CN109861742A - A method of for determining the configuration of constellation - Google Patents
A method of for determining the configuration of constellation Download PDFInfo
- Publication number
- CN109861742A CN109861742A CN201910155921.8A CN201910155921A CN109861742A CN 109861742 A CN109861742 A CN 109861742A CN 201910155921 A CN201910155921 A CN 201910155921A CN 109861742 A CN109861742 A CN 109861742A
- Authority
- CN
- China
- Prior art keywords
- constellation
- time
- satellite
- communication
- indicates
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Landscapes
- Radio Relay Systems (AREA)
Abstract
The present invention relates to a kind of methods for determining the configuration of constellation, comprising: determines the parameter of constellation；The optional configuration of constellation is determined according to the parameter；Emulation input condition is determined according to the satellite orbit feature of constellation and executes emulation；Configuration is selected from the optional configuration according to simulation result.In this way, more excellent scheme can be selected from the plurality of optional scheme of constellation configuration, reference is provided for demonstration early period of constellation systems.
Description
Technical field
Present invention relates in general to Track desigh field, more particularly to constellation configuration to the covering performance point on ground
Analysis field is more precisely related to a kind of method for determining the configuration of constellation.
Background technique
With the rapid development of science and technology, this advanced electronic product of satellite increasingly connects for general public
By.The advantages of satellite, is rapidly traverse the whole world, and meets the people's livelihood needs such as communication, navigation, earth observation.With with
The application demand at family is constantly promoted, and single satellite is unable to do what one wishes, to develop the constellation being made of more stars.But satellite
A possibility that different from general electronic product, it is expensive, and reliability requirement is high, does not reprocess, it is therefore desirable to select
It is just very careful when the space layout of satellite to select, that is to say, that and the steric configuration design of constellation will pass through stringent demonstration, so that
Not only meet user demand, but also development cost can be saved, and can be customized to according to the specific demand of user, realize expensive space flight
The high performance-price ratio of electronic product.
The design of constellation configuration is that longer problem is studied inside Track desigh field, that is, is directed to specific mission requirements, mentions
Certain performance indicator out makees the configuration design of constellation for the demand of performance indicator, provides design result, meet user's need
It asks.But not only unique solution sets satellite orbit often in the presence of a huge disaggregation result of Constellation Design
For meter personnel in other words for satellite user, it is extremely difficult for finding inside huge disaggregation and being most suitable for the optimal solution of project demands
, and in the preliminary stage of satellite constellation project demonstration, often only need the scale and more rough orbital tracking of constellation
For the feasibility of evaluation item, without accurate demonstration selection.
The research of Constellation Design algorithm is much, although as a result, stringent numerical value the selection result, has more
Strong engineering referential, but need a large amount of mathematical computations, it is difficult to preliminary constellation configuration design result is provided in a short time,
And most of projects need successive ignition in the initial stage of demonstration, are not necessarily to particularly accurate constellation structure parameters, Constellation optimization
Algorithm for design is difficult to meet the high-timeliness requirement of project initial stage.
To sum up, the current quick Constellation Design method for needing to solve to be suitable for project demonstration initial stage, to be put down as satellite
The input of platform and load design, and iteratively faster is engineering proposal, and then preferentially by further optimization algorithm.
Summary of the invention
The task of the present invention is a kind of method for determining the configuration of constellation is provided, in this way, can be from constellation
More excellent scheme is selected in the plurality of optional scheme of configuration, provides reference for demonstration early period of constellation systems.
According to the present invention, which is solved by a kind of for determining the method for the configuration of constellation, this method comprises:
Determine the parameter of constellation；
The optional configuration of constellation is determined according to the parameter；
Emulation input condition is determined according to the satellite orbit feature of constellation and executes emulation；
Configuration is selected from the optional configuration according to simulation result.
It is provided in a preferred embodiment of the invention, the parameter includes one or more of the following:
Cover time indicates that all covering or N% cover the time used by a certain regional aim or point target set；
Space percentage is covered, indicates that any sampling instant accounts for the hundred of entire analyzed region by the region that satellite covers
Divide ratio；
Tuple is averagely covered, indicates any sampling instant to a certain observed object or the simultaneously visible satellite number of mesh point
Mesh；
Averagely can communication time, indicate a certain observed object or mesh point single is visible averagely can communication time；
Cover time percentage indicates the time hundred that a certain observed object or mesh point are covered by one or multi-satellite
Divide ratio；
Maximal cover gap indicates the maximum duration gap covered twice；
Average coverage gap, indicates the average length of mesh point covering break period；
Time compliance rate is returned to, indicates that mesh point revisit time in emulation cycle reaches the percentage of a certain thresholding；
Average response time indicates the average value for the time that mesh point terminates apart from this coverage gap；
Response time compliance rate indicates that mesh point response time in emulation cycle reaches the percentage of a certain thresholding；
Maximum communication time delay, indicate user terminal and constellation can communication occasions to constellation next time and terrestrial communication networks
System can communication occasions maximum duration length；
Average communication time delay, indicate user terminal and constellation can communication occasions to constellation next time and terrestrial communication networks
System can communication occasions average length of time；
Communication delay compliance rate indicates that mesh point communication delay in emulation cycle reaches the percentage of a certain thresholding；
And
Time mean gap indicates that the average value of coverage gap is sought in temporally sampling.
Pass through the preferred embodiment, it may be considered that the various parameters of constellation configuration, thus, it is possible to select optimal optional structure
Type.
