CN106570270A - Method for rapidly determining multi-satellite combined coverage characteristics for system-oriented design - Google Patents
Method for rapidly determining multi-satellite combined coverage characteristics for system-oriented design Download PDFInfo
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Abstract
The invention relates to a method for rapidly determining multi-satellite combined coverage characteristics for system-oriented design. The method comprises the following steps: determining the period of an intersection between a satellite and the equatorial plane by using three orbital characteristic parameters; determining the longitude difference of a subsatellite point track of the adjacent orbit of the satellite on the equator; determining the longitude of all intersections between the subsatellite point track of the satellite and the equator within a day; obtaining the longitude of an equator sampling point, and determining the coverage of the satellite load at the equatorial intersection on the equator sampling point; determining the initial position of the satellite at the next day and the longitude of all intersections between the current subsatellite point track of the satellite and the equator to obtain the coverage of the satellite load on the equator sampling point within a day again; obtaining the equatorial intersection longitude of each satellite and the coverage on the equator sampling point; and judging whether the equator sampling point is completely covered, and obtaining a multi-satellite combined coverage time index value. According to the method disclosed by the invention, the calculation amount of coverage prediction and observation of the orbit can be greatly reduced, and a certain degree of accuracy guarantee can be achieved; and meanwhile, the method is simple in calculation and easy to implement the projects.
Description
Technical field
The present invention relates to a kind of many stars combine the quick calculation method of Global coverage time, it is particularly well-suited to constitute complexity
When planning and designing, the measures of effectiveness of spacecraft system, the cover time for being rapidly completed satellite multiple combination mode is needed
Simulation calculation, with support system scheme iteration Optimization Seeking Design.
Background technology
Many star combined covering characteristics include many stars combination the whole world or the designated area cover time, many stars combination designated area or
The multifrequency nature index such as appointed place revisit time.For generally for System Design emulation, many stars combine the Global coverage time
It is a kind of most representational characteristic index.
With flourishing for space industry, space remote sensing application demand and remote sensing satellite value volume and range of product are increased rapidly,
" star is multiplex " and " many stars are public " becomes the establishing criteria of the input of architecture design requirement and effectiveness assessment, space-based resource
Architecture design and construction and resource coordination it is shared become aerospace system planning, build important trend with application, therefore produce
Give birth to the design of spacecraft system optimization and apply evaluation problem.The maximum difficult point of the problem is for systematic planning design
Speech, quantity required is huge, and the quantity and load categories of the star of constitution system constitute star far above generally several stars
The situation of seat, has various satellite load combination application modes, when demand entry increases and observes for specific application demand
When task has conflict, in order to as much as possible demand is met, need to carry out satellite multiple combination, traversal amount of calculation is very big.Together
When, it is contemplated that in System Design stage track six roots of sensation number it is a kind of experimental coarse designs, especially needs to consider
The observing capacity of rail star, can carry out prolonged orbital prediction, and the uncertainty of the remote sensing task design apply in addition in all can
Impact is produced on covering numerical simulation precision.Therefore, accurate numerical simulation calculates and is not suitable with the calculating demand of such case,
But a kind of versatility of needs is good, can significantly improve the simplified calculation method of emulation of coverage capability efficiency.
It is current for single star or many star coverage property computational problems it is more be the method for taking numerical simulation, be generally used for
The covering performance emulation of many stars of Simulation Evaluation.Concretely comprise the following steps：(1) based on coverage required precision, overlay area is carried out
Rasterizing；(2) orbit prediction simulation step length is set, further according to all On Orbit Character of Satellite parameter (tracks for participating in coverage
Six roots of sensation number) orbit prediction is carried out to every star, and calculate sub-satellite track；(3) with reference to the load fabric width on every star and observation
The coverage property indexs such as the calculating of the information such as angle is revisited, cover time.The advantage of this computational methods be it is fine in grid granularity,
Accurately, the results contrast that perturbation model is calculated in the case of selecting reasonably is accurate for the parameters such as track, fabric width, observation angle；Lack
, it is also obvious that i.e. computationally intensive, time-consuming for point, especially the combinations of satellites class in the number of satellite for participating in calculating more or for applying
In the case that type is more, System Design simulation calculation amount is excessive.
