CN110096746A - A kind of satellite cluster preliminary orbit design method and device - Google Patents
A kind of satellite cluster preliminary orbit design method and device Download PDFInfo
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Abstract
The invention discloses a kind of satellite cluster preliminary orbit design method and devices, the present invention uses relative eccentric ratio and orbit inclination angle vector design method, the restrictive conditions such as minimum safe distance and maximum communication distance between foundation primary orbit parameter, cluster satellite quickly generate the cluster satellite orbit specified number, the cluster satellite that this method generates is able to maintain minimum orbit offset under the influence of J2 perturbs, the distance between cluster satellite restrictive condition will not be broken in the relatively long time, because without carrying out orbit adjusting.
Description
Technical field
The invention patent relates to a kind of satellite cluster flight preliminary orbit design method and devices, according to a primary and set
It is fixed to quickly generate satellite cluster track apart from restrictive condition, belong to spacecraft cluster track formation design field.
Background technique
With the development of satellite application demand, more and more space missions cannot be completed only by single satellite,
And must rely on multi-satellite associated working could complete.With the gradually development of international aerospace industry, new space mission is needed
It asks and is constantly proposed, the cluster orbital flight of more star systems such as satellites formation, satellite cluster becomes the one of international space industry
A important directions.It needs to keep particular configuration different from satellites formation, satellite cluster only needs cluster satellite to be maintained at specific
In distance limitation range, more cluster satellites are maintained in closer airspace and run, and realize that information is handed over by inter-satellite link
Mutual and task cooperative.
The advantages that satellite cluster is flexible, task response is fast, high reliablity, reconfigurability are good with its deployment, has attracted the world
The concern of various countries space flight department and scientific research personnel.Compared with the single independent satellite system of tradition, a satellite group of stars is in reliability, task
Diversity, functional expansionary, production cycle, system cost etc. are significantly improved, and are that Future Satellite technology develops
Important directions.Scientific research personnel has done numerous studies to the relative orbit design of formation flight and the theoretical research of control for many years
Work, but substantially satellites formation is a kind of special circumstances formed between closed circuit orbits controlling the additional star of satellite cluster.
Due to the limitation of resource and technical conditions on star, the outer space flight department of Current Domestic only realizes small-scale formation task.Strictly
Formation task in meaning is difficult longtime running, and new observation phenomenon and increasingly complicated space mission cooperate with more satellites
The demand of work, such as multi-platform more means Information acquiring technologies proposed in recent years and space sensor network technique, make
The research work for obtaining satellite cluster seems rather important.
Summary of the invention
The technical problem to be solved in the present invention is that with its deployment, flexible, task is rung for satellite cluster in the prior art
Should be fast, high reliablity, reconfigurability are good the advantages that, provides a kind of satellite cluster preliminary orbit design method and device.
Wherein one side, the present invention according to the present invention solve its technical problem, and used technical solution is: providing
A kind of satellite cluster preliminary orbit design method, comprises the following steps:
S1, variable preset value is obtained first, including the minimum safe distance d between satellitesafe, maximum distance dmax, from star
Quantity N；
The parameter initialization of S2, genetic algorithm: according to (a δ ek)ij∈[dsafe,dmax/ 2], (a δ ik)ij∈[dsafe,dmax]
Generate one group of δ e at random respectivelykWith δ ikValue；Concurrently set αkValue and αkFor fixed value, and set relative eccentric ratio vector
Angular amountOr 3 pi/2；Wherein, vector parameters of the k representative from star with respect to primary are designated as under, a indicates the length of primary
The length of semiaxis, that subscript ij is indicated is any satellite i and satellite j, δ ekIndicate relative eccentric ratio, δ ekTable is to orbit inclination angle；
S3, it solves initial optimization value: considering minimum safe distance constraintUnder the premise of objective function,
One group of δ e is solved using genetic algorithmkWith δ ikOptimal value；The mathematical model of genetic algorithm is as follows:
Objective function are as follows:
Constraint condition are as follows:
Wherein,Indicate the minimum range between any two satellite i, j, It indicates
The angular amount of relative orbit dip vector；
S4, judgment step S3 solve resulting δ ekWith δ ikWhether maximum distance constraint condition is met
Group optimization solution meets cluster Track desigh requirement if meeting, and terminates parametric solution process and goes to S6；Turn if being unsatisfactory for
Continue parameter optimization to step S5 to solve；Wherein,Indicate the maximum distance between any two satellite i, j；
S5, the optimization solution δ e that will be acquired using genetic algorithmkAnd δ ikAs MATLAB nonlinear constrained optimization function
The initial value of fmincon continues to carry out non-linear solution to the above Optimized model, goes to step S6；
S6, the resulting parameter δ e of step S4 or S5 is utilizedkAnd δ ik, bring into from star orbital tracking solution procedure, solution pair
The slave star orbital road six roots of sensation number answered terminates.
