CN113619813B - High-orbit space debris fast traversing space-based optical observation system and method - Google Patents
High-orbit space debris fast traversing space-based optical observation system and method Download PDFInfo
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Abstract
The invention provides a high-orbit space debris fast traversal space-based optical observation system and a method, which comprise the following steps: a low-earth observation satellite configured to observe the geosynchronous belt at a latitude of 0 degrees on a near-earth orbit to cooperatively observe the geosynchronous belt at a first longitude range; an oblique geosynchronous orbit observation satellite configured to observe a geosynchronous belt of a second latitude and longitude range of 0 degrees on an oblique geosynchronous orbit; the central point of the first longitude range is opposite to the backlight blind area, and the second longitude range comprises the backlight blind area.
Description
Technical Field
The invention relates to the technical field of spaceflight, in particular to a high-orbit space debris fast traversing space-based optical observation system and a method.
Background
The dynamic characteristics of the geosynchronous orbit belt endow the geosynchronous orbit belt with good coverage stability relative to the earth surface, namely the aircraft on the orbit belt has the characteristics of being the same as or similar to the rotation angular velocity of the earth, and the aircraft on the orbit belt is static relative to the ground when viewed from the ground, so that the spacecraft arranged on the orbit belt can continuously and constantly stare at a fixed area on the ground for a long time in 24 hours, and therefore, the geosynchronous orbit belt becomes a gathering place of high-value space assets in the fields of modern navigation communication, data relay, meteorological observation and the like. However, the orbital space and spectrum resources are limited, and more novel spacecrafts enter the GEO orbit, so that the limited GEO orbit resources are more and more in short supply.
Meanwhile, space debris in the orbital zone is increased, space debris such as invalid spacecrafts, satellite scattering assemblies, rocket debris and the like in the GEO orbit seriously affect the operation safety of other satellites, once collision occurs, the number of new debris is exponentially increased, and the environmental deterioration of the geosynchronous orbit zone is aggravated. Therefore, it is necessary to observe fragments of the geosynchronous orbit band to ensure the safe operation of other satellites.
In addition, in many fields such as scientific research, military affairs and the like, the space debris needs to be monitored, the position of the space debris in the sky at each moment and the change of the position are given, the operation track of the space debris is determined, and therefore accurate information of the space debris is obtained.
At present, space debris is observed through a ground-based geosynchronous orbit zone debris observation system, the observation distance of the ground-based geosynchronous orbit zone debris observation system is long, at least 35785km is needed, and the ground-based geosynchronous orbit zone debris observation system is easily influenced by factors such as meteorological environment, site coverage, illumination interference and the like, so that the coverage range, observation timeliness, cataloging quantity, detection size and other capabilities are limited, and the observation requirements cannot be met. The observation platform on the low earth orbit is also difficult to overcome the problems of long distance, limited observation capability and the like of the observation system of the fragments of the geosynchronous orbit.
Especially, in the current space target observation system, the problems of backlight, detection sensitivity and the like can not realize the rapid traversal observation of high-orbit space debris. Specifically, the existing space-based optical observation technology has the following problems: the problem of backlight in the observation process cannot be solved; the observation timeliness of the high-rail fragments cannot be fast; the large-view-field wide-area observation detection capability is insufficient.
Disclosure of Invention
The invention aims to provide a space-based optical observation system and a space-based optical observation method for quickly traversing high-orbit space debris, so as to solve the problem that the conventional space target observation system cannot realize quick traversal observation of the high-orbit space debris.
In order to solve the above technical problem, the present invention provides a high-orbit space debris fast traversal space-based optical observation system, including:
a low-earth observation satellite configured to observe the geosynchronous belt at a latitude of 0 degrees on a near-earth orbit to cooperatively observe the geosynchronous belt at a first longitude range;
an oblique geosynchronous orbit observation satellite configured to observe a geosynchronous belt of a second latitude and longitude range of 0 degrees on an oblique geosynchronous orbit;
the central point of the first longitude range is opposite to the backlight blind area, and the second longitude range comprises the backlight blind area.