It provides in another preferred embodiment of the invention, this method further include:
Determine the constraint condition of constellation；And
Optional configuration is selected according to the constraint condition.
By adding constraint condition, it is contemplated that more actual factors or requirement, thus formulate and more correspond to actual needs
Constellation configuration.
It being provided in another preferred embodiment of the invention, the constraint condition includes Condition of Strong Constraint and weak constraint condition,
Wherein Condition of Strong Constraint is the constraint condition that constellation must satisfy, and weak constraint condition is that constellation is allowed to have 10% deviation
Constraint condition；
Wherein Condition of Strong Constraint includes one or more of the following:
800 km of the average height of orbit is the sun-synchronous orbit of 10:30 when southbound node place；
Shadow region can be in ground in call duration time section；
Can communication time be greater than 60 seconds；
Earth station can communication constraint: 15 ° of the elevation angle；
Coverage goal: -70 °~70 °, 6 ° of Grid simulations；And
Load Field of View Constraint: satellite flight direction ± 70 °, perpendicular to heading ± 60 °；
Wherein weak constraint condition includes one or more of the following:
In the continuous cover time section of satellite, with orbital plane adjacent satellite to the coverage gap on ground less than 30 minutes；With
And
In the continuous cover time section of satellite, face orbital plane adjacent satellite to the longest coverage gap on ground less than 90 points
Clock.
It, can be by a variety of constraint conditions in view of being achieved in better configuration in configuration selection by the preferred embodiment
Selection.It should be noted here that under the teachings of the present invention, other constraint conditions are also conceivable.
It is provided in an expansion scheme of the invention, the optional configuration of constellation includes the Walker star with uniform properties
Seat.By the expansion scheme, Global coverage uniform as far as possible may be implemented.
It is provided in a preferred embodiment of the invention, emulation input condition is determined simultaneously according to the satellite orbit feature of constellation
Executing emulation includes:
Recursion period is determined according to the recurrence characteristic of constellation；
Simulation time section is determined according to recursion period；And
Emulation is executed in simulation time section.
By the preferred embodiment, realistic simulation process may be implemented, thus obtain more closing to reality situation
Simulation result.
It provides in another preferred embodiment of the invention, the simulation time section includes one or more typical times
Section.By the preferred embodiment, the calculation amount of emulation can be greatly reduced.For example, if in strict accordance with all ground is traversed
It stands, the relative positional relationship of satellite, the sun, then the time interval for needing to emulate is recursion period and 365.25 days least common multiples
Number, i.e., 58 × 365.25=21184.5 days, calculation amount be it is quite huge, select typical time interval to be emulated here,
The foundation of project choice is can be used as engineer application.
Detailed description of the invention
With reference to specific embodiment, the present invention is further explained with reference to the accompanying drawing.
Fig. 1 shows according to the present invention for determining the process of the method for the configuration of constellation；
Fig. 2 shows the schematic diagrames of single star covered ground；And
Fig. 3 to Fig. 4 shows 3 hours 3 faces of southbound node place phase difference, 12 star substar schematic diagram；
Fig. 5 shows the relativeness of September satellites on the 8th and sun, earth (earth's surface dark colour is ground area shading)；
Fig. 6 shows the relativeness of satellite on December 21 and sun, earth (earth's surface dark colour is ground area shading)；
Fig. 7 shows the relativeness of satellite on April 8 and sun, earth (earth's surface dark colour is ground area shading)；
Fig. 8 shows average coverage gap: 29 days before and after the Autumnal Equinox, 9:00,10:30,16:30 when southbound node place；
Fig. 9 shows average coverage gap: 29 days -2 orbital planes and 3 orbital planes before and after the Autumnal Equinox；
Figure 10 is shown before and after the Autumnal Equinox 29 days, the phase of 9:00,10:30,16:30 satellite and sun, earth when southbound node place
To relationship (earth's surface dark colour is ground area shading)；
Figure 11 shows average coverage gap: halcyon days 29 days, 9:00,10:30,16:30 when southbound node place；
Figure 12 shows average coverage gap: 29 days -2 orbital planes of halcyon days and 3 orbital planes；
Figure 13 shows halcyon days 29 days, the phase of 9:00,10:30,16:30 satellite and sun, earth when southbound node place
To relationship (earth's surface dark colour is ground area shading)；
Figure 14 shows average coverage gap: 29 days before and after the Summer Solstice, 9:00,10:30,16:30 when southbound node place；
Figure 15 shows average coverage gap: 29 days -2 orbital planes and 3 orbital planes before and after the Summer Solstice；And
Figure 16 is shown before and after the Summer Solstice 29 days, the phase of 9:00,10:30,16:30 satellite and sun, earth when southbound node place
To relationship (earth's surface dark colour is ground area shading).
Specific embodiment
It should be pointed out that each component in each attached drawing may be shown in which be exaggerated in order to illustrate, and it is not necessarily ratio
Example is correctly.In the drawings, identical appended drawing reference is equipped with to the identical component of identical or function.
In the present invention, unless otherwise indicated, " on being arranged in ... ", " being arranged in ... top " and " on being arranged in ... "
Do not exclude the case where there are intermediaries therebetween.
In the present invention, each embodiment is intended only to illustrate the solution of the present invention, and is understood not to restrictive.
In the present invention, unless otherwise indicated, quantifier "one", " one " and the scene for not excluding element.
It is also noted herein that in an embodiment of the present invention, for it is clear, for the sake of simplicity, might show only one
Sub-unit or component, but those skilled in the art are it is understood that under the teachings of the present invention, it can be according to concrete scene
Need to add required component or component.
