Space Debris Observation System

Abstract

The present invention provides a space debris observation system, comprising: a low-orbit observation satellite, configured to observe the geosynchronous belt at a latitude of 0 degrees in a near-Earth orbit, so as to coordinate with the observation of the geosynchronous belt in a first longitude range; an inclined geosynchronous orbit observation satellite, configured to observe the geosynchronous belt at a latitude of 0 degrees and a second longitude range in the inclined geosynchronous orbit; wherein the center point of the first longitude range is opposite to a backlight blind zone, and the second longitude range includes the backlight blind zone.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and in particular to a high-orbit space debris rapid traversal space-based optical observation system. Background Art

[0002] The dynamic characteristics of the geosynchronous orbit belt itself give it good coverage stability relative to the surface, that is, the spacecraft on the orbit belt has the same or similar angular velocity as the earth's rotation. From the ground, the spacecraft on the orbit belt is stationary relative to the ground, so that the spacecraft arranged in the orbit belt can stare at a fixed area on the ground for a long time without interruption for 24 hours. Therefore, the geosynchronous orbit belt has become a gathering place for high-value space assets in the fields of modern navigation and communication, data relay, meteorological observation, etc. However, the orbital space and spectrum resources are limited. As more and more new spacecraft enter the GEO orbit, the limited GEO orbital resources are becoming increasingly scarce.

[0003] At the same time, the number of space debris in the orbital belt has also increased. Failed spacecraft, satellite scattered components, rocket debris and other space debris in the GEO orbit seriously affect the operational safety of other satellites. Once a collision occurs, the number of new debris will increase exponentially, exacerbating the environmental degradation of the geosynchronous orbit belt. Therefore, it is necessary to observe the debris in the geosynchronous orbit belt to ensure the operational safety of other satellites.

[0004] In addition, in many fields such as scientific research and military, it is necessary to monitor space debris, give the position and changes of space debris in the sky at every moment, determine the orbit of space debris, and thus obtain accurate information about space debris.

[0005] The existing space target observation system has the problem of backlight during the observation process, so the observation capability is limited. Summary of the invention

[0006] The purpose of the present invention is to provide a high-orbit space debris rapid traversal space-based optical observation system to solve the problem of backlighting in existing space target observation systems.

[0007] In order to solve the above technical problems, the present invention provides a high-orbit space debris rapid traversal space-based optical observation system, comprising:

[0008] A low-orbit observation satellite is configured to observe the geosynchronous belt at 0 degrees latitude in a low-Earth orbit to coordinate with the observation of the geosynchronous belt in the first longitude range;

[0009] an inclined geosynchronous orbit observation satellite configured to observe a geosynchronous belt in a 0 degree latitude and a second longitude range in an inclined geosynchronous orbit;

[0010] The center point of the first longitude range is opposite to the backlight blind area, and the second longitude range includes the backlight blind area.

[0011] Optionally, in the high-orbit space debris rapid traversal space-based optical observation system,

[0012] Through attitude maneuvers, the low-orbit observation satellite enables the low-orbit wide-area observation camera to observe the 0-degree latitude geosynchronous belt in accordance with the step-by-step survey observation mode, and observe the 300° longitude belt in one orbit. A low-orbit observation satellite cooperates to achieve the observation capability of the 300° longitude belt in one orbit.

[0013] Optionally, in the high-orbit space debris rapid traversal space-based optical observation system, the inclined geosynchronous orbit observation satellite performs attitude maneuvers and observes in a sky survey mode, observing the 60-degree backlight blind area including the low-orbit observation satellite, and finally the dual-satellite system realizes rapid traversal observation of synchronous belt debris.

[0014] In the high-orbit space debris rapid traversal space-based optical observation system provided by the present invention, the geosynchronous belt at 0 degree latitude is observed by a low-orbit observation satellite in a near-Earth orbit, so as to coordinate with the observation of the geosynchronous belt in a first longitude range opposite to the backlight blind zone. The inclined geosynchronous orbit observation satellite observes the geosynchronous belt at 0 degree latitude and in a second longitude range including the backlight blind zone in an inclined geosynchronous orbit, thereby solving the backlight problem in the observation process. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 is a schematic diagram of a high-orbit space debris rapid traversal space-based optical observation system in one embodiment of the present invention;

[0016] Figure 2 This is a schematic diagram of a high-orbit space debris rapidly traversing a space-based optical observation system for step-by-step sky survey observation in one embodiment of the present invention;

[0017] Figure 3 It is a schematic diagram of the initial orbit position error of a single IGSO + a single LEO in one embodiment of the present invention. DETAILED DESCRIPTION

[0018] The present invention will be further described below in conjunction with specific embodiments with reference to the accompanying drawings.

[0019] It should be noted that the components in the figures may be shown exaggeratedly for the sake of illustration and are not necessarily true to scale. In the figures, identical or functionally identical components are provided with the same reference numerals.

[0020] In the present invention, unless otherwise specified, "arranged on...", "arranged above..." and "arranged above..." do not exclude the existence of an intermediate between the two. In addition, "arranged on or above..." merely indicates the relative positional relationship between two components, and in certain cases, such as after reversing the product direction, it can also be converted into "arranged below or below...", and vice versa.

[0021] In the present invention, each embodiment is only intended to illustrate the aspects of the present invention and should not be construed as limiting.

[0022] In the present invention, unless otherwise specified, the quantifiers "a", "an" and "an" do not exclude the presence of a plurality of elements.

[0023] It should also be noted that in the embodiments of the present invention, for the sake of clarity and simplicity, only a portion of the parts or components may be shown, but those of ordinary skill in the art will understand that under the teachings of the present invention, the required parts or components may be added according to the needs of the specific scenario. In addition, unless otherwise specified, the features in different embodiments of the present invention may be combined with each other. For example, a feature in the second embodiment may be used to replace a corresponding or functionally identical or similar feature in the first embodiment, and the resulting embodiment also falls within the disclosure scope or recorded scope of the present application.

[0024] It should also be noted that within the scope of the present invention, the terms "same", "equal", "equal to" and the like do not mean that the values ​​of the two are absolutely equal, but allow a certain reasonable error, that is, the terms also cover "substantially the same", "substantially equal", "substantially equal to". By analogy, in the present invention, the terms "perpendicular to", "parallel to" and the like indicating directions also cover the meanings of "substantially perpendicular to" and "substantially parallel to".

[0025] In addition, the numbering of the steps of the methods of the present invention does not limit the execution order of the method steps. Unless otherwise specified, the method steps can be executed in different orders.

[0026] The high-orbit space debris rapid traversal space-based optical observation system proposed by the present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments. The advantages and features of the present invention will become clearer according to the following description and claims. It should be noted that the drawings are all in a very simplified form and are not in precise proportions, and are only used to conveniently and clearly assist in explaining the purpose of the embodiments of the present invention.

[0027] At present, space debris is observed through the ground-based geosynchronous orbit debris observation system, which has a long observation distance of at least 35,785 km and is easily affected by factors such as meteorological environment, site coverage, and light interference, which limits its coverage, observation timeliness, cataloging quantity, and detection size, and cannot meet the observation requirements. The observation system of geosynchronous orbit debris by the observation platform in low earth orbit is also difficult to overcome the problems of long distance and limited observation capability.

[0028] In particular, the current space target observation system cannot achieve rapid traversal observation of high-orbit space debris due to problems such as backlighting and detection sensitivity. Specifically, the existing space-based optical observation technology has the following problems: it cannot solve the backlighting problem during the observation process; the observation timeliness of high-orbit debris cannot be achieved quickly; and the large field of view and wide-area observation detection capabilities are insufficient.

[0029] The purpose of the present invention is to provide a high-orbit space debris rapid traversal space-based optical observation system to solve the problem that the existing space target observation system cannot achieve rapid traversal observation of high-orbit space debris.

[0030] To achieve the above-mentioned objectives, the present invention provides a high-orbit space debris rapid traversal space-based optical observation system, comprising: a low-orbit observation satellite, configured to observe the geosynchronous belt at 0 degrees latitude in a low-Earth orbit, so as to coordinate the observation of the geosynchronous belt in a first longitude range; an inclined geosynchronous orbit observation satellite, configured to observe the geosynchronous belt at 0 degrees latitude and a second longitude range in an inclined geosynchronous orbit; wherein the center point of the first longitude range is opposite to the backlight blind zone, and the second longitude range includes the backlight blind zone.

[0031] An embodiment of the present invention provides a high-orbit space debris rapid traversal space-based optical observation system, such as Figure 1 As shown, it includes: a low-orbit observation satellite, which is configured to observe the geosynchronous belt at 0 degrees latitude in a near-Earth orbit, so as to coordinate the observation of the geosynchronous belt in a first longitude range (low-orbit wide-area survey); an inclined geosynchronous orbit observation satellite, which is configured to observe the geosynchronous belt in a second longitude range at 0 degrees latitude on an inclined geosynchronous orbit (high-orbit wide-area blind spot); wherein the center point of the first longitude range is opposite to the backlight blind spot, and the second longitude range includes the backlight blind spot.