Optionally, in the high-orbit space debris fast traversal space-based optical observation system, the low-orbit observation satellite observes the geosynchronous belt in the first longitude range, and can realize that one orbit observes the geosynchronous belt in a longitude of 300 °.
Optionally, in the high-orbit space debris fast traversing space-based optical observation system, the low-orbit observation satellite includes a low-orbit wide-area observation camera, a camera view field of the low-orbit wide-area observation camera is not less than 20 ° x 40 °, and the detection capability is 13Mv within 300 ms;
the low-orbit wide-area observation camera is formed based on a low-orbit view field splicing method, and the low-orbit view field splicing method comprises the following steps: according to the distribution of high-orbit fragments, setting the latitude direction view field of a camera to be 40 degrees, and ensuring the coverage of a maximum latitude zone; the longitudinal field of view is set to be 20 degrees, so that a large-range scanning band is formed by utilizing the track motion difference of the low track and the high track, and finally, the large-range coverage of the longitudinal band is achieved.
According to the specific content of the low-orbit view field splicing method and the characteristics of the low-orbit observation and the camera on the IGSO satellite, the technical effects of low cost and high observation precision can be realized.
Optionally, in the high-orbit space debris fast traversal space-based optical observation system, the oblique geosynchronous orbit observation satellite includes a high-orbit wide-area observation camera, a camera view field of the high-orbit wide-area observation camera is not less than 10 ° × 10 °, and a detection capability is 15Mv within 300 ms;
the high-rail wide-area observation camera is formed based on a high-rail view field splicing method, and the high-rail view field splicing method comprises the following steps: IGSO satellites can use 10 ° × 10 ° cameras aimed at the regional latitude center that is not seen by the low-orbit satellites to splice the observations back and forth in east-west directions.
According to the specific content of the high-orbit view field splicing method, the inclined geosynchronous orbit observation and the cameras on the low-orbit satellites have different characteristics, and the technical effects of low cost and high observation precision can be realized.
Optionally, in the high-orbit space debris fast traversing space-based optical observation system, the low-orbit observation satellite maneuvers through an attitude, so that the low-orbit wide-area observation camera observes the 0-degree latitude geosynchronous belt and observes a 300-degree longitude belt in one orbit according to a stepping sky-patrol observation mode.
Optionally, in the high-orbit space debris fast traversal space-based optical observation system, in the observation process of the low-orbit observation satellite, the satellite attitude maneuver makes up the relative movement speed of the debris through the longitude maneuver while ensuring that the visual axis is constantly stared at the 0-degree latitude synchronous belt, so that the low-orbit wide-area observation camera adopts a long exposure method, the detection capability is improved, and the exposure time is 5s to 7 s.
Optionally, in the high-orbit space debris fast-traversal space-based optical observation system,
the inclined geosynchronous orbit observation satellite performs observation according to an observation mode by attitude maneuver, compensates the relative movement speed of fragments by longitude maneuver in the observation process, and improves the observation capability by adopting a long exposure method for a high-orbit wide area observation camera;
the oblique geosynchronous orbit observation satellite observes a second longitude range containing a 60-degree backlight blind area; finally, the double-star system realizes quick traversal observation of synchronous belt fragments.
Optionally, in the high-orbit space debris fast traversal space-based optical observation system, the relative movement speed of the debris is compensated by longitudinal maneuvering, so that the low-orbit wide-area observation camera adopts a long exposure method, and improving the detection capability includes:
firstly, ensuring that the image plane movement rate of the fragments is within 1 pixel through satellite image motion compensation;
in the second part, the camera increases the detection capability by extending the exposure time.