In addition in engineering, for many same type satellites of same orbital plane have a kind of conventional coverage property empirical estimating
Method, is usually used in the range of budgetary estimate territory meeting certain same rail same type number of satellite and designed phase point for covering and requiring
Cloth.Concretely comprise the following steps：(1) calculated daily around the earth number of turns or orbital period according to the orbit parameter, and according to classification of track (such as
Morning and afternoon star) estimation overlay area effective observation rail number；(2) bounds further according to load fabric width and observation area and
Total rail number of budgetary estimate needs and the phase contrast of adjacent orbit are required to the revisit time in the region；(3) with reference to the load on every star
Lotus fabric width calculates the PHASE DISTRIBUTION and coverage property parameter of many stars.This budgetary estimate method assumed condition is more satisfactory, is to spy
The short time for determining region is calculated quickly roughly, it is impossible to rapid translating to different tracks, the calculated case of different loads, the versatility of method
Inadequate and precision cannot ensure.
In System Effectiveness assessment, many star coverage property relative analyses are a basic index computational problems.Work as calculating
Amount is little, and to calculate it is time-consuming do not require when, using the method for the first numerical computations mentioned above, can meet will
Ask；But when participate in calculating star is relatively more, System Design across time period is longer, the situation more than needs assessment quantity required
Under, in addition to assuming that preferably second fast arithmetic can be adopted with orbital plane combinations of satellites, for different tracks, different loads
The situation of lotus fabric width, if necessary to the System Effectiveness index of the coverage property such as, many stars multiplex to a star are public calculating is estimated
When, numerical computations complexity can make simulation time become very long；Simultaneously because in the planning and designing stage, the orbit parameter of satellite sets
Meter usually first sets empirical value, and further according to Architecture simulation adjustment is optimized, therefore this calculating is to also need to iterate, phase
Time needed for the calculating answered can be longer.
For whole system, when region to be calculated dispersed and distributed in the world, and quantity are indefinite,
It is difficult to the coverage condition of Fast estimation difference track, different loads fabric width to these regions, it is therefore necessary to which the method is entered
Row is improved, and is made condition hypothesis for different situations and is designed corresponding simplified calculation method and general judgment criterion.
The content of the invention
The present invention technology solve problem be：Overcome the deficiencies in the prior art part, there is provided a kind of many stars cover quick meter
Calculation method, can greatly reduce orbit prediction and observation coverage amount, and with certain accuracy guarantee, while calculate simple,
Project Realization is easy.
The present invention technical solution be：A kind of quick side of determination of many star combined covering characteristics of System of System Oriented design
Method, it is characterised in that step is as follows：
(1) using semi-major axis of orbit, orbital eccentricity, three track characteristic parameter determination satellites of orbit inclination angle and the equatoriat plane
Nodal period；
(2) nodal period obtained using rotational-angular velocity of the earth and step (1) determines satellite adjacent orbit substar rail
The difference of longitude that mark is gone up under the line；
(3) using the intersection point in satellite preliminary orbit substar and equator as the initial position of each star, satellite and the equatoriat plane
The difference of longitude that nodal period and step (2) Satellite adjacent orbit sub-satellite track are gone up under the line determines sub-satellite point in a day
Track and all intersection point longitudes in equator；
(4) sampling granularity in the case of all standing of equator is set, equator sampled point longitude is obtained, using satellite load fabric width
With all intersection point longitudes in the equator for obtaining, coverage condition of the satellite load to equator sampled point at equatorial node is determined；
(5) to the integral multiple of satellite nodal period with day as unit remainder, and determined using step (1) to step (3) and defended
The initial position and satellite same day sub-satellite track of star next day and all intersection point longitudes in equator, recycle satellite load fabric width
Coverage condition of the satellite load to equator sampled point in one day is obtained with the equator sampled point longitude of step (4)；
(6) using the semi-major axis of many stars, orbital eccentricity, three track characteristic parameters of orbit inclination angle, repeat step (1) is extremely
Step (5), obtains each star equatorial node longitude and to equator sampled point coverage condition；
(7) judge whether equator sampled point covers completely, if not covering complete repeat step (5), if covering completely recorded
Natural law, obtains many star combined covering time index values.
The step (1) is using semi-major axis of orbit, orbital eccentricity, three track characteristic parameter determination satellites of orbit inclination angle
Obtain as follows with the nodal period of the equatoriat plane：
If nodal period is
Wherein：
Wherein n is satellite motion average period, i.e.,
In formula,For argument of perigee, unit is radian；For mean anomaly, unit is radian；A is that track half is long
Axle, unit is rice；E is orbital eccentricity, and i is orbit inclination angle, J2=1.082625829965505e-3, is terrestrial gravitation gesture
Second order zonal harmonic coefficient, Re=6378137.0, it is terrestrial equator radius, unit is rice；μE=3.98600436e+14, is the earth
Gravitational constant, unit is rice3/ the second2。
The method of the difference of longitude that the determination satellite adjacent orbit sub-satellite track of the step (2) is gone up under the line is：
If satellite xjThe difference of longitude Δ λ that adjacent track is gone up under the linej,
Wherein,
For right ascension of ascending node rate of change；For the angle of rotation speed of the earth
Degree；A is semi-major axis of orbit, and unit is rice；E is orbital eccentricity, and i is orbit inclination angle.
In the step (3)
(1) initial position of each star determines that method is：
If the initial position of jth star is xloc(j), xlocJ () is for the random number between (0,2 Π) and more than or equal to many stars
Minimum load fabric width W in combinationmin, represented with radian；The initial position of each star is obtained in the same manner；
Track of Sub-Satellite Point determines that method is with all intersection point longitudes in equator in (2) one days：
Xj={ xloc(j)+(n-1)·Δλj| n ∈ N and n≤cj, wherein xlocJ () is the initial position of jth star, n is
The ordinal number of Track of Sub-Satellite Point and equatorial node, cjIt is satellite xjThe nodal period number of one day,Represent
Round downwards,The satellite obtained for step (1) and the nodal period of the equatoriat plane, unit is hour.
In the step (4)
(1) equator sampled point longitude coverage condition method for expressing is：
Rasterizing is carried out to equator respectively to sample, and in the case of N deciles, that is, has N+1 sampled point, p-th sampling optimization
Put and be designated as Np, using satellite fabric width to the covering of whole sampled points as coverage condition basis for estimation, uncovered sampling number
It is designated as NNot, the threshold value of uncovered sampling number for terminating all standing cycle calculations is designated as Ntol, introduce the mark of each sample point
Note function flag (p),
(2) satellite load determines that method is to the coverage condition of equator sampled point at equatorial node：
With satellite xjAs a example by the coverage condition of c-th intersection point of the d days, satellite x is calculated firstjCurrent coverage area betweenWhereinxlocJ () is jth
The initial position of star, unit is radian；ΔλjIt is satellite xjThe difference of longitude that adjacent track is gone up under the line, unit is radian, then successively
Judge whether N+1 equator sampled point is capped；
The step whether equator sampled point is capped is：If current sampling point NpIt was not covered with, i.e. current sampling point
Labeling function value flag (p) be 0, then judge sampled point NpWhether covering intervalIn the range of：If Np
In the interval, then labeling function value flag (p) for changing current sampling point is 1, and uncovered sampling number is designated as NNot=NNot-
1；If NpNot in the interval, do not make any operation, circulate N+1 time, complete each equator sampled point coverage condition and determine.
Satellite load is to the determination method of the coverage condition of equator sampled point in a day in the step (5)：
For satellite xjThe coverage condition of the c intersection point of the d days, first with satellite load at step (4) equatorial node to equator
The coverage condition of sampled point determines that method determines that the covering of c intersection point is interval
Again to the equator sampled point Covering judgment step in the interval circulation step (4) of each covering, satellite load is obtained in one day to red
The coverage condition of road sampled point.
The determination method of each star equator sampled point longitude and equator sampled point coverage condition in the step (6) is：
Coverage condition to the d days, obtains based on step (4) and step (5) first with step (1) to step (3)
The difference of longitude that the initial position (unit is radian) and every star adjacent track of every star needed for calculating is gone up under the line, then to per
Star reuses step (5), that is, obtain each star equator sampled point longitude and equator sampled point coverage condition at the d days.
Many star combined covering time index values in the step (7) cover the determination method of natural law d：
If original state d=0, after step (6) is completed, judge whether to cover whole equator sampled points, i.e. NNotIt is
It is no less than Ntol, wherein NNotRepresent uncovered sampling number, NtolTo terminate the uncovered sampling of all standing cycle calculations
The threshold value of points, if NNotMore than Ntol, then d=d+1, circulates execution step (6), if NNotLess than or equal to Ntol, then many stars are obtained
Combined covering time index value covers natural law d.
Present invention advantage compared with prior art is：
(1) periodic feature that the present invention is run using earth observation satellite, with satellite transit track and equatorial node Jing
Spend computational methods to simplify satellite orbit whole world substar forecast calculation, significantly reduce the track of Service Global coverage
Forecast calculation amount；Using the nodal period computation model for considering the perturbation of J2 items, it is ensured that orbital node longitude has higher calculating
Precision, can meet the application demand of System Design emulation.
(2) present invention replaces load Global coverage geography grid to all standing property calculation on equator using satellite load
Judge to calculate, i.e., the one-dimensional coverage condition of equatorial perimeter is calculated with fabric width and replace Global coverage two dimension to calculate, reduce geography
Grid circulating judges to calculate dimension, it is to avoid multistep coordinate system of the equator to polar regions sampled point two-dimensional coordinates in raster symbol-base
Conversion Calculation；Compare general two-dimentional sampled point Covering judgment, it is to avoid the calculation error that coordinate system transfer zone comes, calculate more
Simplicity, Project Realization is easy.
(3) basis that the nodal period information that the present invention is obtained can be calculated as further zoning Cover Characteristics.Enter
When the satellite load specific region coverage property of row System of System Oriented is analyzed, the minimum dimension circle that can adopt the place earth in region is made
The equatorial circumference in method is determined for this, by calculating nodal period, joint rotational-angular velocity of the earth is corresponding with orbit inclination angle acquisition
The difference of longitude between adjacent orbit on dimension circle, is sampled using subsequent step to dimension circle, and it is right so can quickly to determine
The all standing feature in the region, can so reduce region overlay grid and judge to calculate, and be easy to engineer applied.
In a word, the present invention has passed through real data checking, method in spacecraft Architecture simulation and Effectiveness Evaluation System
Feasible, engineering technology is easily realized, therefore with practicality.
Description of the drawings
Fig. 1 is that many star combined covering characteristics of System of System Oriented design of the present invention quickly determine flow chart.
Specific embodiment
Embodiment 1：
As shown in figure 1, the present invention's comprises the following steps that：
(1) using semi-major axis of orbit, orbital eccentricity, three track characteristic parameter determination satellites of orbit inclination angle and the equatoriat plane
Nodal period.
If nodal period is
Wherein：
Here n is satellite motion average period, i.e.,
In formula,For argument of perigee (unit is radian),For mean anomaly (unit is radian), a is that track half is long
Axle (unit is rice), e is orbital eccentricity, and i is orbit inclination angle, J2=1.082625829965505e-3, is terrestrial gravitation gesture
Second order zonal harmonic coefficient, Re=6378137.0, it is terrestrial equator radius (unit is rice), μE=3.98600436e+14, is ground
(unit is rice to the gravitational constant of ball3/ the second2)。
(2) nodal period obtained using rotational-angular velocity of the earth and step (1) determines satellite adjacent orbit substar rail
The difference of longitude that mark is gone up under the line.
If satellite xjThe difference of longitude Δ λ that adjacent track is gone up under the linej,
Wherein,
For right ascension of ascending node rate of change；For the angle of rotation speed of the earth
Degree；A is semi-major axis of orbit (unit is rice), and e is orbital eccentricity, and i is orbit inclination angle.
(3) using the intersection point in satellite preliminary orbit substar and equator as the initial position of each star, satellite and the equatoriat plane
The difference of longitude that nodal period and step (2) Satellite adjacent orbit sub-satellite track are gone up under the line determines sub-satellite point in a day
Track and all intersection point longitudes in equator.
First, the initial position of each star determines that method is：
If the initial position of jth star is xloc(j), xlocJ () is for the random number between (0,2 Π) and more than or equal to many stars
Minimum load fabric width W in combinationmin, represented with radian；The initial position of each star is obtained in the same manner.
Then, Track of Sub-Satellite Point determines that method is with all intersection point longitudes in equator in one day：
Xj={ xloc(j)+(n-1)·Δλj| n ∈ N and n≤cj, wherein xlocJ () is the initial position of jth star, n is
The ordinal number of Track of Sub-Satellite Point and equatorial node, cjIt is satellite xjThe nodal period number of one day,Represent
Round downwards,The satellite obtained for step (1) and the nodal period (unit is hour) of the equatoriat plane.
(4) sampling granularity in the case of all standing of equator is set, equator sampled point longitude is obtained, using satellite load fabric width
With all intersection point longitudes in the equator for obtaining, coverage condition of the satellite load to equator sampled point at equatorial node is determined.
First, equator sampled point longitude coverage condition method for expressing is defined：
Rasterizing is carried out to equator respectively to sample, and in the case of N deciles, that is, has N+1 sampled point, p-th sampling optimization
Put and be designated as Np, using satellite fabric width to the covering of whole sampled points as coverage condition basis for estimation, uncovered sampling number
It is designated as NNot, the threshold value of uncovered sampling number for terminating all standing cycle calculations is designated as Ntol, introduce the mark of each sample point
Note function flag (p),
Then, it is determined that coverage condition of the satellite load to equator sampled point at equatorial node：
With satellite xjAs a example by the coverage condition of c-th intersection point of the d days, satellite x is calculated firstjCurrent coverage area betweenWhereinxlocJ () is jth
The initial position (unit is radian) of star, Δ λjIt is satellite xjThe difference of longitude (unit is radian) that adjacent track is gone up under the line, then according to
It is secondary to judge whether N+1 equator sampled point is capped.
The step whether equator sampled point is capped is：If current sampling point NpIt was not covered with (i.e. current sampling point
Labeling function value flag (p) for 0), then judge sampled point NpWhether covering intervalIn the range of：If Np
In the interval, then labeling function value flag (p) for changing current sampling point is 1, and uncovered sampling number is designated as NNot=
NNot-1；If NpNot in the interval, any operation is not made.Circulation N+1 time, completes each equator sampled point coverage condition and determines.
(5) to the integral multiple of satellite nodal period with day as unit remainder, and determined using step (1) to step (3) and defended
The initial position and satellite same day sub-satellite track of star next day and all intersection point longitudes in equator, recycle satellite load fabric width
Coverage condition of the satellite load to equator sampled point in one day is obtained with the equator sampled point longitude of step (4).
Above-mentioned solution procedure is as follows：With satellite xjAs a example by the coverage condition of the c intersection point of the d days, first with step
(4) satellite load determines that method determines that the covering of c intersection point is interval to the coverage condition of equator sampled point at equatorial nodeAgain in the interval circulation step (4) of each covering
Equator sampled point Covering judgment step, can obtain coverage condition of the satellite load to equator sampled point in a day.
(6) using the semi-major axis of many stars, orbital eccentricity, three track characteristic parameters of orbit inclination angle, repeat step (1) is extremely
Step (5), obtains each star equatorial node longitude and to equator sampled point coverage condition.
