.
The above examples are intended only to illustrate the technical solution of the present invention and not to limit it, and although the present invention has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that: modifications and equivalents may be made to the invention without departing from the spirit and scope of the invention.
Claims (10)
1. A generation method of space debris space-based optical observation tasks is characterized by comprising the following steps:
acquiring a gesture dynamic angle and a starting duration time when the observation star corresponding to each time point can observe each fragment, and further acquiring a gesture dynamic angle and a starting duration time set;
deleting elements which do not meet the observation star attitude maneuver restriction constraint and the environmental constraint condition from the attitude maneuver angle and the starting duration set to obtain a deleted attitude maneuver angle and starting duration set;
finding out all element combinations which meet the condition that the observation star observes one fragment each time and meets the condition that the time interval of two adjacent attitude maneuvers is constrained from the deleted attitude maneuvering angle and the startup duration set to form an element combination set;
obtaining the total observation efficiency, the total task time and the total resource consumption corresponding to each element combination in the element combination set according to the total observation efficiency, the total task time and the total resource consumption objective function;
and carrying out weighted summation on the total observation efficiency, the total task time and the total resource consumption corresponding to each element combination to obtain a target value corresponding to each element combination, and taking the element combination corresponding to the maximum target value as the GEO fragment space-based optical observation task under attitude coordination.
2. The generation method of claim 1, wherein each element of the gestural motor angle and start-up duration set includes a start-up time, a fragment, a gestural motor angle, and a start-up duration.
3. The generation method of claim 1, wherein the observation star pose maneuver limit constraint is:
wherein the content of the first and second substances,
and
the maneuvering angles of the jth GEO fragment along the x axis, the y axis and the z axis are respectively observed for the ith time; thetax_min、θy_minAnd thetaz_minRespectively the lower limits of maneuvering angles of the observation star along the x, y and z axes; thetax_max、θy_maxAnd thetaz_maxThe upper limits of maneuvering angles of the observation star along the x axis, the y axis and the z axis respectively; thetai,jFor the ith observation of the synthetic attitude-adjusting angle theta of the jth GEO fragmentmaxIs the upper limit of the synthetic attitude adjusting angle of the observation star.
4. The generation method according to any one of claims 1 to 3, wherein the environmental constraint conditions include an SAA area constraint, a terrestrial gas light constraint, a solar light constraint, a moonlight constraint, a reflection angle constraint, and a terrestrial shadow constraint.
5. The generation method according to any one of claims 1 to 3, wherein the observed total performance is obtained by using the following formula:
wherein V is the observed total potency; vjis the observed efficiency of the jth GEO fragment etajAnd SNRjThe value and the observed signal-to-noise ratio of the jth GEO fragment are respectively; tau is1The weight ratio of the value of the fragment to the observed signal-to-noise ratio;
and
respectively the observation times, the total observation arc length and the total observation interval of the jth GEO fragment in one period; tau is2、τ3And τ4The weight coefficients corresponding to the observation times, the total observation arc length and the total observation arc interval in one period of the fragments are respectively.
6. The generation method according to any one of claims 1 to 3, wherein the total task time is obtained by using the following formula:
wherein, the delta T is the total time of the task; i is the observation frequency;
and
the last observation camera boot time, the observation camera boot duration, and the first observation camera boot time, respectively.
7. The generation method according to any one of claims 1 to 3, wherein the total resource consumption is obtained by using the following formula:
wherein, Δ E is the total resource consumption;
and
the motorized angles along the x axis, the y axis and the z axis are respectively used for observing the jth GEO fragment for the ith time; Δ eg_attThe resources consumed for 1 ° per maneuver.
8. A storage medium storing computer program instructions for executing the generation method according to any one of claims 1 to 7.
9. A generation system of space debris space-based optical observation tasks is characterized by comprising an acquisition module, a deletion module, an element combination set forming module, a target function module and a weighted summation module;
the acquisition module is used for acquiring the attitude dynamic angle and the starting duration time when the observation satellite corresponding to each time point can observe each fragment, and further acquiring an attitude dynamic angle and a starting duration time set which are sent to the deletion module;
the deleting module is used for deleting elements which do not meet the observation star attitude maneuver restriction constraint and the environmental restriction condition from the attitude maneuver angle and the starting duration in a centralized manner to obtain a deleted attitude maneuver angle and starting duration set which is sent to the element combination set forming module;
the element combination set forming module is used for finding out all element combinations which meet the condition that an observation star observes one fragment each time and meets the condition that the time interval of two adjacent attitude maneuvers is constrained from the deleted attitude maneuver angle and the deleted startup duration set to form an element combination set to the objective function module;
the objective function module is used for obtaining the weighted summation module of the total observation efficiency, the total task time and the total resource consumption corresponding to each element combination in the element combination set according to the objective function of the total observation efficiency, the total task time and the total resource consumption;
and the weighted summation module is used for carrying out weighted summation on the total observation efficiency, the total task time and the total resource consumption corresponding to each element combination to obtain a target value corresponding to each element combination and taking the element combination corresponding to the maximum target value as the GEO fragment space-based optical observation task under the posture coordination.