The invention also provides a high-orbit space debris fast traversing space-based optical observation method, which comprises the following steps:
firstly, developing a wide-area observation camera based on a view field splicing method;
deploying a low-orbit observation satellite on the near-earth orbit, deploying an inclined geosynchronous orbit observation satellite on the inclined geosynchronous orbit, and carrying a wide-area observation camera on each observation satellite;
thirdly, the low-orbit observation satellite maneuvers through the attitude, so that the low-orbit wide-area observation camera observes the 0-degree latitude geosynchronous belt according to the stepping sky-patrolling observation mode, and observes a 300-degree longitude belt in one orbit;
fourthly, the inclined geosynchronous orbit observation satellite performs observation according to the sky-patrolling mode through attitude maneuver, observes a 60-degree backlight blind area containing the low-orbit observation satellite, and finally realizes quick traversal observation of synchronous belt fragments by the double-satellite system;
and fifthly, the ground performs multi-platform high-precision initial orbit determination and orbit improvement on fragment observation data acquired by a low-orbit observation satellite and an inclined geosynchronous orbit observation satellite.
Optionally, in the method for fast traversing space debris in high orbit for space-based optical observation, the method further includes:
the satellite attitude maneuver of the low-orbit observation satellite in the observation process ensures that the visual axis always stares at the 0-degree latitude synchronous belt on one hand, and compensates the relative movement speed of fragments through the longitude maneuver on the other hand, so that the low-orbit wide-area observation camera can adopt a long exposure method to improve the detection capability;
the inclined geosynchronous orbit observation satellite compensates the relative movement speed of fragments in the observation process, so that the high-orbit wide-area observation camera adopts a long exposure method, and the observation capability is improved.
In the high-orbit space debris fast traversal space-based optical observation system and method provided by the invention, the low-orbit observation satellite is used for observing the earth synchronous belt with the latitude of 0 degree in the near-earth orbit so as to cooperatively observe the earth synchronous belt in the first longitude range opposite to the backlight blind area, thereby solving the problem of the observation timeliness of high-orbit debris; the inclined geosynchronous orbit observation satellite observes a geosynchronous belt with a latitude of 0 degree and a second longitude range including a backlight blind area on the inclined geosynchronous orbit, and solves the problem of backlight in the observation process.
The invention realizes the detection capability, the detection view field and the sunlight inhibition capability based on the existing space-based optical sensor, and solves the problem that the rapid traversal observation of high-orbit space debris cannot be realized due to the counter light and the detection sensitivity in the prior art through the multi-satellite cooperative observation of different orbits.
According to the invention, the synchronous belt fragments are quickly traversed and observed through the double-star system, and the relative movement speed of the fragments is compensated through the longitudinal maneuvering, so that the low-orbit wide-area observation camera adopts a long exposure method, the detection capability is improved, and the problem of insufficient wide-area observation detection capability of a large view field is solved.
According to the invention, the GEO target is observed all day long through high and low orbit satellite partitioned observation, so that the observation problem of the traditional backlight blind area is solved; high-rail fragments are quickly traversed by high-low rail networking in a matched quick traversing observation mode; the large-view-field high-detection capability is realized through the innovative working mode design (namely, the camera image motion compensation and the observation area splicing are carried out based on the satellite attitude maneuver, so that the contradiction between the detection capability and the large-range observation is overcome); and the kilometer grade primary rail and the hectometer grade precise rail are determined by the high-low rail long base line rail determination.
The invention has the advantages that: the detection field of view is large, the detection capacity is high, and high coverage rate on fragments can be realized; the scanning speed is high, multiple stars cooperatively make up a backlight blind area, and fragments can be quickly traversed; the invention can be applied to various tracks such as sun synchronous tracks, zero dip angles, small dip angles and the like, and is flexible to deploy; the invention adopts a multi-platform combined orbit determination mode to realize high-precision and rapid orbit determination.
Drawings
FIG. 1 is a schematic diagram of a high-orbit space debris fast-traversal space-based optical observation system according to an embodiment of the invention;
FIG. 2 is a schematic diagram of a high-orbit space debris fast traversing space-based optical observation system for step-by-step observation during a tour in an embodiment of the present invention;
fig. 3 is a schematic diagram of the initial rail position error of a single IGSO + single LEO in an embodiment of the present invention.
Detailed Description
The invention is further elucidated with reference to the drawings in conjunction with the detailed description.
It should be noted that the components in the figures may be exaggerated and not necessarily to scale for illustrative purposes. In the figures, identical or functionally identical components are provided with the same reference symbols.
In the present invention, "disposed on …", "disposed over …" and "disposed over …" do not exclude the presence of an intermediate therebetween, unless otherwise specified. Further, "disposed on or above …" merely indicates the relative positional relationship between two components, and may also be converted to "disposed below or below …" and vice versa in certain cases, such as after reversing the product direction.
In the present invention, the embodiments are only intended to illustrate the aspects of the present invention, and should not be construed as limiting.
In the present invention, the terms "a" and "an" do not exclude the presence of a plurality of elements, unless otherwise specified.
It is further noted herein that in embodiments of the present invention, only a portion of the components or assemblies may be shown for clarity and simplicity, but those of ordinary skill in the art will appreciate that, given the teachings of the present invention, required components or assemblies may be added as needed in a particular scenario. In addition, features in different embodiments of the invention may be combined with each other, unless otherwise specified. For example, a feature of the second embodiment may be substituted for a corresponding or functionally equivalent or similar feature of the first embodiment, and the resulting embodiments are likewise within the scope of the disclosure or recitation of the present application.
It is also noted herein that, within the scope of the present invention, the terms "same", "equal", and the like do not mean that the two values are absolutely equal, but allow some reasonable error, that is, the terms also encompass "substantially the same", "substantially equal". By analogy, in the present invention, the terms "perpendicular", "parallel" and the like in the directions of the tables also cover the meanings of "substantially perpendicular", "substantially parallel".
The numbering of the steps of the methods of the present invention does not limit the order in which the method steps are performed. Unless specifically stated, the method steps may be performed in a different order.
The fast traversal space-based optical observation system and method for high-orbit space debris proposed by the present invention are further described in detail with reference to the accompanying drawings and the specific embodiments. Advantages and features of the present invention will become apparent from the following description and from the claims. It is to be noted that the drawings are in a very simplified form and are not to precise scale, which is merely for the purpose of facilitating and distinctly claiming the embodiments of the present invention.
The invention aims to provide a space-based optical observation system and a space-based optical observation method for quickly traversing high-orbit space debris, so as to solve the problem that the conventional space target observation system cannot realize quick traversal observation of the high-orbit space debris.
In order to achieve the above object, the present invention provides a high-orbit space debris fast traversal space-based optical observation system and method, including: a low-earth observation satellite configured to observe the geosynchronous belt at a latitude of 0 degrees on a near-earth orbit to cooperatively observe the geosynchronous belt at a first longitude range; an oblique geosynchronous orbit observation satellite configured to observe a geosynchronous belt of a second latitude and longitude range of 0 degrees on an oblique geosynchronous orbit; the central point of the first longitude range is opposite to the backlight blind area, and the second longitude range comprises the backlight blind area.
An embodiment of the present invention provides a high-orbit space debris fast traversal space-based optical observation system, as shown in fig. 1, including: a low-orbit observation satellite configured to observe the geosynchronous belt at a latitude of 0 degrees in a near-earth orbit to cooperatively observe the geosynchronous belt at a first longitude range (low-orbit wide-area general survey); an oblique geosynchronous orbit observation satellite configured to observe a geosynchronous belt of a second latitude range of 0 degrees latitude on an oblique geosynchronous orbit (high-orbit wide-area blind compensation); the central point of the first longitude range is opposite to the backlight blind area, and the second longitude range comprises the backlight blind area.
In an embodiment of the invention, in the high-orbit space debris fast traversing space-based optical observation system, the orbit of the low-orbit observation satellite is a zero-dip-angle orbit, and the attitude maneuver is [ -150 °, 150 ° ], so that the geosynchronous belt in the first longitude range can be observed through cooperative fit, and the geosynchronous belt in the longitude range of 300 ° can be observed in one orbit.