Above-mentioned solution procedure is as follows：By taking the coverage condition of the d days as an example, obtain to step (3) first with step (1)
Step (4) must be used for and step (5) calculates the initial position (unit is radian) and every star adjacent track of every required star
The difference of longitude (unit is radian) gone up under the line, then step (5) is reused to every star, you can obtain red in the d days each stars
Road sampled point longitude and equator sampled point coverage condition.
(7) judge whether equator sampled point covers completely, if not covering complete repeat step (5), if covering completely recorded
Natural law, obtains many star combined covering time index values.
Above-mentioned solution procedure is as follows：If original state d=0, after step (6) is completed, judge whether complete to cover
Portion equator sampled point, i.e. NNotWhether N is less thantol, wherein NNotRepresent uncovered sampling number, NtolTo terminate all standing circulation
The threshold value of the uncovered sampling number for calculating, if NNotMore than Ntol, then d=d+1, circulates execution step (6), if NNotLess than or
Equal to Ntol, then obtain many star combined covering time index values and cover natural law d.
Claims (8)
1. many star combined covering characteristic fast determination methods that a kind of System of System Oriented is designed, it is characterised in that step is as follows：
(1) using the friendship of semi-major axis of orbit, orbital eccentricity, three track characteristic parameter determination satellites of orbit inclination angle and the equatoriat plane
The point cycle；
(2) nodal period obtained using rotational-angular velocity of the earth and step (1) determines that satellite adjacent orbit sub-satellite track exists
Difference of longitude on equator；
(3) using the intersection point in satellite preliminary orbit substar and equator as the intersection point of the initial position of each star, satellite and the equatoriat plane
The difference of longitude that cycle and step (2) Satellite adjacent orbit sub-satellite track are gone up under the line determines Track of Sub-Satellite Point in a day
With all intersection point longitudes in equator；
(4) sampling granularity in the case of all standing of equator is set, equator sampled point longitude is obtained, using satellite load fabric width and obtains
All intersection point longitudes in the equator for obtaining, determine coverage condition of the satellite load to equator sampled point at equatorial node；
(5) to the integral multiple of satellite nodal period with day as unit remainder, and satellite is determined using step (1) to step (3)
The initial position and satellite same day sub-satellite track of day and all intersection point longitudes in equator, recycle satellite load fabric width and step
Suddenly the equator sampled point longitude of (4) obtains coverage condition of the satellite load to equator sampled point in a day；
(6) using the semi-major axis of many stars, orbital eccentricity, three track characteristic parameters of orbit inclination angle, repeat step (1) is to step
(5) each star equatorial node longitude, is obtained and to equator sampled point coverage condition；
(7) judge whether equator sampled point covers completely, if not covering complete repeat step (5), if covering completely recorded natural law,
Obtain many star combined covering time index values.
2. many star combined covering characteristic fast determination methods that System of System Oriented according to claim 1 is designed, its feature exists
In：The step (1) using semi-major axis of orbit, orbital eccentricity, three track characteristic parameter determination satellites of orbit inclination angle with it is red
The nodal period in road face is obtained as follows：
If nodal period is
Wherein：
Wherein n is satellite motion average period, i.e.,
In formula,For argument of perigee；For mean anomaly；A is semi-major axis of orbit, and unit is rice；E is orbital eccentricity, and i is
Orbit inclination angle, J2=1.082625829965505e-3, is the second order zonal harmonic coefficient of terrestrial gravitation gesture, Re=6378137.0, be
Terrestrial equator radius；μE=3.98600436e+14, is the gravitational constant of the earth.
3. many star combined covering characteristic fast determination methods that System of System Oriented according to claim 1 is designed, its feature exists
In：The method of the difference of longitude that the determination satellite adjacent orbit sub-satellite track of the step (2) is gone up under the line is：
If satellite xjThe difference of longitude Δ λ that adjacent track is gone up under the linej,
Wherein,
For right ascension of ascending node rate of change；For the spin velocity of the earth；a
For semi-major axis of orbit；E is orbital eccentricity, and i is orbit inclination angle.