[0032] In one embodiment of the present invention, in the high-orbit space debris rapid traversal space-based optical observation system, the orbit of the low-orbit observation satellite is a zero-inclination orbit and the attitude maneuver is [-150°, 150°], so as to achieve observation of the geosynchronous belt in the first longitude range through coordinated cooperation, and can achieve observation of the geosynchronous belt in the longitude of 300° with one orbit.

[0033] In one embodiment of the present invention, in the high-orbit space debris rapid traversal space-based optical observation system, the low-orbit observation satellite includes a low-orbit wide-area observation camera, the camera field of view of the low-orbit wide-area observation camera is not less than 20°×40°, and the detection capability is 13Mv within 300ms; wherein the low-orbit wide-area observation camera is formed based on a low-orbit field of view splicing method, and the low-orbit field of view splicing method includes: according to the distribution of high-orbit debris, setting the camera's latitude field of view to 40° to ensure coverage of the maximum latitude band; setting the longitude field of view to 20°, so as to utilize the low-orbit and high-orbit orbital motion difference to form a large-range scanning belt, and finally achieve a large-range coverage of the longitude belt.

[0034] In one embodiment of the present invention, in the high-orbit space debris rapid traversal space-based optical observation system, the inclined geosynchronous orbit observation satellite includes 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°×10°, and the detection capability is 15Mv within 300ms; wherein the high-orbit wide-area observation camera is formed based on a high-orbit field of view stitching method, and the high-orbit field of view stitching method includes: the IGSO satellite can use a 10°×10° camera, aiming at the latitude center of the area that the low-orbit satellite cannot see, and stitching observation back and forth in the east-west direction.

[0035] In one embodiment of the present invention, in the high-orbit space debris rapid traversal space-based optical observation system, as Figure 2 As shown, the low-orbit observation satellite performs attitude maneuvers so that the low-orbit wide-area observation camera observes the 0-degree latitude geosynchronous belt in the step survey observation mode and observes the 300-degree longitude belt in one orbit.

[0036] In one embodiment of the present invention, in the high-orbit space debris rapid traversal space-based optical observation system, as Figure 2 As shown in the figure, during the observation process of the low-orbit observation satellite, the satellite attitude maneuver ensures that the visual axis always stares at the 0° latitude synchronization belt, while compensating for the relative movement speed of the debris through longitude maneuvers, so that the low-orbit wide-area observation camera adopts a long exposure method to improve the detection capability, and the exposure time is 5s~7s.

[0037] In one embodiment of the present invention, in the high-orbit space debris rapid traversal space-based optical observation system, the inclined geosynchronous orbit observation satellite performs attitude maneuvers and observes in a sky survey mode. During the observation process, the relative movement speed of the debris is compensated by longitude maneuvers. The high-orbit wide-area observation camera adopts a long exposure method to improve the observation capability; the inclined geosynchronous orbit observation satellite observes a second longitude range including a 60-degree backlight blind area; the second longitude range includes the ±90° area of ​​the positioning point, and finally the three-star system realizes rapid traversal observation of the synchronous belt debris.

[0038] In one embodiment of the present invention, in the high-orbit space debris rapid traversal space-based optical observation system, the relative movement speed of the debris is compensated by longitude maneuvers, so that the low-orbit wide-area observation camera adopts a long exposure method.

[0039] The present invention also provides a method for rapid traversal of high-orbit space debris by space-based optical observation, comprising: a first step, developing a wide-area observation camera based on a field of view stitching method; a second step, deploying a low-orbit observation satellite in a low-Earth orbit and an inclined geosynchronous orbit observation satellite in an inclined geosynchronous orbit, each observation satellite carrying a wide-area observation camera; a third step, the low-orbit observation satellite performs attitude maneuvers so that the low-orbit wide-area observation camera observes the 0-degree latitude geosynchronous belt in a step-by-step sky survey observation mode, and observes the 300-degree longitude belt in one orbit, and a low-orbit observation satellite cooperates to achieve one-hour observation capability of the 300-degree longitude belt; a fourth step, the inclined geosynchronous orbit observation satellite performs attitude maneuvers in accordance with the sky survey mode, observes the ±90-degree area of ​​the positioning point including the 60-degree backlight blind spot of the low-orbit observation satellite, and finally the three-star system realizes rapid traversal observation of synchronous belt debris; a fifth step, the ground performs multi-platform high-precision initial orbit determination and orbit improvement on the debris observation data obtained by the low-orbit observation satellite and the inclined geosynchronous orbit observation satellite.