It is also noted herein that within the scope of the invention, the wording such as " identical ", " equal ", " being equal to " are not meant to
The two numerical value is absolutely equal, but allows certain reasonable error, that is to say, that the wording also contemplated " substantially phase
Together ", " being essentially equal ", " being substantially equal to ".
In addition, the number of the step of each method of the invention limit the method step execute sequence.Unless special
It does not point out, various method steps can be executed with different order.
Fig. 1 shows according to the present invention for determining the process of the method 100 of the configuration of constellation, wherein dotted line frame expression
Optional step.
In step 102, the parameter of constellation is determined.
In optional step 104, the constraint condition of constellation is determined.
In step 106, the optional configuration of constellation is determined according to the parameter and optional constraint condition.
In optional step 108, recursion period is determined according to the recurrence characteristic of constellation.
In optional step 110, simulation time section is determined according to recursion period.
In step 112, emulation is executed.
In step 114, configuration is selected from optional configuration according to simulation result.
The present invention is illustrated below according to specific application example.
Ideas based on the present invention is: the constellation configuration design requirement based on project demonstration initial stage provides theory analysis,
Preliminary constellation configuration design scheme is provided according to theoretical analysis result, is determined according to satellite orbit feature and mission requirements imitative
True input condition is simultaneously emulated, and the foundation of constellation configuration selection is provided according to simulation result.
In order to illustrate that foregoing invention, this application example adopt the following technical scheme that:
Firstly, providing being specifically defined for typical constellation performance indicator, and preliminary analysis application field.
Secondly, according to the particular task provided, analysis task demand determines the preliminary scale of constellation configuration, provides optional
Constellation.
Finally, determining emulation input condition and simulation calculation according to constellation Satellite track feature, simulation result is provided, and
Constellation superiority and inferiority is judged according to result and to the satisfaction of mission requirements, selects constellation configuration.
Further, the specific implementation step of the technical program is described below:
Step 1, being specifically defined for typical constellation performance indicator, and preliminary analysis application field are provided.
Cover time T
Cover time is the time that a certain regional aim or point target set whole covering or N% covering is used, only right
Regional aim or point target set are effective.
This index is spreadability index, is suitable for earth observation, communication, navigation, meteorological satellite Constellation Design.
Cover space percentage PecS
Covering space percentage, that is, any sampling instant is accounted for the percentage in entire analyzed region by the region that satellite covers,
When doing Constellation Design, it should the average value P ecS_A of all sampling instants is taken, it is only effective to regional aim or point target set.
This index is spreadability index, is suitable for earth observation, communication, navigation, meteorological satellite Constellation Design.
Averagely cover tuple N_A
Tuple, that is, any sampling instant is covered to a certain observed object or the simultaneously visible number of satellite of mesh point, is doing star
When seat design, the average value N_A of all sampling instants should be taken, if calculating all nets for regional aim or point target set
The average value N_AA of lattice point.
This index is spreadability index, is suitable for earth observation, communication, navigation, meteorological satellite Constellation Design.
It averagely can communication time Du_A
Averagely can communication time Du_A, that is, a certain observed object or mesh point single it is visible averagely can communication time, if right
In regional aim or point target set, then the average value Du_AA of all mesh points is calculated.
This index is the singal reporting code of spreadability index and calculation delay, is suitable for earth observation, communication, navigation, gas
As Satellite Constellation Design.
Cover time percentage PecT
The percentage of time that a certain observed object or mesh point are covered by one or multi-satellite, i.e., defended by one or more
The number (number is primary with a sampling instant) of star covering is divided by the total number of sampling instant in simulation time, if for area
Domain target or point target set then need to count the average value P ecT_A of all mesh points.
This index is spreadability index, is suitable for earth observation, communication, navigation, meteorological satellite Constellation Design.
Maximal cover gap RevTMax
The time slot that coverage gap covers twice, also referred to as revisit time, maximal cover gap RevTMax (Maximum
Coverage Gap) i.e. mesh point longest coverage gap, abbreviation maximal clearance is equal to longest response time (Maximum
Response Time).If calculating the average value RevTMax_A of all mesh points for regional aim or point target set.
This covering performance index can only provide constellation to the most harsh conditions of covered ground, to the whole spreadability of constellation
The index that the assessment of energy has not been.
This index is the singal reporting code of calculation delay, is suitable for communication satellite constellation and designs.
Average coverage gap RevT_A
Average coverage gap RevT_A (Mean Coverage Gap) abbreviation mean gap, i.e., when mesh point covering is interrupted
Between average length, i.e., total gap length is divided by gap number.If being calculated all for regional aim or point target set
The average value RevT_AA of mesh point.
Its expression formula is
This index is the singal reporting code of calculation delay, is suitable for communication satellite constellation and designs.
Revisit time compliance rate PecRev
Revisit time compliance rate PecRev, that is, mesh point revisit time in emulation cycle reaches the percentage of a certain thresholding.
If calculating the average value P ecRev_A of all mesh points for regional aim or point target set.
This index is the singal reporting code of calculation delay, is suitable for communication satellite constellation and designs.
Average response time MRT
Response time is the time that mesh point terminates (i.e. next time, covering started) apart from this coverage gap, when average response
Between average value of the MRT (Mean Response Time) i.e. to the response time of this mesh point.If for regional aim or point mesh
Mark set, then calculate the average value MRT_A of all mesh points.