Further, in satellite cluster preliminary orbit design method of the invention, step S6 is specifically included from star in master
Final relative eccentric ratio δ e in star coordinate systemk, dip vector δ ikValue after be calculated accordingly from star orbit parameter, with
Under be from star orbit parameter according to primary orbit parameter solution procedure:
(1) it is diversion to form stable formation, the major semiaxis a from star should be made2With the major semiaxis a of primary1It is equal, i.e. a2=
a1；
(2) eccentricity from star with respect to primary is according to formula
It acquires；e1Indicate the eccentricity of primary, ω1Indicate the argument of perigee of primary；
(3) orbit inclination angle from star with respect to primary is according to formulaIt acquires；i1Indicate primary
Orbit inclination angle；
(4) right ascension of ascending node from star with respect to primary is according to formulaIt acquires；Ω1
Indicate the right ascension of ascending node of primary；
(5) argument of perigee from star with respect to primary is according to formula ω2=acos ((δ ekcosθk+e1cosω1)/e2) ask
?；A=a1；
(6) mean anomaly from star with respect to primary is according to formula
It acquires；Wherein, M1Indicate the mean anomaly of primary.
Further, in satellite cluster preliminary orbit design method of the invention,It is calculated according to following formula
It obtains:
It is calculated according to following formula:
Further, in satellite cluster preliminary orbit design method of the invention, α in step S2k=0.
According to another aspect of the present invention, the present invention is to solve its technical problem, and it is initial to additionally provide a kind of satellite cluster
Track desigh device, has computer storage medium, for storing the instruction of computer feasibility, the computer feasibility instruction
For realizing above-mentioned satellite cluster preliminary orbit design method.
The present invention uses relative eccentric ratio and orbit inclination angle vector design method, according to primary orbit parameter, cluster satellite
Between minimum safe distance and the restrictive conditions such as maximum communication distance quickly generate the cluster satellite orbit specified number, the party
The cluster satellite that method generates is able to maintain minimum orbit offset under the influence of J2 perturbs, in the relatively long time cluster satellite it
Between will not be broken apart from restrictive condition, because without carry out orbit adjusting.
Detailed description of the invention
Present invention will be further explained below with reference to the attached drawings and examples, in attached drawing:
Fig. 1 is the flow chart of one embodiment of satellite cluster preliminary orbit design method；
Fig. 2 is satellite cluster set interface；
Fig. 3 is satellite cluster two and three dimensions display window；
Fig. 4 is the local coordinate system display window centered on primary；
Fig. 5 is satellite cluster distance change tendency chart.
Specific embodiment
For a clearer understanding of the technical characteristics, objects and effects of the present invention, now control attached drawing is described in detail
A specific embodiment of the invention.
It is the flow chart of one embodiment of satellite cluster preliminary orbit design method of the invention with reference to Fig. 1.In this implementation
In example, satellite cluster preliminary orbit design method of the invention is comprised the following steps:
S1, variable preset value is obtained first, including the minimum safe distance d between satellitesafe, maximum distance dmax, from star
Quantity N, N are positive integer；
The parameter initialization of S2, genetic algorithm: according to (a δ ek)ij∈[dsafe,dmax/ 2], (a δ ik)ij∈[dsafe,dmax]
Generate one group of δ e at random respectivelykWith δ ikValue；Concurrently set αkValue and αkFor fixed value, such as αk=0, and set relatively inclined
The angular amount of heart rate vectorOr 3 pi/2；Wherein, vector parameters of the k representative from star with respect to primary are designated as under, a is indicated
The length of the major semiaxis of primary, that subscript ij is indicated is any satellite i and satellite j, δ ekIndicate relative eccentric ratio, δ ekTable is to rail
Road inclination.
Wherein,Or 3 pi/2 be to analyze influence of the J2 perturbation factors to any two satellite orbit ranging offsets
The corresponding restrictive condition obtained.