[0040] In one embodiment of the present invention, the method for rapid traversal of high-orbit space debris by space-based optical observation also includes: satellite attitude maneuvers by low-orbit observation satellites during the observation process ensure that the visual axis always gazes at the 0° latitude synchronization belt on the one hand, and compensate for the relative movement speed of the debris through longitude maneuvers on the other hand, so that the low-orbit wide-area observation camera can adopt a long exposure method to improve the detection capability; tilting the geosynchronous orbit observation satellite during the observation process compensates for the relative movement speed of the debris, so that the high-orbit wide-area observation camera can adopt a long exposure method to improve the observation capability.

[0041] In the high-orbit space debris rapid traversal space-based optical observation system provided by the present invention, if Figure 3 As shown, the initial orbit position error of a single IGSO + a single LEO is visible. The low-orbit observation satellite observes the geosynchronous belt at 0 degrees latitude in the near-Earth orbit, so as to coordinate and observe the geosynchronous belt in the first longitude range opposite to the backlight blind zone, thereby solving the problem that the observation timeliness of high-orbit debris cannot be achieved quickly. The inclined geosynchronous orbit observation satellite observes the geosynchronous belt at 0 degrees latitude and the second longitude range including the backlight blind zone in the inclined geosynchronous orbit, thereby solving the backlight problem in the observation process.

[0042] The present invention realizes the detection capability, detection field of view and sunlight suppression capability based on existing space-based optical sensors, and solves the problem of the prior art that rapid traversal observation of high-orbit space debris cannot be achieved due to backlighting and detection sensitivity through collaborative observation of multiple satellites in different orbits.

[0043] The present invention realizes rapid traversal observation of synchronous belt debris through the three-star system, and compensates for the relative movement speed of the debris by longitude maneuvering, so that the low-orbit wide-area observation camera adopts a long exposure method to improve the detection capability, thus solving the problem of insufficient detection capability of large-field-of-view wide-area observation.

[0044] The present invention realizes all-day observation of GEO targets through partitioned observation of high and low orbit satellites, overcoming the difficulty of traditional backlight blind area observation; through high and low orbit networking, in conjunction with the fast traversal observation mode, rapid traversal of high orbit debris is realized; through innovative working mode design (camera image motion compensation and observation area splicing based on satellite attitude maneuvers, overcoming the contradiction between detection capability and large-scale observation), a large field of view and high detection capability are achieved; through high and low orbit long baseline orbit determination, kilometer-level initial orbit determination and hundred-meter-level cataloguing orbit determination are achieved.

[0045] The advantages of the present invention are: large detection field of view, high detection capability, and high coverage of debris; fast scanning speed, multi-satellite collaboration to compensate for backlight blind spots, and rapid traversal of debris; the present invention can be applied to a variety of orbits such as sun-synchronous orbit, zero inclination, and small inclination, and is flexible to deploy; the present invention adopts a multi-platform joint orbit determination method to achieve high-precision and rapid orbit determination.

[0046] Optionally, in the high-orbit space debris rapid traversal space-based optical observation system, the low-orbit observation satellite observes the geosynchronous belt within a first longitude range, and can observe the geosynchronous belt within a longitude of 300° in one orbit.

[0047] Optionally, in the high-orbit space debris rapid traversal space-based optical observation system, the low-orbit observation satellite includes a low-orbit wide-area observation camera, the camera field of view of the low-orbit wide-area observation camera is not less than 20°×40°, and the detection capability is 13Mv within 300ms;

[0048] The low-orbit wide-area observation camera is formed based on the low-orbit field of view stitching method, which includes: according to the distribution of high-orbit fragments, the camera's latitude field of view is set to 40° to ensure coverage of the maximum latitude band; the longitude field of view is set to 20°, so as to utilize the difference in orbital motion between the low orbit and the high orbit to form a large-scale scanning belt, and finally achieve a large-scale coverage of the longitude belt.

[0049] According to the specific content of the above low-orbit field of view stitching method, and the different characteristics of low-orbit observations and cameras on IGSO satellites, a technical effect of low cost and high observation accuracy can be achieved.

[0050] Optionally, in the high-orbit space debris rapid traversal space-based optical observation system, the inclined geosynchronous orbit observation satellite includes 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°×10°, and the detection capability is 15Mv within 300ms;

[0051] The high-orbit wide-area observation camera is formed based on the high-orbit field of view stitching method, which includes: the IGSO satellite can use a 10°×10° camera to stitch and observe back and forth in the east-west direction at the latitude center of the area that the low-orbit satellite cannot see.