10. The generation system of claim 9, wherein the observation star pose maneuver limit constraint is:
wherein the content of the first and second substances,
and
the maneuvering angles of the jth GEO fragment along the x axis, the y axis and the z axis are respectively observed for the ith time; thetax_min、θy_minAnd thetaz_minRespectively the lower limits of maneuvering angles of the observation star along the x, y and z axes; thetax_max、θy_maxAnd thetaz_maxThe upper limits of maneuvering angles of the observation star along the x axis, the y axis and the z axis respectively; thetai,jFor the ith observation of the synthetic attitude-adjusting angle theta of the jth GEO fragmentmaxThe upper limit of the synthetic attitude adjusting angle of the observation star;
the environmental constraints include SAA area constraints, ground gas light constraints, sunlight constraints, moonlight constraints, reflection angle constraints, and ground shadow constraints.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811649815.7A CN109901232B (en) | 2018-12-30 | 2018-12-30 | Space debris space-based optical observation task generation method, storage medium and system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811649815.7A CN109901232B (en) | 2018-12-30 | 2018-12-30 | Space debris space-based optical observation task generation method, storage medium and system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109901232A CN109901232A (en) | 2019-06-18 |
| CN109901232B true CN109901232B (en) | 2020-05-19 |
Family
ID=66943553
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811649815.7A Active CN109901232B (en) | 2018-12-30 | 2018-12-30 | Space debris space-based optical observation task generation method, storage medium and system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109901232B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103675938A (en) * | 2013-11-29 | 2014-03-26 | 北京空间机电研究所 | Full-airspace-coverage dual-mode integrated space-based space debris detection system |
| CN103983250A (en) * | 2014-05-19 | 2014-08-13 | 上海微小卫星工程中心 | Space target space-based imaging method and space target space-based imaging device |
| CN104570319A (en) * | 2014-11-27 | 2015-04-29 | 中国科学院国家天文台长春人造卫星观测站 | Photoelectric observing system for space debris with array structures |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP3671220B2 (en) * | 2002-04-30 | 2005-07-13 | 独立行政法人 宇宙航空研究開発機構 | Moving object detection method |
-
2018
- 2018-12-30 CN CN201811649815.7A patent/CN109901232B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103675938A (en) * | 2013-11-29 | 2014-03-26 | 北京空间机电研究所 | Full-airspace-coverage dual-mode integrated space-based space debris detection system |
| CN103983250A (en) * | 2014-05-19 | 2014-08-13 | 上海微小卫星工程中心 | Space target space-based imaging method and space target space-based imaging device |
| CN104570319A (en) * | 2014-11-27 | 2015-04-29 | 中国科学院国家天文台长春人造卫星观测站 | Photoelectric observing system for space debris with array structures |
Non-Patent Citations (1)
| Title |
|---|
| 空间碎片监测技术研究;袁伟明 等;《现代雷达》;20121231;第34卷(第12期);第16-19页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109901232A (en) | 2019-06-18 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Bakos et al. | System description and first light curves of the Hungarian automated telescope, an autonomous observatory for variability search | |
| Liebe | Pattern recognition of star constellations for spacecraft applications | |
| Boain | AB-Cs of sun-synchronous orbit mission design | |
| Rayman | The successful conclusion of the Deep Space 1 Mission: important results without a flashy title | |
| WO2017113567A1 (en) | Autonomous navigation method for mars probe | |
| CN109901232B (en) | Space debris space-based optical observation task generation method, storage medium and system | |
| Perryman et al. | In-orbit performance of the Hipparcos astrometry satellite | |
| Lederer et al. | The NASA meter class autonomous telescope: Ascension Island | |
| CN112649006A (en) | Orbit planning method for sun synchronous circular orbit | |
| Wang et al. | Analytical field-of-regard representation for rapid and accurate prediction of agile satellite imaging opportunities | |
| Rayman et al. | Dawn׳ s operations in cruise from Vesta to Ceres | |
| Accomazzo et al. | Rosetta following a living comet | |
| Golikov | THEONA—a numerical-analytical theory of motion of artificial satellites of celestial bodies | |
| CN115271528A (en) | Task planning method suitable for counterglow observation satellite | |
| CN110398241B (en) | Fixed star selection method for pointing correction of stationary orbit earth observation satellite instrument | |
| Schmidt et al. | ESA's Mars express mission-Europe on its way to Mars | |
| Wood | The Evolution of Deep Space Navigation: 2009–2012 | |
| Sezer et al. | Microsatellite constellation for earth observation missions | |
| Son et al. | Optical orbit determination of a geosynchronous Earth orbit satellite effected by baseline distances between various ground-based tracking stations I: COMS simulation case | |
| Garmier et al. | Philae landing on comet churyumov-gerasimenko: understanding of its descent trajectory, attitude, rebound and final landing site | |
| Lemmens et al. | Calibration of radar based re-entry predictions | |
| Clement et al. | Coordination challenges for autonomous spacecraft | |
| Zhang et al. | Multi-Mode Autonomous Mission Planning Approach for Earth Observation Satellites | |
| Hardhienata et al. | LAPAN-TUBSAT: From Concept to Early Operation | |
| Hall et al. | Determination of shadowing on the lunar surface using a lunar-celestial equatorial coordinate system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |