CN110017815A - A kind of construction method of Space-based Space Surveillance photoelectric fencing system - Google Patents
A kind of construction method of Space-based Space Surveillance photoelectric fencing system Download PDFInfo
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- CN110017815A CN110017815A CN201910364755.2A CN201910364755A CN110017815A CN 110017815 A CN110017815 A CN 110017815A CN 201910364755 A CN201910364755 A CN 201910364755A CN 110017815 A CN110017815 A CN 110017815A
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- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C11/00—Photogrammetry or videogrammetry, e.g. stereogrammetry; Photographic surveying
Abstract
The invention discloses a kind of construction methods of Space-based Space Surveillance photoelectric fencing system, comprising: according to observation object parameter information and observation satellite parameter information, determines observation initial parameter；According to the observation initial parameter, observed range and observation angle are determined；According to the observed range and observation angle, loading demands are determined；According to the loading demands, Space-based Space Surveillance photoelectric fencing system is constructed.The Space-based Space Surveillance photoelectric fencing system constructed through the invention arranges more observation satellites in same orbital plane, the observation scope of every observation satellite intersects with adjacent observation satellite, form an observation annulus, guarantee that the observation of high timeliness can may be implemented by observing annulus in the every circle of extraterrestrial target run in low rail.
Description
Technical field
The invention belongs to Space-based Space monitoring technical field more particularly to a kind of Space-based Space Surveillance photoelectricity hedges
The construction method of basketry system.
Background technique
Extraterrestrial target monitoring system mainly has two kinds of forms of ground and space-based.Currently, Chinese Space target monitoring system master
Low-level devices are relied on, since ground base fabric station range is very limited, so that when the detection of China's ground extraterrestrial target monitoring system
Between and spatial coverage be difficult to be promoted.
Extraterrestrial target is detected and is tracked using ground based system, the advantages of this mode be technology maturation, investment at
This is low, but is limited by a variety of conditions: (1) geographical location limits: in the high rail of ground location or geostationary orbit target, ground
Monitoring station must be all over the world, serious by territory restriction, it is difficult to continuous monitoring, tracking and accurate spy of the realization to space-based target
Sign measurement；(2) time restriction: ground optical observation equipment can only be illuminated in target by sunlight, and measuring station is in earth's shadow
In period in morning and evening, weather it is fine when could work, be not able to satisfy the requirement of high timeliness detection.
Compared with ground based system, space-base monitoring system have the advantages that (1) space-base monitoring system not by geographical location and
Meteorological condition limitation, and can be from different azimuthal observation targets；(2) when space-base monitoring, echo signal without atmospheric attenuation,
Space-base monitoring has higher signal-to-noise ratio than ground based observa tion；(3) space-base monitoring system is in orbit, it is only necessary to which a star can be complete
The covering of entire geostationary orbit in pairs.
Space-based Space monitoring system is the extension and supplement of foundation detection system, can effectively promote China to space mesh
Mark the spreadability, timeliness and cataloguing precision of monitoring.But there are rulers relative to ground based system for Space-based Space monitoring system
The conditionalities such as very little weight, so optimization design and effectiveness analysis must be carried out under the conditions of resource is limited.
Summary of the invention
Technology of the invention solves the problems, such as: overcoming the deficiencies of the prior art and provide a kind of Space-based Space Surveillance photoelectricity
The construction method of fencing system, to realize the observation of high timeliness.
In order to solve the above-mentioned technical problem, the invention discloses a kind of structures of Space-based Space Surveillance photoelectric fencing system
Construction method, comprising:
According to observation object parameter information and observation satellite parameter information, observation initial parameter is determined；Wherein, the observation
Initial parameter, comprising: observation bound, observation satellite orbit altitude and observation satellite quantity；
According to the observation initial parameter, observed range and observation angle are determined；
According to the observed range and observation angle, loading demands are determined；
According to the loading demands, Space-based Space Surveillance photoelectric fencing system is constructed；Wherein, space-based space mesh
Mark monitoring photoelectric fencing system arranges more observation satellites in same orbital plane, the observation scope of every observation satellite with it is adjacent
Observation satellite intersection, forms an observation annulus.
It is described to be believed according to observation object parameter in the construction method of above-mentioned Space-based Space Surveillance photoelectric fencing system
Breath and observation satellite parameter information determine observation initial parameter；Wherein, the observation initial parameter, comprising:
According to the height of observation object, the observation bound is determined；
According to static coverage rate demand, observation satellite quantity is determined；
According to observation satellite quantity, observation satellite orbit altitude is determined.