When sampled point is enough, there is the relationship of average response time and time mean gap to be
Sampling instant point generally can be more when due to statistics, it is contemplated that above-mentioned relation, therefore subsequent do constellation covering performance
" time mean gap " index is not considered further that when indicator-specific statistics formula.
This covering performance index had both considered the statistical property of covering, it is contemplated that the statistical property in gap, therefore very
The performance for comprehensively reflecting whole system is to evaluate the best covering performance index of responsiveness.This covering performance index is to place
Reason communication delay (request and reception delay including data) is very convenient, when communication delay can be applied directly to covering response
Between in, obtain total response time, it indicates to receive total times of the data from user's request data to user.
This index is the singal reporting code of calculation delay, is suitable for communication satellite constellation and designs.
Response time compliance rate PecRT
Response time compliance rate PecRT, that is, mesh point response time in emulation cycle reaches the percentage of a certain thresholding.
If calculating the average value P ecRT_A of all mesh points for regional aim or point target set.
This index is the singal reporting code of calculation delay, is suitable for communication satellite constellation and designs.
Maximum communication time delay SYMax
Maximum communication time delay SYMax, that is, user terminal (or mesh point, do not constitute network) and constellation can communication occasions arrive
Next constellation and terrestrial communication networks system can communication occasions maximum duration length.If being calculated all for area terminal
The average value SYMax_A of terminal or mesh point.
This index is the singal reporting code of calculation delay, is suitable for communication satellite constellation and designs.
Average communication time delay SY_A
Average communication time delay SY_A, that is, user terminal (or mesh point, do not constitute network) and constellation can communication occasions arrive down
Secondary constellation and terrestrial communication networks system can communication occasions average length of time.If calculating all ends for area terminal
The average value SY_AA of end or mesh point.
This index is the singal reporting code of calculation delay, is suitable for communication satellite constellation and designs.
Communication delay compliance rate PecSY
Communication delay compliance rate PecSY, that is, mesh point communication delay in emulation cycle reaches the percentage of a certain thresholding.
If calculating the average value P ecSY_A of all terminals or mesh point for area terminal.
This index is the singal reporting code of calculation delay, is suitable for communication satellite constellation and designs.
Time mean gap TAG
Time mean gap (Time Average Gap) temporally samples the average value for seeking coverage gap, expression
Formula is
This index is the singal reporting code of calculation delay, is suitable for communication satellite constellation and designs.
Step 2, according to the particular task provided, analysis task demand determines the preliminary scale of constellation configuration, provides optional
Constellation.
The application of satellite constellation becomes more diverse in recent years, but the movement characteristic based on satellite itself with respect to the earth, constellation
Application focus primarily upon the following aspects:
(1) it communicates
The main still terrestrial user of the application of telecommunication satellite, current era is an electronic age, the connection between people and people
It is all by electronic communication channel that system, which has 60% or more, and the communication network on ground has it to be difficult to the shortcomings that overcoming satellite is needed to come more
It mends.Meagrely-populated remote mountains on the earth, midoceanic isolated island, the special place etc. for scientific experiment require covering for satellite
Lid is communicated.
The covering of telecommunication satellite is related with the characteristic of load on star, for example, quantum communications load need ground be in ground shadow and
The fine partly cloudy bit error rate that just can ensure that communication does not exceed design thresholding, meets the needs of normal communication.
(2) it navigates
It is similar with the demand of " communication ", it is desirable that the design of constellation guarantees the uniform fold in the whole world, but the difference is that base as far as possible
In terrestrial positioning demand, it is desirable that the number of satellites of synchronization covered ground is more as far as possible, and geometry distribution is preferable.
The scale of navigation satellite is generally large, is related to the relationship for the efficiency that funds are generated with it, therefore prove in project
Initial stage just should quickly choose constellation scale, and do further in-depth argument and analysis, and only analysis project proves initial stage to this patent
The design method of constellation, as the estimation of engineering funds and the determination of preliminary satellite scheme.
(3) remote sensing
Remote sensing satellite is that it needs to be imaged over the ground with " communication ", the maximum difference of " navigation " satellite, this is just and on star
Load type has a very big relationship, and the most common optics loading demands satellite is each when crossing target, and solar elevation has certain pact
Beam, the imaging effect that can have just had in this way, while the lighting requirements based on optical imagery, remote sensing of the earth satellite often have recurrence to want
It asks, light conditions are similar to meet, and for portable extraction target image and do and splice or compare.
Remote sensing satellite application is wider, needs to determine its design constraint according to its Load Characteristics, selects reasonable track and designs
Satellite constellation.
(4) electronic reconnaissance
Reconnaissance spacecraft is chiefly used in military affairs, due to highest priority determines, is not necessarily to Global coverage, there is apparent area
Domain property, and have this qualitative difference since load difference specific on star will lead to the design of constellation configuration.Such as SAR load is due to transmitting
The constraint of the problem of power, orbit altitude can be than stronger, and the constellation of reconnaissance spacecraft has relatively stringent baseline, need
Consider frequency, precision and the demand for fuel of orbits controlling.
Reconnaissance spacecraft constellation is more special, needs according to specific load restraint designed path and constellation configuration.
Step 3, emulation input condition and simulation calculation are determined according to constellation Satellite track feature, provide simulation result,
And constellation superiority and inferiority is judged according to result and to the satisfaction of mission requirements, selects constellation configuration.