S3, it solves initial optimization value: considering minimum safe distance constraintUnder the premise of objective function,
One group of δ e is solved using genetic algorithmkWith δ ikOptimal value；The mathematical model of genetic algorithm is as follows:
Objective function are as follows:
Constraint condition are as follows:
Wherein,Indicate the minimum range between any two satellite i, j, It indicates
The angular amount of relative orbit dip vector；
S4, judgment step S3 solve resulting δ ekWith δ ikWhether maximum distance constraint condition is met
Group optimization solution meets cluster Track desigh requirement if meeting, and terminates parametric solution process and goes to S6；Turn if being unsatisfactory for
Continue parameter optimization to step S5 to solve；Wherein,Indicate the maximum distance between any two satellite i, j.
S5, the optimization solution δ e that will be acquired using genetic algorithmkAnd δ ikAs MATLAB nonlinear constrained optimization function
The initial value of fmincon continues to carry out non-linear solution to the above Optimized model, goes to step S6.
S6, the resulting parameter δ e of step S4 or S5 is utilizedkAnd δ ik, bring into from star orbital tracking solution procedure, solution pair
The slave star orbital road six roots of sensation number answered terminates.From final relative eccentric ratio δ e of the star in primary coordinate systemk, dip vector δ ik's
Be calculated after value be below accordingly from star orbit parameter from star orbit parameter according to primary orbit parameter solution procedure:
(1) it is diversion to form stable formation, the major semiaxis a from star should be made2With the major semiaxis a of primary1It is equal, i.e. a2=
a1；
(2) eccentricity from star with respect to primary is according to formula
It acquires；e1Indicate the eccentricity of primary, ω1Indicate the argument of perigee of primary；
(3) orbit inclination angle from star with respect to primary is according to formulaIt acquires；i1Indicate primary
Orbit inclination angle；
(4) right ascension of ascending node from star with respect to primary is according to formulaIt acquires；Ω1
Indicate the right ascension of ascending node of primary；
(5) argument of perigee from star with respect to primary is according to formula ω2=acos ((δ ekcosθk+e1cosω1)/e2) ask
?；A=a1；
(6) mean anomaly from star with respect to primary is according to formula
It acquires；Wherein, M1Indicate the mean anomaly of primary.
Wherein, in above-mentioned step S3 and S4,It is calculated according to following formula:
It is calculated according to following formula:
It is following to be described below partial parameters meaning for the ease of the understanding to above scheme, belong to this field
Common knowledge.
Wherein, subscript x indicates that the component in the direction x, subscript y indicate the component in the direction y.
Description of test
Related initial parameter is provided that
1. minimum safe distance is arranged are as follows: 0.1km
2. maximum communication distance is arranged are as follows: 10km
3. being arranged from star number mesh are as follows: 5
4. the setting of primary orbit parameter is as follows
As shown in table 1, the orbit parameter that primary is arranged is respectively as follows: semi-major axis 7178km, and eccentricity 0.0001, track inclines
Angle is 98.4 degree, and argument of perigee is 30 degree, and right ascension of ascending node is 0.25 degree, and true anomaly is 30 degree.
1 primary track six roots of sensation number of table
| Semi-major axis | Eccentricity | Orbit inclination angle | Argument of perigee | Right ascension of ascending node | True anomaly |
| 7178 | 0.0001 | 98.4 | 30 | 0.25 | 30 |
5. solving resulting from star orbital tracking
It is a set interface of satellite cluster as shown in Figure 2, as can be seen from the figure we need to input 3 parameters,
It is the slave star number mesh of the minimum safe distance of cluster satellite, maximum communication distance and cluster satellite respectively, after setting parameter
Clicking confirming button can automatically generate from the orbit parameter of star and establish the satellite orbit from star in software.
Table 2 is from star orbital road six roots of sensation number
It is to be generated after being 5 from star number mesh maximum distance is arranged as 10km, minimum range 0.1km as shown in table 2
From star orbital road six roots of sensation number.
Fig. 3 is the view of the slave star generated and primary in two and three dimensions space, very due to the distance between satellite cluster
It is small so can not specifically distinguish each satellite in the two views in the relative position in space, therefore joined in CSTK with
Primary is the satellite cluster local coordinate system at visual angle center to facilitate the opposite variation relation in space observed between each cluster satellite,
The local coordinate system display window centered on primary as shown in Figure 4, in the window 5 satellites on the left side be generate from
One satellite of star, the right is primary.
In addition, being exactly to need constantly paying close attention between cluster satellite in simulating scenes duration after establishing satellite cluster
Distance change is the satellite cluster distance change of the middle interface the CSTK real-time display in one month emulation duration as shown in Figure 5
Figure, as can be seen from the figure upper part is that the maximum distance between each satellite calculated changes over time, and variation range exists
Between 4.5km-10km, meet maximum distance less than 10km requirement.A width figure is then the most narrow spacing calculated between each satellite below
From changing over time, variation range meets the requirement that minimum range is greater than 0.1km between 0.1km-0.22km.Hence it is demonstrated that
The design method is highly effective clustering design scheme.