[0052] According to the specific content of the high-orbit field of view stitching method, the inclined geosynchronous orbit observation and the cameras on the low-orbit satellite have different characteristics, and the technical effect of low cost and high observation accuracy can be achieved.

[0053] In the high-orbit space debris rapid traversal space-based optical observation system, the inclined geosynchronous orbit observation satellite performs attitude maneuvers and observes in a sky survey mode. During the observation process, the relative movement speed of the debris is compensated by longitude maneuvers. The high-orbit wide-area observation camera adopts a long exposure method to improve the observation capability. The inclined geosynchronous orbit observation satellite observes the second longitude range including a 60-degree backlight blind zone. Finally, the dual-satellite system realizes rapid traversal observation of synchronous belt debris.

[0054] In the high-orbit space debris rapid traversal space-based optical observation system provided by the present invention, the low-orbit observation satellite observes the geosynchronous belt at 0 degree latitude in the near-Earth orbit, so as to coordinate with the observation of the geosynchronous belt in the first longitude range opposite to the backlight blind zone, thereby solving the problem of timeliness of observation of high-orbit debris; the inclined geosynchronous orbit observation satellite observes the geosynchronous belt at 0 degree latitude and in the second longitude range including the backlight blind zone on the inclined geosynchronous orbit, thereby solving the backlight problem in the observation process.

[0055] In summary, the above embodiments describe in detail different configurations of the high-orbit space debris rapid traversal space-based optical observation system. Of course, the present invention includes but is not limited to the configurations listed in the above embodiments, and any content that is transformed based on the configurations provided in the above embodiments belongs to the scope of protection of the present invention. Those skilled in the art can draw inferences based on the contents of the above embodiments.

[0056] In this specification, each embodiment is described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the embodiments can be referred to each other. For the system disclosed in the embodiment, since it corresponds to the method disclosed in the embodiment, the description is relatively simple, and the relevant parts can be referred to the method part.

[0057] The above description is only a description of the preferred embodiments of the present invention, and is not intended to limit the scope of the present invention. Any changes or modifications made by a person skilled in the art in the field of the present invention based on the above disclosure shall fall within the scope of protection of the claims.

Claims

1. A high-orbit space debris rapid traversal space-based optical observation system, characterized in that: include: A low-orbit observation satellite is configured to observe the geosynchronous belt at 0 degrees latitude in a low-Earth orbit to coordinate with the observation of the geosynchronous belt in the first longitude range; an inclined geosynchronous orbit observation satellite configured to observe a geosynchronous belt in a 0 degree latitude and a second longitude range in an inclined geosynchronous orbit; The center point of the first longitude range is opposite to the backlight blind area, and the second longitude range includes the backlight blind area; The low-orbit observation satellite includes a low-orbit wide-area observation camera, the field of view of the low-orbit wide-area observation camera is not less than 20°×40°, and the detection capability is 13Mv within 300ms; The low-orbit wide-area observation camera is formed based on a low-orbit field of view stitching method, which includes: according to the distribution of high-orbit debris, the camera's latitude field of view is set to 40° to ensure coverage of the maximum latitude band; the longitude field of view is set to 20°, and a large-scale scanning belt is formed by using the difference in orbital motion between the low orbit and the high orbit, and finally a large-scale coverage of the longitude belt is achieved; the inclined geosynchronous orbit observation satellite includes 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°×10°, and the detection capability is 15Mv within 300ms; The high-orbit wide-area observation camera is formed based on a high-orbit field of view stitching method, which includes: the IGSO satellite uses a 10°×10° camera to stitch and observe back and forth in the east-west direction at the latitude center of the area that the low-orbit satellite cannot see; and Among them, the low-orbit observation satellite performs attitude maneuvers to enable the low-orbit wide-area observation camera to observe the 0-degree latitude geosynchronous belt in accordance with the step-by-step survey observation mode, and observe the 300° longitude belt in one orbit. A low-orbit observation satellite cooperates to achieve the observation capability of the 300° longitude belt in one orbit.

2. The high-orbit space debris rapid traversal space-based optical observation system according to claim 1, characterized in that: The inclined geosynchronous orbit observation satellite conducts observations in the sky survey mode through attitude maneuvers, observing the 60-degree backlight blind area including the low-orbit observation satellite. Ultimately, the binary satellite system achieves rapid traversal observation of the synchronous belt debris.

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