The satellite constellation that several typical cases are described in step 2 can basis behind the clear satellite application field of user
Specific requirements design satellite constellation configuration.Firstly, determining the specific distribution of constellation Satellite according to preliminary theory analysis, determine
The smallest size constellation of meet demand；Secondly, determining that emulation is defeated according to the smallest size constellation and task restriction chosen
The characteristics of entering condition, carrying out the correctness of simulating, verifying theory analysis, and explain simulation result by theory analysis, reaches
Purpose that is theoretical and actually combining；Finally, being used for the input of engineering tentative programme according to simulation result selection preferably constellation.
Constellation Design constraint
This patent is carried out low rail and is defended for the subsequent applications demand of the emitted quantum communications satellite (Mo-tse number) in China
Star Constellation Design.Specific constraint condition has:
(1) strong constraint
It must be taken into consideration, i.e., be designed under following precondition before such constraint design.
(1) satellite constrains: the average height of orbit 800km (corresponding semi-major axis 7178.137km), and when southbound node place is 10:
30 sun-synchronous orbit
(2) shadow region can be in ground in call duration time section
It (3) can communication time: greater than 60s
(4) earth station can communication constraint: 15 ° of the elevation angle
(5) coverage goal: -70 °~70 °, 6 ° of Grid simulations
(6) load Field of View Constraint: Rectangular, Vertical:60 ° Horizontal:70 °, i.e. satellite flight direction
± 70 °, perpendicular to heading ± 60 °
(2) weak constraint
Such constraint is the factor of consideration to be taken into account when design, but due to being rough estimation when design, design result can
Certain deviation can be had, at most allows 10% to be unsatisfactory for index.
(1) in the continuous cover time section of satellite, it is less than 30min with coverage gap of the orbital plane adjacent satellite to ground；
(2) in the continuous cover time section of satellite, face orbital plane adjacent satellite and the longest coverage gap on ground is less than
90min。
Determine two class constellations
This constellation requires whole world uniform fold as far as possible, therefore selection has the Walker constellation of uniform properties.
(1) basic conception of Walker constellation
Constellation reference code is T/P/F, and wherein T is constellation Satellite total number, and P is orbital plane number, and F is adjacent for determining
The factor (F=0,1,2,3 ..., P-1) of orbital plane satellite relative phase, the phase phase difference of adjacent orbit face satellite are F constellation
Basic unit PU (Pattern Unit), PU=360 °/T.
(2) number of satellites in same rail face
Satellite is run in the sky is known as nodal period by the time interval of intersection point twice in succession, the table of average nodal period
Up to shown in formula such as formula (3).
Related symbol in formula (3) is explained as follows:
1) a is the flat semi-major axis of satellite orbit；
2) μ=398600.4418 × 109m3/s2For Gravitational coefficient of the Earth；
3)J2=1.08263 × 10-3, it is the humorous term coefficient of earth gravitational field second order band；
4)Re=6378137m, terrestrial equator mean radius；
5) e is the flat eccentricity of satellite orbit；
6) i is the flat inclination angle of satellite orbit.
It is computed, the average nodal period of the sun synchronous satellite of 800km mean orbit height is 101min, and consideration " is defended
In the continuous cover time section of star, coverage gap is less than the weak constraint condition of 30min ", and 4 satellites of cloth can expire in an orbital plane
This condition of foot.
(3) interval of different orbital planes
With terrestrial equator mean radius Re=6378.137km estimation, single star covered ground signal are as shown in Figure 2.
In Fig. 2, A is to cover boundary point on ground, and the intersection point G of the line and earth ellipsoid in satellite and the earth's core is known as satellite
Substar；The tangent line of satellite and the earth is known as the geometric horizon of satellite, and P is known as level point.
According to simple trigonometric function sine relation, have
I.e.
The angle (90 ° of-α-θ) that satellite covering ground can be calculated according to above formula, for 800km mean orbit height
Satellite is constrained according to 15 ° of elevations angle, and calculating 90 ° of-α-θ is 15.88 °, and the corresponding half field angle α that covers over the ground is 59.12 °.For
Satellite in Sun-synchronous orbit, the movement velocity of earth relative satellite are 360 °/our=1 ° for 24 hours/4min, therefore, same satellite
Sub-satellite track under the line on difference of longitude be 101/4=25.25 °.The lower locus of points of adjacent satellite in same orbital plane exists
Difference of longitude on equator is 101/4/4=6.31 °, considers that the weak constraint of design " in the continuous cover time section of satellite, faces orbital plane
Adjacent satellite is less than 90min " to the most short coverage gap on ground, between Preliminary design adjacent orbit face between be divided into 45 °, quite
In southbound node place phase difference 3 hours.It can be found in Fig. 3, Fig. 4.
(4) constellation types are determined
1) first kind constellation-constellation 1
3 orbital planes, 4 satellites of each orbital plane, 45 degree of track face interval (i.e. southbound node local time was every 3 hours),
It is 9:00 when leftmost orbital plane (seed satellite orbit face) southbound node place.
According to the design principle of Walker constellation, (kind component, 135 degree are divided equally 9:00,135/3=when southbound node place
45),12:00,15:00；T=12, P=3, F=2.
2) the second class constellation-constellation 2
With constellation 1 only difference is that being 10 when leftmost orbital plane (seed satellite orbit face) southbound node place:
30。
In view of the transmitting of constellation Satellite can not simultaneously, first batch of star is with selecting the readily selected southbound node for carrying chance
The track of Fang Shiwei 10:30, when southbound node place of other two orbital plane, successively translate 3 hours.
Emulate input requirements
This track is Sun synchronization repeating orbit, and the load operation time is the period that ground is in shadow region, therefore is needed
To consider the relative positional relationship on satellite and the sun and ground comprehensively, before and after selecting the Summer Solstice in 1 year, before and after the Autumnal Equinox, Winter Solstice
The classic regression cycle time section of front and back 3 is as simulation time section.
It is defined according to regression orbit, the recursion period for calculating 800km sun-synchronous orbit is 58 days, selects May in summer
23 days~July 20, autumn August 23~October 20,20 days January 23 days~next year of November in winter are used as simulation time area
Between.
Additionally, it is contemplated that the earth circumsolar period of revolution is 1 year, that is to say, that the relationship of light conditions and earth satellite
Long period be 1 year, 1 year can also be analyzed as simulation time.
It should be understood that if in strict accordance with the relative positional relationship for traversing all earth station, satellite, the sun,
The time interval for needing to emulate is recursion period and 365.25 days least common multiples, i.e., 58 × 365.25=21184.5 days, counts
Calculation amount be it is quite huge, select typical time interval to be emulated here, can be used as engineer application
The foundation of project choice.
Specific simulation result
Since the most important index of telecommunication satellite is coverage gap (also referred to as revisit time), this index determines that satellite can
How long access same place again, therefore, specific implementation of the patent example using average coverage gap as statistical analysis index, and
It chooses type locality 1 (latitude, longitude is all the point on 0 equator) and type locality 2 (Beijing) analyzes 3 periods and 1
Longest coverage gap statistics in year in section of continuous cover time, to verify the Article 2 of weak constraint " when satellite continuously covers
Between in section, face orbital plane adjacent satellite and the longest coverage gap on ground met less than 90min ".Concrete outcome is referring to table 1.
Longest coverage gap in the continuous cover time section of table 1 counts (minute)
About table 1, it is seen that:
(1) for the place 1 on equator, constellation 1 and 2 indifference of constellation；
(2) for northern middle latitude place Beijing, constellation 1 is in January 13 12~next year of November, constellation 2 in September 8
Have the exceeded of 132min~155min in the period in April 10 day~next year as a result, but percentage and be less than 10%, it is former
Because being: being the satellite orbit of the satellite orbit of 15:00 and 16:30 when southbound node place in above-mentioned time interval, there is 1 daily
Secondary of short duration drop rail communication opportunity (schematic diagram is detailed in 5, Fig. 6, Fig. 7), it is right due to only only accounting for rail lift communication when design constellation
In drop rail close to the track in afternoon of the confused line line of demarcation of daytime to night (ground by), the drop rail communication based on season reason is not
In the range of designing consideration, it can not count；
(3) it for the coverage gap of a small amount of 54min of appearance, the reason is that terrestrial elevation angle is too low, loses and a certain star
Can communication opportunity, wait with the adjacent satellite in orbital plane.
In addition, dividing ground region for -70 °~70 ° of earth surface with 6 ° of points, the mesh as analysis covering
Mark region, the average coverage gap of 3 periods of two class constellation of simulation calculation, specific result referring to Fig. 8, Fig. 9, Figure 11,
Figure 12, Figure 14, Figure 15, it is concluded that as follows:
(1) before and after the Autumnal Equinox that the sun is in equator, the average covering of 9:00,10:30 track when southbound node place
Gap is essentially identical, but larger with the average coverage gap difference of 16:30, reason be 16:30 track drop gauge from confused line compared with
Closely (reference can be made to Fig. 8 and Figure 10), increase part drop rail can call duration time, but on the average coverage gap of two class constellations influence simultaneously
It is unobvious, reference can be made to 9.
(2) halcyon days in the Southern Hemisphere is in the sun, with Autumnal Equinox the case where is similar, but differentiation is more obvious, especially
It is embodied in the otherness of 16:30 track southern hemisphere and northern hemisphere covering, reference can be made to Figure 11, Figure 12 and schematic diagram Figure 13.
(3) before and after the Summer Solstice that the sun is in the Northern Hemisphere, 9:00,10:30,16:30 track is averaged when southbound node place
Coverage gap is little in Southern Hemisphere difference, but on the Northern Hemisphere, drop gauge from the morning line line of demarcation of night to daytime (ground by) compared with
The average coverage gap of close 9:00 track and drop gauge 16:30 track closer from confused line is larger on the Northern Hemisphere, and reason is
Summer the arctic nearby be in positive photograph, reduce can call duration time, but on the average coverage gap of two class constellations influence be not obvious,
It can be found in Figure 14, Figure 15 and schematic diagram Figure 16.
To sum up, for the demand of global uniform fold, selection has more the constellation 1 of terminator symmetry；If demand tendency
Covering in the Northern Hemisphere, it may be considered that non-morning and evening symmetrical constellation 2.This judgment criterion can be used as engineering project demonstration according to
According to.
Although some embodiments of the present invention are described in present specification, those skilled in the art
Member is it is understood that these embodiments are merely possible to shown in example.Those skilled in the art under the teachings of the present invention may be used
To expect numerous variant schemes, alternative solution and improvement project without beyond the scope of this invention.The appended claims purport
It is limiting the scope of the invention, and is covering the method in the range of these claims itself and its equivalents and knot whereby
Structure.
Claims (7)
1. a kind of method for determining the configuration of constellation, comprising:
Determine the parameter of constellation；
The optional configuration of constellation is determined according to the parameter；
Emulation input condition is determined according to the satellite orbit feature of constellation and executes emulation；
Configuration is selected from optional configuration according to simulation result.