In one embodiment of the invention, in the high-orbit space debris fast traversal space-based optical observation system, the low-orbit observation satellite comprises a low-orbit wide-area observation camera, the camera view field of the low-orbit wide-area observation camera is not less than 20 degrees multiplied by 40 degrees, and the detection capability is 13Mv within 300 ms; the low-orbit wide-area observation camera is formed based on a low-orbit view field splicing method, and the low-orbit view field splicing method comprises the following steps: according to the distribution of high-orbit fragments, setting the latitude direction view field of a camera to be 40 degrees, and ensuring the coverage of the maximum latitude zone; the longitudinal field of view is set to be 20 degrees, so that a large-range scanning band is formed by utilizing the track motion difference of the low track and the high track, and finally, the large-range coverage of the longitudinal band is achieved.
In one embodiment of the invention, in the high-orbit space debris fast traversal space-based optical observation system, the inclined geosynchronous orbit observation satellite comprises a high-orbit wide-area observation camera, the camera field of view of the high-orbit wide-area observation camera is not less than 10 degrees multiplied by 10 degrees, and the detection capability is 15Mv within 300 ms; the high-rail wide-area observation camera is formed based on a high-rail view field splicing method, and the high-rail view field splicing method comprises the following steps: IGSO satellites can use 10 ° × 10 ° cameras aimed at the regional latitude center that is not seen by the low-orbit satellites to splice the observations back and forth in east-west directions.
In an embodiment of the invention, in the high-orbit space debris fast-traversal space-based optical observation system, as shown in fig. 2, the low-orbit observation satellite is maneuvered by an attitude, so that the low-orbit wide-area observation camera observes a 0-degree latitude geosynchronous belt and observes a 300-degree longitude belt in one orbit according to a stepping sky-patrol observation mode.
In an embodiment of the invention, in the high-orbit space debris fast traversal space-based optical observation system, as shown in fig. 2, in the observation process of a low-orbit observation satellite, a satellite attitude maneuver makes up the relative movement speed of debris through a longitude maneuver while ensuring that a visual axis always stares at a 0-degree latitude synchronous belt, so that a low-orbit wide-area observation camera adopts a long exposure method, the detection capability is improved, and the exposure time is 5-7 s.
In one embodiment of the invention, in the high-orbit space debris fast traversal space-based optical observation system, an inclined geosynchronous orbit observation satellite observes according to a sky inspection mode through attitude maneuver, the relative movement speed of the debris is compensated through longitude maneuver in the observation process, and a high-orbit wide-area observation camera adopts a long exposure method to improve the observation capability; the oblique geosynchronous orbit observation satellite observes a second longitude range containing a 60-degree backlight blind area; the second longitude range comprises a positioning point +/-90-degree area, and finally the three-star system realizes quick traversal observation of synchronous belt fragments.
In one embodiment of the invention, in the high-orbit space debris fast traversal space-based optical observation system, the relative movement speed of the debris is compensated through longitudinal maneuvering, so that the low-orbit wide-area observation camera adopts a long exposure method.
The invention also provides a high-orbit space debris fast traversal space-based optical observation method, which comprises the following steps: firstly, developing a wide-area observation camera based on a view field splicing method; deploying a low-orbit observation satellite on the near-earth orbit, deploying an inclined geosynchronous orbit observation satellite on the inclined geosynchronous orbit, and carrying a wide-area observation camera on each observation satellite; thirdly, the low-orbit observation satellite maneuvers through the attitude, so that the low-orbit wide-area observation camera observes a 0-degree latitude earth synchronous belt according to a stepping sky-patrol observation mode, one orbit observes a 300-degree longitude zone, and one low-orbit observation satellite cooperatively realizes the observation capability of the 300-degree longitude zone in one hour; fourthly, the inclined geosynchronous orbit observation satellite performs observation according to the sky-patrolling mode through attitude maneuver, observes a +/-90-degree area of a positioning point including a 60-degree backlight blind area of the low-orbit observation satellite, and finally realizes quick traversal observation of synchronous belt fragments by the three-star system; and fifthly, the ground performs multi-platform high-precision initial orbit determination and orbit improvement on fragment observation data acquired by a low-orbit observation satellite and an inclined geosynchronous orbit observation satellite.