4. many star combined covering characteristic fast determination methods that System of System Oriented according to claim 1 is designed, its feature exists
In：In the step (3)
(1) initial position of each star determines that method is：
If the initial position of jth star is xloc(j), xlocJ () is the random number between (0,2 Π) and combines more than or equal to many stars
Middle minimum load fabric width Wmin, represented with radian；The initial position of each star is obtained in the same manner；
Track of Sub-Satellite Point determines that method is with all intersection point longitudes in equator in (2) one days：
Xj={ xloc(j)+(n-1)·Δλj| n ∈ N and n≤cj, wherein xlocJ () is the initial position of jth star, n is satellite
The ordinal number of sub-satellite track and equatorial node, cjIt is satellite xjThe nodal period number of one day, Expression takes downwards
It is whole,The satellite obtained for step (1) and the nodal period of the equatoriat plane, unit is hour.
5. many star combined covering characteristic fast determination methods that System of System Oriented according to claim 1 is designed, its feature exists
In：In the step (4)
(1) equator sampled point longitude coverage condition method for expressing is：
Rasterizing is carried out to equator respectively to sample, and in the case of N deciles, that is, has N+1 sampled point, p-th sampling point position note
For Np, using satellite fabric width to the covering of whole sampled points as coverage condition basis for estimation, uncovered sampling number is designated as
NNot, the threshold value of uncovered sampling number for terminating all standing cycle calculations is designated as Ntol, introduce the labelling letter of each sample point
Number flag (p),
(2) satellite load determines that method is to the coverage condition of equator sampled point at equatorial node：
For satellite xjThe coverage condition of c-th intersection point of the d days, calculates first satellite xjCurrent coverage area between
WhereinxlocJ () is the initial position of jth star；
ΔλjIt is satellite xjThe difference of longitude that adjacent track is gone up under the line, unit is radian, then whether judges N+1 equator sampled point successively
It is capped；
The step whether equator sampled point is capped is：If current sampling point NpIt was not covered with, i.e. the labelling of current sampling point
Functional value flag (p) is 0, then judge sampled point NpWhether covering intervalIn the range of：If NpIn the interval
Interior, then labeling function value flag (p) for changing current sampling point is 1, and uncovered sampling number is designated as NNot=NNot-1；If Np
Not in the interval, do not make any operation, circulate N+1 time, complete each equator sampled point coverage condition and determine.
6. many star combined covering characteristic fast determination methods that System of System Oriented according to claim 1 is designed, its feature exists
In：Satellite load is to the determination method of the coverage condition of equator sampled point in a day in the step (5)：
For satellite xjThe coverage condition of the c intersection point of the d days, samples first with satellite load at step (4) equatorial node to equator
The coverage condition of point determines that method determines that the covering of c intersection point is interval
Again to the equator sampled point Covering judgment step in the interval circulation step (4) of each covering, satellite load is obtained in one day to red
The coverage condition of road sampled point.
7. many star combined covering characteristic fast determination methods that System of System Oriented according to claim 1 is designed, its feature exists
In：The determination method of each star equator sampled point longitude and equator sampled point coverage condition in the step (6) is：
Coverage condition to the d days, obtains first with step (1) to step (3) and calculates institute for step (4) and step (5)
The difference of longitude that the initial position (unit is radian) and every star adjacent track of the every star for needing is gone up under the line, then to every star weight
Step (5) is used again, that is, obtain each star equator sampled point longitude and equator sampled point coverage condition at the d days.
8. many star combined covering characteristic fast determination methods that System of System Oriented according to claim 1 is designed, its feature exists
In：Many star combined covering time index values in the step (7) cover the determination method of natural law d：
If original state d=0, after step (6) is completed, judge whether to cover whole equator sampled points, i.e. NNotIt is whether little
In Ntol, wherein NNotRepresent uncovered sampling number, NtolTo terminate the uncovered sampling number of all standing cycle calculations
Threshold value, if NNotMore than Ntol, then d=d+1, circulates execution step (6), if NNotLess than or equal to Ntol, then many star combinations are obtained
Cover time desired value covers natural law d.
Priority Applications (1)
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