2. according to the method described in claim 1, wherein the parameter includes one or more of the following:
Cover time indicates that all covering or N% cover the time used by a certain regional aim or point target set；
Space percentage is covered, indicates that any sampling instant is accounted for the percentage in entire analyzed region by the region that satellite covers
Than；
Tuple is averagely covered, indicates any sampling instant to a certain observed object or the simultaneously visible number of satellite of mesh point；
Averagely can communication time, indicate a certain observed object or mesh point single is visible averagely can communication time；
Cover time percentage indicates the time percentage that a certain observed object or mesh point are covered by one or multi-satellite
Than；
Maximal cover gap indicates the maximum duration gap covered twice；
Average coverage gap, indicates the average length of mesh point covering break period；
Time compliance rate is returned to, indicates that mesh point revisit time in emulation cycle reaches the percentage of a certain thresholding；
Average response time indicates the average value for the time that mesh point terminates apart from this coverage gap；
Response time compliance rate indicates that mesh point response time in emulation cycle reaches the percentage of a certain thresholding；
Maximum communication time delay, indicate user terminal and constellation can communication occasions arrive next constellation and terrestrial communication networks system
Can communication occasions maximum duration length；
Average communication time delay, indicate user terminal and constellation can communication occasions arrive next constellation and terrestrial communication networks system
Can communication occasions average length of time；
Communication delay compliance rate indicates that mesh point communication delay in emulation cycle reaches the percentage of a certain thresholding；And
Time mean gap indicates that the average value of coverage gap is sought in temporally sampling.
3. according to the method described in claim 1, further include:
Determine the constraint condition of constellation；And
Optional configuration is selected according to the constraint condition.
4. according to the method described in claim 3, wherein the constraint condition includes Condition of Strong Constraint and weak constraint condition, wherein
Condition of Strong Constraint is the constraint condition that constellation must satisfy, and weak constraint condition is the constraint for allowing constellation to have 10% deviation
Condition；
Wherein Condition of Strong Constraint includes one or more of the following:
800 km of the average height of orbit is the sun-synchronous orbit of 10:30 when southbound node place；
Shadow region can be in ground in call duration time section；
Can communication time be greater than 60 seconds；
Earth station can communication constraint: 15 ° of the elevation angle；
Coverage goal: -70 °~70 °, 6 ° of Grid simulations；And
Load Field of View Constraint: satellite flight direction ± 70 °, perpendicular to heading ± 60 °；
Wherein weak constraint condition includes one or more of the following:
In the continuous cover time section of satellite, with orbital plane adjacent satellite to the coverage gap on ground less than 30 minutes；And
In the continuous cover time section of satellite, face orbital plane adjacent satellite to the longest coverage gap on ground less than 90 minutes.
5. according to the method described in claim 3, wherein the optional configuration of constellation includes the Walker constellation with uniform properties.
6. according to the method described in claim 3, wherein determining emulation input condition according to the satellite orbit feature of constellation and holding
Row emulates
Recursion period is determined according to the recurrence characteristic of constellation；
Simulation time section is determined according to recursion period；And
Emulation is executed in simulation time section.
7. according to the method described in claim 6, wherein the simulation time section includes one or more typical time zones
Between.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910155921.8A CN109861742B (en) | 2019-03-01 | 2019-03-01 | Method for determining constellation configuration |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910155921.8A CN109861742B (en) | 2019-03-01 | 2019-03-01 | Method for determining constellation configuration |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109861742A true CN109861742A (en) | 2019-06-07 |
| CN109861742B CN109861742B (en) | 2021-10-26 |
Family
ID=66899534
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910155921.8A Active CN109861742B (en) | 2019-03-01 | 2019-03-01 | Method for determining constellation configuration |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109861742B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111800182A (en) * | 2020-06-17 | 2020-10-20 | 北京理工大学 | Design method for realizing flexible coverage of global communication constellation |
| CN112073112A (en) * | 2020-08-17 | 2020-12-11 | 东方红卫星移动通信有限公司 | Construction method of reconfigurable constellation with multiple coverage and reconfigurable constellation |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105335541A (en) * | 2014-08-12 | 2016-02-17 | 中国人民解放军装备学院 | Engineering design method for navigation satellite constellation |
| CN106156417A (en) * | 2016-07-04 | 2016-11-23 | 中国人民解放军国防科学技术大学 | Constant duration quickly revisits satellite constellation configuration Optimization Design |
| CN106250616A (en) * | 2016-07-29 | 2016-12-21 | 北京空间飞行器总体设计部 | The aeronautical satellite Constellation availability appraisal procedure estimated based on dynamic reliability |
| CN106446333A (en) * | 2016-08-19 | 2017-02-22 | 航天东方红卫星有限公司 | Optimized design method for configuration of small-scale satellite constellation |
| CN106599398A (en) * | 2016-11-25 | 2017-04-26 | 航天恒星科技有限公司 | Simulation method and apparatus of space-ground integrated management system |