In an embodiment of the present invention, in the method for fast traversing space debris over an air-based optical observation on an elevated track, the method further includes: the satellite attitude maneuver of the low-orbit observation satellite in the observation process ensures that the visual axis always stares at the 0-degree latitude synchronous belt on one hand, and compensates the relative movement speed of fragments through the longitude maneuver on the other hand, so that the low-orbit wide-area observation camera can adopt a long exposure method to improve the detection capability; the inclined geosynchronous orbit observation satellite compensates the relative movement speed of fragments in the observation process, so that the high-orbit wide-area observation camera adopts a long exposure method, and the observation capability is improved.
In the high-orbit space debris fast traversal space-based optical observation system and method provided by the invention, as shown in fig. 3, the error of the initial orbit position of a single IGSO + single LEO is visible, a low-orbit observation satellite is used for observing a geosynchronous belt at 0-degree latitude in a near-earth orbit so as to cooperatively observe the geosynchronous belt in a first longitude range opposite to a backlight blind zone, and the problem that the observation timeliness of high-orbit space debris cannot be fast is solved; the inclined geosynchronous orbit observation satellite observes a geosynchronous belt with 0-degree latitude and a second longitude range including a backlight blind area on the inclined geosynchronous orbit, and solves the problem of backlight in the observation process.
The invention realizes the detection capability, the detection view field and the sunlight inhibition capability based on the existing space-based optical sensor, and solves the problem that the rapid traversal observation of high-orbit space debris cannot be realized due to the counter light and the detection sensitivity in the prior art through the multi-satellite cooperative observation of different orbits.
According to the invention, the synchronous belt fragments are quickly traversed and observed through the three-star system, and the relative movement speed of the fragments is compensated through the longitudinal maneuvering, so that the low-orbit wide-area observation camera adopts a long exposure method, the detection capability is improved, and the problem of insufficient wide-area observation detection capability of a large view field is solved.
According to the invention, the GEO target is observed all day long through high and low orbit satellite partitioned observation, so that the observation problem of the traditional backlight blind area is solved; high-rail fragments are quickly traversed by high-low rail networking in a matched quick traversing observation mode; the large-view-field high-detection capability is realized through innovative working mode design (camera image motion compensation and observation area splicing are carried out based on satellite attitude maneuver, and the contradiction between detection capability and large-range observation is overcome); and the kilometer grade primary rail and the hectometer grade cataloging rail are determined through the high-low rail long base line rail determination.
The invention has the advantages that: the detection field of view is large, the detection capacity is high, and high coverage rate on fragments can be realized; the scanning speed is high, multiple stars cooperatively make up a backlight blind area, and fragments can be quickly traversed; the invention can be applied to various tracks such as sun synchronous tracks, zero dip angles, small dip angles and the like, and is flexible to deploy; the invention adopts a multi-platform combined orbit determination mode to realize high-precision and rapid orbit determination.
In summary, the above embodiments have described in detail various configurations of the space debris fast traverse space-based optical observation system and method, and it is understood that the present invention includes, but is not limited to, the configurations listed in the above embodiments, and any modifications based on the configurations provided by the above embodiments are within the scope of the present invention. One skilled in the art can take the content of the above embodiments to take the inverse three.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other. For the system disclosed by the embodiment, the description is relatively simple because the system corresponds to the method disclosed by the embodiment, and the relevant points can be referred to the method part for description.
The above description is only for the purpose of describing the preferred embodiment of the present invention, and is not intended to limit the scope of the present invention, and any variations and modifications made by those skilled in the art based on the above disclosure are intended to fall within the scope of the appended claims.
