CN112591146A - Observation method and system for high-orbit target minute-level rapid traversal - Google Patents

Observation method and system for high-orbit target minute-level rapid traversal Download PDF

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CN112591146A
CN112591146A CN202011522858.6A CN202011522858A CN112591146A CN 112591146 A CN112591146 A CN 112591146A CN 202011522858 A CN202011522858 A CN 202011522858A CN 112591146 A CN112591146 A CN 112591146A
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CN112591146B (en
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王鲲鹏
余汉晨
郑珍珍
董磊
段美亚
陈起行
王东亚
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63921 Troops of PLA
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    • B—PERFORMING OPERATIONS; TRANSPORTING
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    • B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
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Abstract

The embodiment of the invention relates to an observation method and system for quickly traversing a high orbit target in minute level, wherein the method comprises the following steps: setting the observation capability of an observation system according to the observation area and the coverage requirement of the observation target; sending the observation system to a quasi GEO orbit as an initial observation point; constructing a multi-satellite observation system with the total number of stars being N by taking the initial observation point as a standard, wherein the system is a constellation which is uniformly distributed on a quasi GEO orbit; if the track inclination angle i is equal to 0 degrees, the system construction is finished; if the inclination angle i is not equal to 0, the platform posture is required to be subjected to adaptive maneuvering, so that the visual axis of each observation point points to a 0-degree synchronous belt region. According to the multi-satellite observation system, the observation field of view forms a gapless observation screen covering a 360-degree GEO zone on the GEO area in real time, the tracks of the GEO target can be completely covered by the gapless observation screen, and the observation method enables the traversal observation period of high-orbit space fragments and the target to enter a minute-level order.

Description

Observation method and system for high-orbit target minute-level rapid traversal
Technical Field
The invention relates to the technical field of space target detection, in particular to an observation method and system for minute-level fast reading traversal of a high-orbit target.
Background
Due to the obvious advantages of the earth synchronous belt satellite in the fields of remote sensing, communication, navigation and the like, the high-orbit satellite generally has great application significance and belongs to high-value space assets. The high-orbit space debris has great threat to the in-orbit safety of high-orbit satellites, particularly to non-geostationary satellites, and once impact occurs, the satellites can fail in advance and other serious adverse effects can be caused. Therefore, the distribution and the change conditions of the high-orbit fragments and the targets are comprehensively monitored, fragment threat early warning information can be timely provided for the high-orbit satellite, and the method has important significance for guaranteeing the safe operation environment of the high-orbit satellite. In addition, cataloging observation on the high-orbit targets is a necessary way for comprehensively mastering the movement of the high-orbit space satellite.
The space-based optical high-orbit debris and the target catalogs and observes the requirement of three high and one low: high coverage, high time effect, high revisiting and low brightness. If the above requirements are to be met, the space-based observation platform is required to have a large field of view, high detection capability and a high scanning rate. However, in the system for observing the high rail at the low rail, the observation of the fragments and the target in the reverse light region is always restricted by the solar stray light inhibiting capability of the system, the timeliness is in the order of several hours to 1 day, and the requirement of increasing timeliness cannot be met.
The existing space target monitoring satellite MSX-SBV can observe 17.8% of targets and does not meet any requirement of three high and one low; the newly-built SBSS system catalog updating period is 1 day, and the high aging requirement is difficult to achieve; the newly-built ORS-5 system adopts a TDI push-sweep mode, can complete one-time scanning on the whole synchronous Earth Orbit (Geosynchronous Earth Orbit, GEO for short) band every 100 minutes, and is difficult to break through 1 Orbit period due to timeliness. In addition, the observation system is required to operate in a zero-inclination orbit, the emission difficulty is high, and the matching requirement of a Time Delay Integration (TDI) push-sweep mode on the motion characteristic of the target is extremely high. In order to meet the continuously improved high-efficiency coverage requirements of high-orbit space debris and targets, a high-orbit observation system is designed.
Based on the above, in the prior art, the high-orbit synchronous belt fragments and the target observation system are limited by backlight observation, and the timeliness cannot break through the problem of several hours of magnitude.
The above drawbacks are expected to be overcome by those skilled in the art.
Disclosure of Invention
Technical problem to be solved
In order to solve the problems, the invention provides an observation method and system for high-orbit target minute-level fast reading traversal, and solves the problems that in the prior art, high-orbit synchronous belt fragments and a target observation system are limited by backlight observation, and timeliness cannot break through several hours of levels.
(II) technical scheme
In order to achieve the purpose, the invention adopts the main technical scheme that:
an embodiment of the present invention provides an observation method for minute-level fast reading traversal of a high-orbit target, including:
s1, setting the observation capability of the observation system according to the observation area and the coverage requirement of the observation target;
s2, sending the observation system to a quasi GEO orbit to serve as an initial observation point;
s3, constructing a constellation, with the total star number of N, of the multi-star observation system uniformly distributed on the quasi-GEO orbit by taking the initial observation point as a standard;
and S4, judging whether the inclination angle of the orbit of the constellation is 0, if not, adjusting the observation platform to enable the visual axis to always point to the GEO band of 0 degree.
In one embodiment of the invention, the observation capability includes an observation field and a detection sensitivity, the angle of the observation field is an included angle formed by a field near edge, a field far edge and an observation point, and is 2 θ, the detection sensitivity is represented by a diameter of a target to be detected at a preset observation distance, and is mutually constrained with the total star number of the system, the angle of the observation field and the installation azimuth angle of the observation system.
In one embodiment of the present invention, step S1 includes:
according to the observed target latitude
Figure BDA0002849733570000021
Determining the south-north height corresponding to the observed target as
Figure BDA0002849733570000022
Figure BDA0002849733570000023
Wherein R isgeoIs the radius of a standard GEO orbit;
determining an observation distance according to the mounting system included angle alpha, wherein the observation distance comprises an observation distance L along the visual axisAB＝2RgeoSin α, near-edge observation distance L along the field of viewmin＝2RgeoSin (α - θ), distance L observed along the far side of the field of viewmax＝2Rgeo·sin(α+θ)；
Determining the size of a coverage area in the longitude direction as 4 theta according to the angle 2 theta of the observation field, and determining the north-south height H of the coverage area along the visual axis in the latitude directionB＝±LABTan θ, north-south height H of the near-edge coverage area along the field of viewmin＝±LminTan θ, north-south height H of the near-edge coverage area along the field of viewmax＝±LmaxTan θ, where O is the center of the quasi-GEO orbit, C is the near edge of the field of view, and D is the far edge of the field of view.
In one embodiment of the invention, the installation azimuth angle alpha, the angle theta of the observation field and the observation target latitude
Figure BDA0002849733570000031
Satisfies the relationship:
Figure BDA0002849733570000032
wherein the range of the installation azimuth angle alpha is theta to (81.3-theta).
In one embodiment of the invention, the quasi GEO orbit is a standard GEO orbit or an orbit having a preset height difference from the standard GEO orbit.
In an embodiment of the invention, the value range of the preset height difference is 20-100 km.
In an embodiment of the present invention, the value of N in step S3 is required to satisfy that the observation fields formed by the N-star observation system are overlapped and cover the GEO target zone, and the method further includes:
and forming a synchronous belt observation screen by using the N distributed observation view fields.
In an embodiment of the present invention, two adjacent observation systems in a constellation are respectively located at a first node and a second node, where the first node is located at β 1, and the second node is located at β 2;
the visual axis position of the first node is beta 1+2 alpha, the near edge position of the visual field is beta 1+2 (alpha-theta), and the far edge position of the visual field is beta 1+2 (alpha + theta);
the visual axis position of the second node is beta 2+2 alpha, the near edge position of the visual field is beta 2+2 (alpha-theta), and the far edge position of the visual field is beta 2+2 (alpha + theta);
the overlapping requirement of the observation field formed by the N-star observation system is that the far edge position of the field of view of the first node is overlapped with the position of the second node, and the requirements are met:
β1+2(α+θ)＝β2+2α；
and determining that the ideal phase difference of the two nodes satisfies the conditions that delta beta is 360 DEG/N is 2 theta.
In one embodiment of the present invention, the preset requirement in step S4 is that the inclination angle 0 ≦ i ≦ 30.
Another embodiment of the present invention further provides an observation system for fast minute-level traversal of a high-orbit target, including:
the system comprises an observation platform and a multi-satellite observation system with the total number of N arranged on the observation platform;
the multi-satellite observation system comprises constellations which are uniformly distributed on a quasi GEO orbit, wherein the constellations are distributed on the orbit with the inclination angle meeting the preset requirement, and the preset requirement is that the inclination angle is not less than 0 and not more than i and not more than 30.
(III) advantageous effects
The invention has the beneficial effects that: according to the observation method and the observation system for the high-orbit target minute-level rapid traversal, provided by the embodiment of the invention, the constellations of the multi-satellite observation system with the total star number of N and uniformly distributed on the quasi-GEO orbit are constructed on the quasi-GEO orbit, the observation field of the multi-satellite observation system forms a gapless observation screen covering a GEO zone of 360 degrees on a GEO area in real time, the tracks of the GEO target can be completely covered by the gapless observation screen, and the observation method enables the traversal observation period of high-orbit space fragments and the target to enter the minute-level order.
Drawings
Fig. 1 is a flowchart illustrating steps of an observation method for minute-level fast reading traversal of a high-orbit target according to an embodiment of the present invention;
FIG. 2 is a schematic plan view of an observation process in an embodiment of the present invention;
FIG. 3 is a schematic view of the observation field principle according to the embodiment of the present invention;
FIG. 4 is a schematic view of a single star observation point field of view in an embodiment of the present invention;
fig. 5 is a schematic view of an observation screen of the multi-satellite observation system when N is 16 in the embodiment of the present invention;
fig. 6 is a schematic diagram of coverage of a GEO target zone by the multi-satellite observation system when N is 16 in the embodiment of the present invention;
fig. 7 is a schematic view of an observation screen of a multi-satellite observation system when i is 15 °;
fig. 8 is a schematic diagram of coverage of a GEO target zone by the multi-satellite observation system when i is 15 ° in the embodiment of the present invention;
fig. 9 is a schematic view of an observation screen of a multi-star observation system when i is 28 °;
fig. 10 is a schematic diagram of coverage of a GEO target zone by the multi-satellite observation system when i is 28 ° in the embodiment of the present invention;
fig. 11 is a schematic diagram illustrating a high-orbit target minute-level fast traversal observation system according to another embodiment of the present invention.
Detailed Description
For the purpose of better explaining the present invention and to facilitate understanding, the present invention will be described in detail by way of specific embodiments with reference to the accompanying drawings.
All technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. The terminology used in the description of the invention herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items.
In order to meet the ever-increasing requirements of high-orbit space debris and high-time coverage of targets, high-orbit observation system design is required. The invention utilizes space-based optical observation means to detect the earth synchronous belt target with high coverage, high time efficiency, high revisiting and low brightness, thereby achieving (near) real-time observation capability.
Fig. 1 is a flowchart of steps of an observation method for a high-orbit target minute-level fast-reading traversal provided by an embodiment of the present invention, as shown in fig. 1, specifically including the following steps:
in step S1, the observation capability of the observation system is set according to the observation area in combination with the coverage requirement for the observation target;
in step S2, the observation system is sent to the quasi GEO orbit as an initial observation point;
in step S3, a constellation of the multi-satellite observation system with the total number of stars N evenly distributed on the quasi GEO orbit is constructed with the initial observation point as a standard;
in step S4, it is determined whether the orbit inclination of the constellation is 0, and if not, the observation platform is adjusted so that the visual axis always points to the 0 ° GEO band.
Based on the observation method provided by the invention, the traversal observation period of the fragments and the targets in the high orbit space enters a minute-level order, a gapless observation screen covering a GEO zone of 360 degrees is formed on the GEO area in real time by the observation field of the multi-satellite observation system, and the tracks of the GEO targets can be completely covered by the gapless observation screen.
The above method is described in detail with reference to the steps shown in fig. 1:
in step S1, the observation capability of the observation system is set in accordance with the observation region and the coverage requirement for the observation target.
In an embodiment of the present invention, the observation capability in this step includes an observation field and a detection sensitivity, an angle of the observation field is an included angle formed by a near edge of the field, a far edge of the field and an observation point, and is 2 θ, and the detection sensitivity is represented by a diameter of an object to be detected at a preset observation distance and is mutually constrained with a total star number of the system, an angle of the observation field, and an installation azimuth of the observation system.
Fig. 2 is a schematic plan view of an observation process in an embodiment of the present invention, as shown in fig. 2, a is a position of an observation system, i.e., an observation point position, C is a near side of a field of view, D is a far side of the field of view, B is a field of view axis, O is a center of a quasi GEO orbit, an X axis direction is a tangential position of the observation point, θ is an angle of the observation field of view, and α is an installation azimuth angle of an observation platform, i.e., an included angle between a visual axis of the observation field of view and an X axis of a VVLH coordinate system, where X in the VVLH coordinate system is the same as a velocity direction. FIG. 3 is a schematic view of the observation field of view principle of the embodiment of the present invention, where E and F are the upper and lower edge points of the visual axis, and the distance between EF is the height H in the latitudinal direction along the north-south direction of the coverage area of the visual axisB。
Step S1 is specifically set as follows:
determining the south-north height corresponding to the observation target according to the latitude of the observation target, wherein the latitude of the observation target is
Figure BDA0002849733570000061
Then the corresponding north-south height
Figure BDA0002849733570000062
Wherein R isgeoIs the radius of a standard GEO orbit;
determining an observation distance according to an included angle of the installation system, observing an included angle alpha between a visual axis of a visual field and an X axis of a VVLH coordinate system, and observing a distance L along the visual axisAB＝2RgeoSin α, near-edge observation distance L along the field of viewmin＝2RgeoSin (α - θ), distance observation along the far side of the field of viewLmax＝2Rgeo·sin(α+θ)；
Determining a covered area in the longitude direction of the visual field according to the observation visual field angle, if the observation visual field angle is 2 theta, the covered area in the longitude direction has the size of ═ COD ═ 4 theta, and the south-north height H in the latitude direction along the visual axis covered areaB＝±LABTan θ, north-south height H of the near-edge coverage area along the field of viewmin＝±LminTan θ, north-south height H of the near-edge coverage area along the field of viewmax＝±LmaxTan θ, where O is the center of the quasi-GEO orbit, C is the near edge of the field of view, and D is the far edge of the field of view.
In one embodiment of the present invention, H needs to be satisfied for a single-star observation systemminH, mounting azimuth angle alpha, angle theta of observation field and observation target latitude
Figure BDA0002849733570000071
Satisfies the relationship:
Figure BDA0002849733570000072
considering that the earth can be regarded as a surface target in the system of the present invention, the installation azimuth α cannot be infinite to avoid the influence of stray light.
For example, α may be 45 °, for meeting the requirement of covering a ± 15 ° GEO target area, the half-field of view θ is equal to or greater than 15 °, that is, the field of view in the latitudinal direction should exceed 30 °, the requirement for detection capability is high, and a single star cannot realize full coverage in the longitudinal direction on the GEO target area. The multi-satellite observation system can reduce the requirement on observation view field and realize the full coverage of the GEO target area in the longitude direction by the field complementation of adjacent observation nodes.
In step S2, the observation system is sent to the quasi GEO orbit as an initial observation point.
In an embodiment of the present invention, the quasi GEO orbit may be a standard GEO orbit, or may be a height difference having a preset height difference from the standard GEO orbit. The value range of the preset height difference is 20-100 km, for example, 20km, 50km, 100km and the like.
Fig. 4 is a schematic view of a single-star observation point field of view in the embodiment of the present invention, and as shown in fig. 4, the observation system in the first step is launched to a quasi GEO orbit to form an initial observation node, so as to ensure that the observation field of view is completely within a GEO zone.
In step S3, a constellation of the multi-star observation system with the total number of stars N uniformly distributed on the quasi GEO orbit is constructed using the initial observation point as a standard.
In an embodiment of the invention, the value of N in step S3 needs to satisfy that the observation fields formed by the N-star observation system overlap each other and cover the GEO target belt, and then the synchronous belt observation screen is formed by using the N distributed observation fields. For example, the value of N may be 16 or 18, or selected as desired. The value of N is based on the observation field fully covering the GEO target zone, the adjacent observation fields are overlapped front and back to avoid blank areas, and the target is observed in real time by using the opportunity that the satellite passes through the observation screen.
Fig. 5 is a schematic view of an observation screen of a multi-satellite observation system when N is 16 in an embodiment of the present invention, as shown in fig. 5, taking two adjacent observation systems in a constellation as a first node (i.e., node 1) and a second node (i.e., node 2) respectively, where the first node is β 1 (not shown in the figure), the second node is β 2 (not shown in the figure), and a requirement that observation fields formed by the N-satellite observation systems overlap each other is that a far edge position of a field of view of the first node overlaps the second node.
The principle that the node 1 and the node 2 are mutually overlapped in observation view fields is that the far edge coverage position of the view field of the node 1 is near the visual axis coverage position of the node 2, namely the view field size is required to meet the requirement
Figure BDA0002849733570000081
Take α as 45 ° as an example when
Figure BDA0002849733570000082
Then θ min ≈ 10 °.
Nodes 1 and 2 are positioned at β 1 and β 2, respectively, with a phase difference Δ β of 360 °/N. The observation ranges of the nodes 1 and 2 are respectively as follows:
and the node 1: a visual axis β 1+2 α, a visual field near side β 1+2(α - θ), and a visual field far side β 1+2(α + θ);
and (3) the node 2: a visual axis β 2+2 α, a visual field near side β 2+2(α - θ), and a visual field far side β 2+2(α + θ);
then according to the overlapping principle of the coverage range of the adjacent detection view fields, the following requirements are met:
β1+2(α+θ)＝β2+2α，
namely, the ideal phase difference of the two nodes is determined to satisfy the conditions that delta beta is 360 degrees/N is 2 theta.
When θ is 10 °, Δ β is 20 °, and N is 18, the adjacent observation nodes just satisfy the condition that the far-edge coverage position of the view field of the node 1 is at the view-axis coverage position of the node 2. Considering further the optimization of the system scale, when N is 16, Δ β is 22.5 °, compared to when N is 18, Δ β is 20 °, which is only 2.5 ° different, the coverage benefit of both approaches. Considering comprehensively, the value of N may be 16.
Fig. 6 is a schematic diagram of coverage of the GEO target belt by the multi-satellite observation system when N is 16 in the embodiment of the present invention, such as the synchronous belt observation screen shown in fig. 6.
In step S4, it is determined whether the constellation is distributed on a geosynchronous orbit whose inclination meets a preset requirement, and if so, the observation platform is adjusted, where the preset requirement is that the inclination i is greater than or equal to 0.
In an embodiment of the present invention, if the constellation is distributed on the orbit with the inclination angle i equal to 0, the observation screen can be formed without the maneuvering cooperation of the satellite attitude; if the constellation is distributed on the orbit i ≠ 0, the platform calculates the attitude adjustment amount according to the current position of the platform in the inertial space and the target position with the GEO synchronous belt of 0 degree as the pointing center, and the observation visual axis of the platform always points to the GEO synchronous belt of 0 degree during the orbit through the attitude maneuver of the platform, so that the constellation coverage range is ensured to realize 360-degree coverage observation on the designated high-orbit airspace.
In one embodiment of the invention, the tilt angle mainly affects the detection capability (i.e. sensitivity), the maneuvering pointing capability of the observation platform, etc. Because the distribution range of the main inclination angle of the current GEO target is 0-60 degrees, the inclination angle of the track where the observation system is located is required to be 0-60 degrees, but the larger the inclination angle is, the larger the change of the single coverage condition of the GEO synchronous belt of the field of view towards 0 degrees along with the in-orbit operation of the satellite is, the instable overall coverage of the system can be caused, and the final inclination angle range is 0-30 degrees.
In the first embodiment, assuming that N is 16, the description will be given in the case where i is 15 ° or 28 ° in the range of 0 ≦ i ≦ 30:
fig. 7 is a schematic view of an observation screen of the multi-satellite observation system at an i-15 ° time in the embodiment of the present invention, and fig. 8 is a schematic view of coverage of the GEO target zone by the multi-satellite observation system at an i-15 ° time in the embodiment of the present invention. Fig. 9 is a schematic view of an observation screen of the multi-satellite observation system when i is 28 °, and fig. 10 is a schematic view of coverage of the GEO target zone by the multi-satellite observation system when i is 28 °.
Fig. 11 is a schematic diagram of a high-orbit target minute-level fast traversal observation system according to another embodiment of the present invention, as shown in fig. 11, the system 110 includes: an observation platform 111 and a multi-star observation system 112 with the total number of stars being N, which is arranged on the observation platform; the multi-satellite observation system is uniformly distributed on the constellation on the quasi GEO orbit, the constellation is distributed on the orbit with the inclination angle meeting the preset requirement, and the preset requirement is that the inclination angle i is more than or equal to 0.
The observation method and the observation system for the minute-level fast reading traversal of the high-orbit target provided by the embodiment of the invention have the following effects:
the observation method provided by the invention enables the traversal observation period of the high-orbit space debris and the target to enter the minute-level order, breaks through the timeliness constraint of the order of hours, and improves the timeliness;
the observation system provided by the invention can continuously observe a designated high-orbit airspace through the attitude maneuver of the satellite platform, and has strong operability;
the observation system provided by the invention is ideally distributed on the quasi-geosynchronous orbit with the inclination angle of 0 degree, can be popularized and applied to the quasi-geosynchronous orbit with the inclination angle of more than 0 degree, and has wide applicability.
It should be noted that although in the above detailed description several modules or units of the device for action execution are mentioned, such a division is not mandatory. Indeed, the features and functionality of two or more modules or units described above may be embodied in one module or unit, according to embodiments of the invention. Conversely, the features and functions of one module or unit described above may be further divided into embodiments by a plurality of modules or units.
Through the above description of the embodiments, those skilled in the art will readily understand that the exemplary embodiments described herein may be implemented by software, or by software in combination with necessary hardware. Therefore, the technical solution according to the embodiment of the present invention can be embodied in the form of a software product, which can be stored in a non-volatile storage medium (which can be a CD-ROM, a usb disk, a removable hard disk, etc.) or on a network, and includes several instructions to enable a computing device (which can be a personal computer, a server, a touch terminal, or a network device, etc.) to execute the method according to the embodiment of the present invention.
Other embodiments of the invention will be apparent to those skilled in the art from consideration of the specification and practice of the invention disclosed herein. This application is intended to cover any variations, uses, or adaptations of the invention following, in general, the principles of the invention and including such departures from the present disclosure as come within known or customary practice within the art to which the invention pertains. It is intended that the specification and examples be considered as exemplary only, with a true scope and spirit of the invention being indicated by the following claims.
It will be understood that the invention is not limited to the precise arrangements described above and shown in the drawings and that various modifications and changes may be made without departing from the scope thereof. The scope of the invention is limited only by the appended claims.

Claims (10)

1. An observation method for quickly traversing a high-orbit target in minute level is characterized by comprising the following steps:
s1, setting the observation capability of the observation system according to the observation area and the coverage requirement of the observation target;
s2, sending the observation system to a quasi GEO orbit to serve as an initial observation point;
s3, constructing a constellation, with the total star number of N, of the multi-star observation system uniformly distributed on the quasi-GEO orbit by taking the initial observation point as a standard;
and S4, judging whether the inclination angle of the orbit of the constellation is 0, if not, adjusting the observation platform to enable the visual axis to always point to the GEO band of 0 degree.
2. The observation method for minute-scale fast traversal of the high-orbit target as claimed in claim 1, wherein the observation capability includes an observation field and a detection sensitivity, the angle of the observation field is an included angle formed by a near edge of the field, a far edge of the field and an observation point, and is 2 θ, the detection sensitivity is represented by a diameter of a target to be detected at a preset observation distance, and is mutually constrained with the total star number of the system, the angle of the observation field and an installation azimuth of the observation system.
3. The observation method for high-orbit target minute-level fast traversal according to claim 2, wherein the step S1 comprises:
according to the observed target latitude
Figure FDA0002849733560000011
Determining the south-north height corresponding to the observed target as
Figure FDA0002849733560000012
Figure FDA0002849733560000013
Wherein R isgeoIs the radius of a standard GEO orbit;
determining an observation distance according to the mounting system included angle alpha, wherein the observation distance comprises an observation distance L along the visual axisAB＝2RgeoSin α, near-edge observation distance L along the field of viewmin＝2RgeoSin (α - θ), distance L observed along the far side of the field of viewmax＝2Rgeo·sin(α+θ)；
Determining the size of a coverage area in the longitude direction as 4 theta according to the angle 2 theta of the observation field, and determining the north-south height H of the coverage area along the visual axis in the latitude directionB＝±LABTan θ, north-south height H of the near-edge coverage area along the field of viewmin＝±LminTan θ, north-south height H of the near-edge coverage area along the field of viewmax＝±LmaxTan θ, where O is the center of the quasi-GEO orbit, C is the near edge of the field of view, and D is the far edge of the field of view.
4. The observation method for minute-scale fast traversal of an elevated rail target according to claim 3, wherein the installation azimuth α, the angle θ of the observation field, and the latitude of the observation target
Figure FDA0002849733560000014
Satisfies the relationship:
Figure FDA0002849733560000021
wherein the range of the installation azimuth angle alpha is theta to (81.3-theta).
5. The method for minute-scale fast traversal of an upper-rail target according to claim 1, wherein the quasi-GEO orbit is a standard GEO orbit or an orbit having a preset height difference from the standard GEO orbit.
6. The method for observing high-orbit target minute-scale rapid traversal of claim 5, wherein the preset height difference ranges from 20km to 100 km.
7. The observation method of high-orbit target minute-scale rapid traversal according to claim 1, wherein the value of N in step S3 is required to satisfy that observation fields formed by N-star observation systems are overlapped and cover a GEO target zone, and further comprising:
and forming a synchronous belt observation screen by using the N distributed observation view fields.
8. The observation method for minute-scale fast traversal of the high-orbit target of claim 7, wherein two adjacent observation systems in the constellation are respectively located at a first node and a second node, the first node is β 1, and the second node is β 2;
the visual axis position of the first node is beta 1+2 alpha, the near edge position of the visual field is beta 1+2 (alpha-theta), and the far edge position of the visual field is beta 1+2 (alpha + theta);
the visual axis position of the second node is beta 2+2 alpha, the near edge position of the visual field is beta 2+2 (alpha-theta), and the far edge position of the visual field is beta 2+2 (alpha + theta);
the overlapping requirement of the observation field formed by the N-star observation system is that the far edge position of the field of view of the first node is overlapped with the position of the second node, and the requirements are met:
β1+2(α+θ)＝β2+2α；
and determining that the ideal phase difference of the two nodes satisfies the conditions that delta beta is 360 DEG/N is 2 theta.
9. The observation method for minute-scale fast traversal of an on-orbit target according to claim 1, wherein the preset requirement in step S4 is that the inclination angle 0 ≦ i ≦ 30.
10. An observation system for minute-level fast traversal of an upper-orbit target, comprising:
the system comprises an observation platform and a multi-satellite observation system with the total number of N arranged on the observation platform;
the multi-satellite observation system comprises constellations which are uniformly distributed on a quasi GEO orbit, wherein the constellations are distributed on the orbit with the inclination angle meeting the preset requirement, and the preset requirement is that the inclination angle is not less than 0 and not more than i and not more than 30.
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Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113325704A (en) * 2021-04-25 2021-08-31 北京控制工程研究所 Spacecraft backlight approaching intelligent orbit control method and device and storage medium
CN113619813A (en) * 2021-09-17 2021-11-09 中国科学院微小卫星创新研究院 High-orbit space debris fast traversal space-based optical observation system and method
CN115465475A (en) * 2022-11-02 2022-12-13 哈尔滨工业大学 Inverse orbit intersection detection method and device for large-scale constellation and storage medium
CN115583369A (en) * 2022-10-11 2023-01-10 中国人民解放军63921部队 Ubiquitous perception observation method for GEO space debris by low-orbit multi-observation platform
CN115683090A (en) * 2022-10-11 2023-02-03 中国人民解放军63921部队 Method for observing GEO band target in full coverage mode through multiple observation platforms on sun synchronous track in morning and evening

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100063733A1 (en) * 2008-09-09 2010-03-11 Thomas Patrick Yunck Cellular Interferometer for Continuous Earth Remote Observation (CICERO)
US20110049302A1 (en) * 2009-08-26 2011-03-03 Raytheon Company Retro-Geo Spinning Satellite Utilizing Time Delay Integration (TDI) for Geosynchronous Surveillance
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
CN104077364A (en) * 2014-06-11 2014-10-01 上海微小卫星工程中心 Earth limb observation method
CN109583055A (en) * 2018-11-15 2019-04-05 中国人民解放军61646部队 A kind of Track of Sub-Satellite Point distribution optimization method of adjustment based on covering circle
CN109977456A (en) * 2019-01-31 2019-07-05 上海卫星工程研究所 Satellite Networking scheme aided design system towards observation mission
CN110017815A (en) * 2019-04-30 2019-07-16 北京空间飞行器总体设计部 A kind of construction method of Space-based Space Surveillance photoelectric fencing system
CN110954087A (en) * 2019-12-16 2020-04-03 中国科学院微小卫星创新研究院 System with high coverage rate for observing space target
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

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100063733A1 (en) * 2008-09-09 2010-03-11 Thomas Patrick Yunck Cellular Interferometer for Continuous Earth Remote Observation (CICERO)
US20110049302A1 (en) * 2009-08-26 2011-03-03 Raytheon Company Retro-Geo Spinning Satellite Utilizing Time Delay Integration (TDI) for Geosynchronous Surveillance
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
CN104077364A (en) * 2014-06-11 2014-10-01 上海微小卫星工程中心 Earth limb observation method
CN109583055A (en) * 2018-11-15 2019-04-05 中国人民解放军61646部队 A kind of Track of Sub-Satellite Point distribution optimization method of adjustment based on covering circle
CN109977456A (en) * 2019-01-31 2019-07-05 上海卫星工程研究所 Satellite Networking scheme aided design system towards observation mission
CN110017815A (en) * 2019-04-30 2019-07-16 北京空间飞行器总体设计部 A kind of construction method of Space-based Space Surveillance photoelectric fencing system
CN110954087A (en) * 2019-12-16 2020-04-03 中国科学院微小卫星创新研究院 System with high coverage rate for observing space target
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

Non-Patent Citations (6)

* Cited by examiner, † Cited by third party
Title
张科科,朱振才,周美江,胡海鹰,陈宏宇: "高轨目标监视***星座设计和探测效能分析", 《宇航学报》 *
张科科,朱振才,周美江,胡海鹰,陈宏宇: "高轨目标监视***星座设计和探测效能分析", 《宇航学报》, vol. 39, no. 07, 30 July 2018 (2018-07-30) *
潘晓刚,李济生,段晓君,周海银: "天基空间目标监视与跟踪***轨道确定技术研究", 《自然科学进展》 *
潘晓刚,李济生,段晓君,周海银: "天基空间目标监视与跟踪***轨道确定技术研究", 《自然科学进展》, no. 11, 15 November 2008 (2008-11-15), pages 1 - 7 *
牛照东,汪琳,段宇,潘嘉蒙,陈曾平: "国外地球同步轨道目标天基光学监视策略", 《中国光学》 *
牛照东,汪琳,段宇,潘嘉蒙,陈曾平: "国外地球同步轨道目标天基光学监视策略", 《中国光学》, vol. 10, no. 03, 15 June 2017 (2017-06-15), pages 314 *

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113325704A (en) * 2021-04-25 2021-08-31 北京控制工程研究所 Spacecraft backlight approaching intelligent orbit control method and device and storage medium
CN113325704B (en) * 2021-04-25 2023-11-10 北京控制工程研究所 Spacecraft backlighting approaching intelligent orbit control method, device and storage medium
CN113619813A (en) * 2021-09-17 2021-11-09 中国科学院微小卫星创新研究院 High-orbit space debris fast traversal space-based optical observation system and method
CN113619813B (en) * 2021-09-17 2022-08-26 中国科学院微小卫星创新研究院 High-orbit space debris fast traversing space-based optical observation system and method
CN115583369A (en) * 2022-10-11 2023-01-10 中国人民解放军63921部队 Ubiquitous perception observation method for GEO space debris by low-orbit multi-observation platform
CN115683090A (en) * 2022-10-11 2023-02-03 中国人民解放军63921部队 Method for observing GEO band target in full coverage mode through multiple observation platforms on sun synchronous track in morning and evening
CN115465475A (en) * 2022-11-02 2022-12-13 哈尔滨工业大学 Inverse orbit intersection detection method and device for large-scale constellation and storage medium
CN115465475B (en) * 2022-11-02 2023-03-10 哈尔滨工业大学 Inverse orbit intersection detection method and device for large-scale constellation and storage medium

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