| WO2017068201A1 (en) * | 2015-12-18 | 2017-04-27 | Airbus Defence And Space Limited | Communications constellation optimisation facility |
| CN107329146A (en) * | 2017-07-05 | 2017-11-07 | 中国人民解放军装备学院 | A kind of low rail of aeronautical satellite monitors the Optimization Design of constellation |
| CN107451316A (en) * | 2017-04-01 | 2017-12-08 | 南京航空航天大学 | A kind of configuration design of satellite |
| CN107798187A (en) * | 2017-10-24 | 2018-03-13 | 北京理工大学 | A kind of efficiently satellite constellation Multipurpose Optimal Method |
-
2019
- 2019-03-01 CN CN201910155921.8A patent/CN109861742B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105335541A (en) * | 2014-08-12 | 2016-02-17 | 中国人民解放军装备学院 | Engineering design method for navigation satellite constellation |
| WO2017068201A1 (en) * | 2015-12-18 | 2017-04-27 | Airbus Defence And Space Limited | Communications constellation optimisation facility |
| CN106156417A (en) * | 2016-07-04 | 2016-11-23 | 中国人民解放军国防科学技术大学 | Constant duration quickly revisits satellite constellation configuration Optimization Design |
| CN106250616A (en) * | 2016-07-29 | 2016-12-21 | 北京空间飞行器总体设计部 | The aeronautical satellite Constellation availability appraisal procedure estimated based on dynamic reliability |
| CN106446333A (en) * | 2016-08-19 | 2017-02-22 | 航天东方红卫星有限公司 | Optimized design method for configuration of small-scale satellite constellation |
| CN106599398A (en) * | 2016-11-25 | 2017-04-26 | 航天恒星科技有限公司 | Simulation method and apparatus of space-ground integrated management system |
| CN107451316A (en) * | 2017-04-01 | 2017-12-08 | 南京航空航天大学 | A kind of configuration design of satellite |
| CN107329146A (en) * | 2017-07-05 | 2017-11-07 | 中国人民解放军装备学院 | A kind of low rail of aeronautical satellite monitors the Optimization Design of constellation |
| CN107798187A (en) * | 2017-10-24 | 2018-03-13 | 北京理工大学 | A kind of efficiently satellite constellation Multipurpose Optimal Method |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111800182A (en) * | 2020-06-17 | 2020-10-20 | 北京理工大学 | Design method for realizing flexible coverage of global communication constellation |
| CN111800182B (en) * | 2020-06-17 | 2021-05-18 | 北京理工大学 | Design method for realizing flexible coverage of global communication constellation |
| CN112073112A (en) * | 2020-08-17 | 2020-12-11 | 东方红卫星移动通信有限公司 | Construction method of reconfigurable constellation with multiple coverage and reconfigurable constellation |
| CN112073112B (en) * | 2020-08-17 | 2022-02-15 | 东方红卫星移动通信有限公司 | Construction method of reconfigurable constellation with multiple coverage and reconfigurable constellation |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109861742B (en) | 2021-10-26 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107329146B (en) | Optimal design method for low-orbit monitoring constellation of navigation satellite | |
| Panda et al. | Study of Ionospheric TEC from GPS observations and comparisons with IRI and SPIM model predictions in the low latitude anomaly Indian subcontinental region | |
| Rana et al. | An enhanced method for scheduling observations of large sky error regions for finding optical counterparts to transients | |
| Suvorova et al. | TEC evidence for near‐equatorial energy deposition by 30 keV electrons in the topside ionosphere | |
| Jiang et al. | Influence of spatial gradients on ionospheric mapping using thin layer models | |
| CN109861742A (en) | A method of for determining the configuration of constellation | |
| CN109639338A (en) | One kind being suitable for the distant integral application Global coverage constellation of admittance and its design method | |
| Memon et al. | Determining optimum tilt angle for 1 MW photovoltaic system at Sukkur, Pakistan | |
| Milani et al. | Innovative observing strategy and orbit determination for Low Earth Orbit space debris | |
| CN112769466A (en) | Low-orbit satellite constellation configuration keeping method | |
| da Silva et al. | Comparative analysis of transposition models applied to photovoltaic systems using meteonorm and NASA SSE databases | |
| Yue et al. | GNSS radio occultation technique and space weather monitoring | |
| Plank | VLBI satellite tracking for the realization of frame ties | |
| WO2020066470A1 (en) | Interference power estimation method, interference power estimation device, and program | |
| Loutfi et al. | Interhemispheric asymmetry of the equatorial ionization anomaly (EIA) on the African sector over 3 years (2014–2016): Effects of thermospheric meridional winds | |
| CN106777580B (en) | Method for rapidly designing emission window of near-earth inclined orbit | |
| Wang et al. | Visibility of LEO satellites under different ground network distributions | |
| Barlier et al. | Comparisons between varions semi-empirical thermospheric models of the terrestrial atmosphere | |
| CN103808330B (en) | A kind of star sensor field trial satellite ephemeris computational methods | |
| Abdurrahman et al. | Solar elevation angle and solar culmination determination using celestial observation; a case study of hadejia jigawa state, Nigeria | |
| Mallama | The Sky Distribution and Magnitudes of Starlink Satellites by the Year 2027 | |
| Cesaroni | A multi-instrumental approach to the study of equatorial ionosphere over South America | |
| Sun et al. | Low‐Orbit Large‐Scale Communication Satellite Constellation Configuration Performance Assessment | |
| Thessin | Atmospheric signal delay affecting GPS measurements made by space vehicles during launch, orbit and reentry | |
| Marchaudon et al. | Impact of the dipole tilt angle on the ionospheric plasma as modeled with IPIM |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20230921 Address after: 201306 building C, No. 888, Huanhu West 2nd Road, Lingang New District, China (Shanghai) pilot Free Trade Zone, Pudong New Area, Shanghai Patentee after: Shanghai Zhongkechen New Satellite Technology Co.,Ltd. Address before: No. 4 Building, 99 Haike Road, Pudong New Area, Shanghai, 201203 Patentee before: SHANGHAI ENGINEERING CENTER FOR MICROSATELLITES |