Claims (8)
1. A high-orbit space debris fast traversal space-based optical observation system is characterized by comprising:
a low-earth observation satellite configured to observe the geosynchronous belt at a latitude of 0 degrees on a near-earth orbit to cooperatively observe the geosynchronous belt at a first longitude range;
an oblique geosynchronous orbit observation satellite configured to observe a geosynchronous belt of a second latitude and longitude range of 0 degrees on an oblique geosynchronous orbit;
the central point of the first longitude range is opposite to the backlight blind area, and the second longitude range comprises the backlight blind area;
the low-orbit observation satellite comprises a low-orbit wide area observation camera, the camera view field of the low-orbit wide area observation camera is not less than 20 degrees multiplied by 40 degrees, and the detection capability is 13Mv within 300 ms;
the low-orbit wide-area observation camera is formed based on a low-orbit view field splicing method, and the low-orbit view field splicing method comprises the following steps: according to the distribution of high-orbit fragments, setting the latitude direction view field of a camera to be 40 degrees, and ensuring the coverage of a maximum latitude zone; setting a longitudinal view field to be 20 degrees, forming a large-range scanning band by utilizing the motion difference of low-rail and high-rail tracks, and finally covering the longitudinal band in a large range;
the inclined geosynchronous orbit observation satellite comprises a high orbit wide area observation camera, the camera view field of the high orbit wide area observation camera is not less than 10 degrees multiplied by 10 degrees, and the detection capability is 15Mv within 300 ms;
the high-rail wide-area observation camera is formed based on a high-rail view field splicing method, and the high-rail view field splicing method comprises the following steps: the IGSO satellite adopts a camera of 10 degrees multiplied by 10 degrees, and aims at the regional latitude center which can not be seen by the low orbit satellite to carry out splicing observation in the east-west direction.
2. The system as claimed in claim 1, wherein the number of the low-earth observation satellites is 1, and the observation of the geosynchronous belt with a longitude of 300 ° can be realized by one-orbit through the cooperative observation of the geosynchronous belt with a first longitude range.
3. The high-orbit space debris fast-traversal space-based optical observation system of claim 1,
the low-orbit observation satellite maneuvers through the attitude, so that the low-orbit wide-area observation camera observes the 0-degree latitude earth synchronous belt according to the stepping sky-patrolling observation mode, and observes a 300-degree longitude belt in one orbit.
4. The high-orbit space debris fast-traversal space-based optical observation system of claim 3,
in the low-orbit observation satellite observation process, the satellite attitude maneuver ensures that the visual axis always stares at a 0-degree latitude synchronous belt, and simultaneously compensates the relative movement speed of fragments through the longitude maneuver, so that the low-orbit wide area observation camera adopts a long exposure method, the detection capability is improved, and the exposure time is 5-7 s.
5. The high-orbit space debris fast-traversal space-based optical observation system of claim 4,
the inclined geosynchronous orbit observation satellite performs observation according to an observation mode by attitude maneuver, compensates the relative movement speed of fragments by longitude maneuver in the observation process, and improves the observation capability by adopting a long exposure method for a high-orbit wide area observation camera;
the oblique geosynchronous orbit observation satellite observes a second longitude range including a 60-degree backlit blind area.
6. The system as claimed in claim 5, wherein the longitude maneuver compensates for the relative movement speed of the space debris, so that the low-orbit wide-area observation camera adopts a long exposure method, and the improvement of the detection capability includes: firstly, image motion compensation is carried out through satellite attitude maneuver to ensure that the image plane motion rate of fragments is within 1 pixel;
in the second step, the camera increases the detection capability by prolonging the exposure time.