In the construction method of above-mentioned Space-based Space Surveillance photoelectric fencing system, the height according to observation object
Degree, determines the observation bound, comprising:
It is for statistical analysis to the height distribution of observation object, determine the distribution density of different height observation object；
According to the distribution density of determining different height observation object, observation bound needed for determining observation, to guarantee
Given threshold is greater than to the coverage rate of observation object.
In the construction method of above-mentioned Space-based Space Surveillance photoelectric fencing system, according to static coverage rate demand, really
Determine observation satellite quantity, comprising:
Work as he≥hlWhen, static coverage rate γsAre as follows:
Work as he< hlWhen, static coverage rate γsAre as follows:
According to static coverage rate demand, the minimum number n of required observation satellite is determined；
Wherein, heIndicate that the earth faces side, hlIndicate observation lower limit, ReIndicate earth radius, hhIndicate the observation upper limit.
In the construction method of above-mentioned Space-based Space Surveillance photoelectric fencing system, determine that observation is defended according to the following formula
Star orbit altitude H:
It is described according to the initial ginseng of the observation in the construction method of above-mentioned Space-based Space Surveillance photoelectric fencing system
Number, determines observed range and observation angle, comprising:
According to the observation satellite orbit altitude and observation satellite quantity, according to the observation bound and observation of every satellite
The height of object, determines observed range；
According to the bound of the altitude range of observation object, required observation angle is determined.
It is described according to the observation satellite rail in the construction method of above-mentioned Space-based Space Surveillance photoelectric fencing system
Road height and observation satellite quantity determine observed range according to the observation bound of every satellite and the height of observation object, wrap
It includes:
Observation upper limit h is determined by following formulahRequired upper limit observed range Lh:
Observation lower limit h is determined by following formulalRequired lower limit observed range Ll:
Capping observed range LhWith lower limit observed range LlThe larger value of the two is as the observed range；
Wherein,ReIndicate that earth radius, H indicate observation satellite orbit altitude, n indicates the minimum number of observation satellite
Amount.
In the construction method of above-mentioned Space-based Space Surveillance photoelectric fencing system, the height according to observation object
The bound of range determines required observation angle, comprising:
Pass through minimum observation angle β needed for following formula computed altitude direction:
Minimum observation angle needed for width direction takes 180 °.
In the construction method of above-mentioned Space-based Space Surveillance photoelectric fencing system, it is described according to the observed range and
Observation angle determines loading demands, comprising:
According to the observed range, the observed range requirement of load is determined；
According to observation angle needed for height and width both direction, the visual field of load is determined.
In the construction method of above-mentioned Space-based Space Surveillance photoelectric fencing system, the Space-based Space that constructs
Monitoring photoelectric fencing system includes any at least one in following parameter: observation satellite quantity, observation satellite height, load are seen
Ranging is from, single-point load visual field and load quantity.
The invention has the following advantages that
(1) the Space-based Space Surveillance photoelectric fencing system constructed by the method for the invention, low rail extraterrestrial target covering
Property it is high, around one annulus of formation in the earth one week, the achievable complete monitoring to low rail extraterrestrial target.
(2) the Space-based Space Surveillance photoelectric fencing system constructed by the method for the invention, Space-objects Observation timeliness
Property it is high, revisit time is short.The data update cycle is high, and every enclose of each target can get 2 tracking segmental arcs.Ground-based radar generally can only
Each circle of daily lift rail is covered, about 2 times/day of the update cycle, the program data update cycle is 24 times/day, improves 12 times.
(3) the Space-based Space Surveillance photoelectric fencing system constructed by the method for the invention, observation data distribution are uniform.
Two observation segmental arcs of every circle are uniformly distributed, and to improving, Orbit Determination and Orbit Forecast precision is highly beneficial.
(4) the Space-based Space Surveillance photoelectric fencing system constructed by the method for the invention, round-the-clock work.In the sun
On synchronous morning and evening track, 24 hours continuous observations of extraterrestrial target can not influenced by atmosphere, weather etc..
Detailed description of the invention
The step of Fig. 1 is the construction method of a kind of Space-based Space Surveillance photoelectric fencing system in embodiment of the present invention stream
Cheng Tu；
Fig. 2 is a kind of distribution schematic diagram of the full airspace orbit altitude of extraterrestrial target in the embodiment of the present invention；
Fig. 3 is a kind of schematic diagram of orbit altitude 2000km LEO target below in the embodiment of the present invention；
Fig. 4 is a kind of mutual alignment schematic diagram of adjacent two observation satellites in the embodiment of the present invention；
Fig. 5 is a kind of observed range schematic diagram in the embodiment of the present invention；
Fig. 6 is a kind of list star observation scope schematic diagram in the embodiment of the present invention；
Fig. 7 is that a kind of more stars combine to form observation annulus schematic diagram in the embodiment of the present invention；
Fig. 8 is a kind of low 3 star networking plan schematic diagram of rail in the embodiment of the present invention；
Fig. 9 is a kind of low 4 star networking plan schematic diagram of rail in the embodiment of the present invention；
Figure 10 is a kind of low 6 star networking plan schematic diagram of rail in the embodiment of the present invention.
Specific embodiment
To make the object, technical solutions and advantages of the present invention clearer, below in conjunction with attached drawing to disclosed by the invention
Embodiment is described in further detail.
Referring to Fig.1, a kind of building side of Space-based Space Surveillance photoelectric fencing system in the embodiment of the present invention is shown
The step flow chart of method.The construction method of the Space-based Space Surveillance photoelectric fencing system in the present embodiment, comprising:
Step 101, according to observation object parameter information and observation satellite parameter information, observation initial parameter is determined.
In the present embodiment, which can specifically include: observation bound, observation satellite orbit altitude and
Observation satellite quantity.Specifically, can determine the observation bound according to the height of observation object；According to static coverage rate
Demand determines observation satellite quantity；According to observation satellite quantity, observation satellite orbit altitude is determined.
Preferably, can be for statistical analysis to the distribution of the height of observation object, to determine different height observation object
Distribution density；According to the distribution density of determining different height observation object, observation bound needed for determining observation, to guarantee
Given threshold is greater than to the coverage rate of observation object, that is, guarantee to most targets (generally taking 90%~99% target)
Covering.
Preferably, (1) and (2) minimum number of required observation satellite can be determined according to the following formula
Work as he≥hlWhen, static coverage rate γsAre as follows:
Work as he< hlWhen, static coverage rate γsAre as follows:
As it can be seen that for different observation satellite quantity, available different static coverage rate, according to static coverage rate need
It asks, determines the minimum number n of required observation satellite.Wherein, heIndicate that the earth faces side, hlIndicate observation lower limit, ReIndicate the earth
Radius, hhIndicate the observation upper limit.
Preferably, observation satellite orbit altitude H can be determined by following formula:
Wherein, it should be noted that observation satellite (extraterrestrial target monitoring satellite) orbit altitude mainly considers target (observation
Object) the factors such as orbit altitude, observable angular range, intersatellite communication link, illumination condition.
Spacecraft undergos severe space environment test in space motion.Wherein, from the shock pair of space junk
The operation of spacecraft constitutes serious threat, and space junk and spacecraft can be referred to as to extraterrestrial target, and extraterrestrial target monitoring is answered
Including space junk and in-orbit spacecraft.Wherein, the extraterrestrial target distribution of full airspace orbit altitude is as shown in Figure 2.Orbit altitude
The extraterrestrial target of range is distributed as shown in figure 3, as can be seen from the figure extraterrestrial target is mainly distributed between 200km~2000km
Two altitude ranges of 500km~1000km and 1400km~1600km, wherein 800km height is nearby and the neighbouring mesh of 1400km height
Mark distribution is most.
For low rail extraterrestrial target, be mainly distributed within the scope of 300-1500km, there are 600-800km and
Two peak regions of 1400km and based on 600-800km, in order to shorten observed range, can select within the scope of 600-800km.
As Fig. 4, can only be to satellite and earth tangent line due to being influenced by the earth from the point of view of observable angular range
It more than direction is observed, if satellite altitude is higher, the unobservable region in position is bigger between two stars immediately below satellite, because
This should determine the height of satellite according to number of satellite.
Step 102, according to the observation initial parameter, observed range and observation angle are determined.
It in the present embodiment, can be according to the observation satellite orbit altitude and observation satellite quantity, according to every such as Fig. 5
The observation bound of satellite and the height of observation object, determine observed range；In turn, according to the altitude range of observation object
Bound determines required observation angle.
Preferably, observation upper limit h can be determined by following formulahRequired upper limit observed range Lh:
Observation lower limit h is determined by following formulalRequired lower limit observed range Ll:
In the present embodiment, capping observed range LhWith lower limit observed range LlThe larger value of the two is as the observation
Distance, and there are certain surpluses.Wherein,ReIndicate that earth radius, H indicate observation
Satellite orbital altitude, n indicate the minimum number of observation satellite.
Preferably, required observation angle includes: needed for minimum observation angle and width direction needed for short transverse
Minimum observation angle.
So that realize the detection to 300-1500km, in certain orbit altitude, Cai need to guarantee enough observation angles
The covering to short transverse may be implemented.Minimum observation angle β needed for short transverse can be calculated by following formula:
Minimum observation angle needed for width direction takes 180 °.
It is above-mentioned to give the calculation method of minimum observation angle.The weight in view of observation scope between star is also needed in engineering
It folds, guarantee the factors such as certain observation time, actual observation angle need to increase certain surplus.
Step 103, according to the observed range and observation angle, loading demands are determined.
In the present embodiment, the observed range requirement of load can be determined, wherein load according to the observed range
Observed range requires to should be greater than required observed range.According to observation angle needed for height and width both direction, determines and carry
The visual field of lotus；Generally in such a way that multi-load splices, the visual field of load is made to be greater than required observation visual field.
Step 104, according to the loading demands, Space-based Space Surveillance photoelectric fencing system is constructed.
In the present embodiment, such as Fig. 6 and 7, the Space-based Space Surveillance photoelectric fencing system constructed is in same rail
More observation satellites are arranged on road face, the observation scope of every observation satellite intersects with adjacent observation satellite, forms an observation
Annulus.Wherein, which includes any at least one in following parameter: observation satellite
Quantity, observation satellite height, load observed range, single-point load visual field and load quantity.
On the basis of the above embodiments, it is illustrated below with reference to a specific example.
To 3 stars, 4 stars, 6 stars, allocation plan has carried out preliminary analysis under multiple orbital attitudes respectively.Assuming that static covering
Rate demand is 95% or more.
3 star networking plans are illustrated in fig. 8 shown below, 120 ° of phase intervals between star, and every star covers each 60 ° of ranges in two sides.As it can be seen that
When number of satellite is 3, required satellite altitude is 1102km, and static coverage rate is 90.2%, and lower limit observed range is 7113km, on
Limit observed range is 7967km, and required observed range at least 7967km, width direction observation angle is 11.2 °.
4 star networking plans are illustrated in fig. 9 shown below, 90 ° of phase intervals between star, and every star covers each 45 ° of ranges in two sides.As it can be seen that
When number of satellite is 4, required satellite altitude is 634km, and static coverage rate is 97%, and lower limit observed range is 5248km, the upper limit
Observed range is 6023km, required observed range at least 6023km, and width direction observation angle is 15.5 °.
6 star networking plans are illustrated in fig. 10 shown below, 60 ° of phase intervals between star, and every star covers each 30 ° of ranges in two sides.As it can be seen that
When number of satellite is 6, required satellite altitude is 329km, and static coverage rate is 99.9%, and lower limit observed range is 3464km, on
Limit observed range is 4225km, and required observed range at least 4225km, width direction observation angle is 22.9 °.
To sum up, 3 star scheme static state coverage rates are unsatisfactory for requiring, and 6 star scheme static state coverage rates meet the requirements and have larger remaining
Amount.As can be seen that when number of satellite is 4, static coverage rate meet demand, therefore select 4 star schemes.4 star schemes are corresponding high
Spending direction observation angle is 15.5 °, selects the load of 17 ° × 22.5 ° visual fields, the width for needing 8 load that can form 180 °
The observation angle in direction.
System major parameter are as follows:
Number of satellite: 4
Satellite altitude: 634km
Load observed range: 6023km
Single-point load visual field: 17 ° × 22.5 °
Load quantity needed for every satellite: 8
Various embodiments are described in a progressive manner in this explanation, the highlights of each of the examples are with its
The difference of his embodiment, the same or similar parts between the embodiments can be referred to each other.
The above, optimal specific embodiment only of the invention, but scope of protection of the present invention is not limited thereto,
In the technical scope disclosed by the present invention, any changes or substitutions that can be easily thought of by anyone skilled in the art,
It should be covered by the protection scope of the present invention.
The content that description in the present invention is not described in detail belongs to the well-known technique of professional and technical personnel in the field.
Claims (10)
1. a kind of construction method of Space-based Space Surveillance photoelectric fencing system characterized by comprising
According to observation object parameter information and observation satellite parameter information, observation initial parameter is determined；Wherein, the observation is initial
Parameter, comprising: observation bound, observation satellite orbit altitude and observation satellite quantity；
According to the observation initial parameter, observed range and observation angle are determined；
According to the observed range and observation angle, loading demands are determined；
According to the loading demands, Space-based Space Surveillance photoelectric fencing system is constructed；Wherein, the Space-based Space prison
More observation satellites, the observation scope of every observation satellite and adjacent observation are arranged in same orbital plane depending on photoelectric fencing system
Satellite intersection, forms an observation annulus.
2. the construction method of Space-based Space Surveillance photoelectric fencing system according to claim 1, which is characterized in that institute
It states according to observation object parameter information and observation satellite parameter information, determines observation initial parameter；Wherein, the initial ginseng of the observation
Number, comprising:
According to the height of observation object, the observation bound is determined；
According to static coverage rate demand, observation satellite quantity is determined；
According to observation satellite quantity, observation satellite orbit altitude is determined.
3. the construction method of Space-based Space Surveillance photoelectric fencing system according to claim 2, which is characterized in that institute
The height according to observation object is stated, determines the observation bound, comprising:
It is for statistical analysis to the height distribution of observation object, determine the distribution density of different height observation object；
According to the distribution density of determining different height observation object, observation bound needed for determining observation, to guarantee to sight
The coverage rate for surveying object is greater than given threshold.
4. the construction method of Space-based Space Surveillance photoelectric fencing system according to claim 2, which is characterized in that root
According to static coverage rate demand, observation satellite quantity is determined, comprising:
Work as he≥hlWhen, static coverage rate γsAre as follows:
Work as he< hlWhen, static coverage rate γsAre as follows:
According to static coverage rate demand, the minimum number n of required observation satellite is determined；
Wherein, heIndicate that the earth faces side, hlIndicate observation lower limit, ReIndicate earth radius, hhIndicate the observation upper limit.
5. the construction method of Space-based Space Surveillance photoelectric fencing system according to claim 4, which is characterized in that root
Observation satellite orbit altitude H is determined according to following formula:
6. the construction method of Space-based Space Surveillance photoelectric fencing system according to claim 1, which is characterized in that institute
It states according to the observation initial parameter, determines observed range and observation angle, comprising:
According to the observation satellite orbit altitude and observation satellite quantity, according to the observation bound and observation object of every satellite
Height, determine observed range；
According to the bound of the altitude range of observation object, required observation angle is determined.
7. the construction method of Space-based Space Surveillance photoelectric fencing system according to claim 6, which is characterized in that institute
It states according to the observation satellite orbit altitude and observation satellite quantity, according to the observation bound and observation object of every satellite
Highly, observed range is determined, comprising:
Observation upper limit h is determined by following formulahRequired upper limit observed range Lh:
Observation lower limit h is determined by following formulalRequired lower limit observed range Ll:
Capping observed range LhWith lower limit observed range LlThe larger value of the two is as the observed range；
Wherein,ReIndicate that earth radius, H indicate observation satellite orbit altitude, n indicates the minimum number of observation satellite.
8. the construction method of Space-based Space Surveillance photoelectric fencing system according to claim 7, which is characterized in that institute
The bound for stating the altitude range according to observation object determines required observation angle, comprising:
Pass through minimum observation angle β needed for following formula computed altitude direction:
Minimum observation angle needed for width direction takes 180 °.
9. the construction method of Space-based Space Surveillance photoelectric fencing system according to claim 1, which is characterized in that institute
It states according to the observed range and observation angle, determines loading demands, comprising:
According to the observed range, the observed range requirement of load is determined；
According to observation angle needed for height and width both direction, the visual field of load is determined.
10. the construction method of Space-based Space Surveillance photoelectric fencing system according to claim 1, which is characterized in that
Constructing obtained Space-based Space Surveillance photoelectric fencing system includes any at least one in following parameter: observation satellite number
Amount, observation satellite height, load observed range, single-point load visual field and load quantity.
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