7. A high-orbit space debris fast traversal space-based optical observation method is characterized by comprising the following steps:
firstly, developing a wide-area observation camera based on a view field splicing method;
deploying a low-orbit observation satellite on the near-earth orbit, deploying an inclined geosynchronous orbit observation satellite on the inclined geosynchronous orbit, carrying a low-orbit wide-area observation camera on each low-orbit observation satellite, and carrying a high-orbit wide-area observation camera on each inclined geosynchronous orbit observation satellite;
thirdly, the low-orbit observation satellite maneuvers through the attitude, so that the low-orbit wide-area observation camera observes a 0-degree latitude earth synchronous belt according to a stepping sky-patrol observation mode, one orbit observes a 300-degree longitude zone, and one low-orbit observation satellite is cooperatively matched to realize the observation capability of the one orbit on the 300-degree longitude zone;
fourthly, the inclined geosynchronous orbit observation satellite performs observation according to the sky-patrolling mode through attitude maneuver, observes a 60-degree backlight blind area containing the low-orbit observation satellite, and finally realizes quick traversal observation of synchronous belt fragments by the double-satellite system;
and fifthly, the ground performs multi-platform high-precision initial orbit determination and orbit improvement on fragment observation data acquired by a low-orbit observation satellite and an inclined geosynchronous orbit observation satellite.
8. The method for fast traversal of high-orbit space debris through space-based optical observation of claim 7, further comprising:
the satellite attitude maneuver of the low-orbit observation satellite in the observation process ensures that the visual axis always stares at the 0-degree latitude synchronous belt on one hand, and compensates the relative movement speed of fragments through the longitude maneuver on the other hand, so that the low-orbit wide-area observation camera can adopt a long exposure method to improve the detection capability;
the inclined geosynchronous orbit observation satellite compensates the relative movement speed of fragments in the observation process, so that the high-orbit wide-area observation camera adopts a long exposure method, and the observation capability is improved.
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103699129A (en) * | 2013-12-06 | 2014-04-02 | 上海卫星工程研究所 | Quick traversing method of geosynchronous orbit targets based on low-earth-orbit observation satellite |
| CN110221297A (en) * | 2019-06-18 | 2019-09-10 | 中国空间技术研究院 | A kind of low rail SAR constellation method for arranging of height-based on simulation forward mode |
| 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 |
| CN111609857A (en) * | 2020-06-01 | 2020-09-01 | 中国科学院微小卫星创新研究院 | Space debris orbit determination traversal observation method and system |
| CN112591146A (en) * | 2020-12-21 | 2021-04-02 | 中国人民解放军63921部队 | Observation method and system for high-orbit target minute-level rapid traversal |
| CN113255109A (en) * | 2021-04-29 | 2021-08-13 | 上海宇航系统工程研究所 | Design method and system for on-orbit health monitoring orbit of high-orbit non-zero inclination angle satellite |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| US6019318A (en) * | 1997-06-16 | 2000-02-01 | Hugehs Electronics Corporation | Coordinatable system of inclined geosynchronous satellite orbits |
| US7193557B1 (en) * | 2003-04-29 | 2007-03-20 | Lockheed Martin Corporation | Random set-based cluster tracking |
| US9399527B2 (en) * | 2012-06-07 | 2016-07-26 | Electronics And Telecommunications Research Instit | Apparatus and method for controlling geostationary orbit satellite |
-
2021
- 2021-09-17 CN CN202211004545.0A patent/CN115230992A/en active Pending
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Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103699129A (en) * | 2013-12-06 | 2014-04-02 | 上海卫星工程研究所 | Quick traversing method of geosynchronous orbit targets based on low-earth-orbit observation satellite |
| CN110221297A (en) * | 2019-06-18 | 2019-09-10 | 中国空间技术研究院 | A kind of low rail SAR constellation method for arranging of height-based on simulation forward mode |
| 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 |
| CN111609857A (en) * | 2020-06-01 | 2020-09-01 | 中国科学院微小卫星创新研究院 | Space debris orbit determination traversal observation method and system |
| CN112591146A (en) * | 2020-12-21 | 2021-04-02 | 中国人民解放军63921部队 | Observation method and system for high-orbit target minute-level rapid traversal |
| CN113255109A (en) * | 2021-04-29 | 2021-08-13 | 上海宇航系统工程研究所 | Design method and system for on-orbit health monitoring orbit of high-orbit non-zero inclination angle satellite |
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