The embodiment of the present invention is described with above attached drawing, but the invention is not limited to above-mentioned specific
Embodiment, the above mentioned embodiment is only schematical, rather than restrictive, those skilled in the art
Under the inspiration of the present invention, without breaking away from the scope protected by the purposes and claims of the present invention, it can also make very much
Form, all of these belong to the protection of the present invention.
Claims (5)
1. a kind of satellite cluster preliminary orbit design method, which is characterized in that comprise the following steps:
S1, variable preset value is obtained first, including the minimum safe distance d between satellitesafe, maximum distance dmax, from star number amount
N；
The parameter initialization of S2, genetic algorithm: according to (a δ ek)ij∈[dsafe, dmax/ 2], (a δ ik)ij∈[dsafe, dmax] respectively
One group of δ e is generated at randomkWith δ ikValue；Concurrently set αkValue and αkFor fixed value, and set the angle of relative eccentric ratio vector
MeasurementOr 3 pi/2；Wherein, vector parameters of the k representative from star with respect to primary are designated as under, a indicates the major semiaxis of primary
Length, subscript ij indicate be any satellite i and satellite j, δ ekIndicate relative eccentric ratio, δ ekTable is to orbit inclination angle；
S3, it solves initial optimization value: considering minimum safe distance constraintUnder the premise of objective function, use
Genetic algorithm solves one group of δ ekWith δ ikOptimal value；The mathematical model of genetic algorithm is as follows:
Objective function are as follows:
Constraint condition are as follows:
Wherein,Indicate the minimum range between any two satellite i, j, Indicate opposite
The angular amount of orbit inclination angle vector；
S4, judgment step S3 solve resulting δ ekWith δ ikWhether maximum distance constraint condition is metIf full
Sufficient then group optimization solution meets cluster Track desigh requirement, terminates parametric solution process and goes to S6；Step is gone to if being unsatisfactory for
S5 continues parameter optimization solution；Wherein,Indicate the maximum distance between any two satellite i, j；
S5, the optimization solution δ e that will be acquired using genetic algorithmkAnd δ ikAs MATLAB nonlinear constrained optimization function fmincon's
Initial value continues to carry out non-linear solution to the above Optimized model, goes to step S6；
S6, the resulting parameter δ e of step S4 or S5 is utilizedkAnd δ ik, bring into from star orbital tracking solution procedure, solve corresponding
From star orbital road six roots of sensation number, terminate.
2. satellite cluster preliminary orbit design method according to claim 1, which is characterized in that step S6 specifically include from
Final relative eccentric ratio δ e of the star in primary coordinate systemk, dip vector δ ikValue after be calculated accordingly from star orbital road
Parameter is the solution procedure from star orbit parameter according to primary orbit parameter below:
(1) it is diversion to form stable formation, the major semiaxis a from star should be made2With the major semiaxis a of primary1It is equal, i.e. a2=a1；
(2) eccentricity from star with respect to primary is according to formula It asks
?；e1Indicate the eccentricity of primary, ω1Indicate the argument of perigee of primary；
(3) orbit inclination angle from star with respect to primary is according to formulaIt acquires；i1Indicate the track of primary
Inclination angle；
(4) right ascension of ascending node from star with respect to primary is according to formulaIt acquires；Ω1It indicates
The right ascension of ascending node of primary；
(5) argument of perigee from star with respect to primary is according to formula ω2=acos ((δ ekcosθk+e1cosω1)/e2) acquire；a
=a1；
(6) mean anomaly from star with respect to primary is according to formula It asks
?；Wherein, M1Indicate the mean anomaly of primary.
3. satellite cluster preliminary orbit design method according to claim 1, which is characterized in thatAccording to following
Formula is calculated:
It is calculated according to following formula:
4. satellite cluster preliminary orbit design method according to claim 1, which is characterized in that α in step S2k=0.
5. a kind of satellite cluster preliminary orbit designs device, which is characterized in that have computer storage medium, calculated for storing
The instruction of machine feasibility, the computer feasibility instruction is for realizing at the beginning of satellite cluster according to any one of claims 1-4
Beginning rail design method.
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| CN110789739A (en) * | 2019-11-08 | 2020-02-14 | 中国人民解放军国防科技大学 | Method for quickly estimating optimal speed increment of long-time rail crossing under J2 perturbation |
| CN114265432A (en) * | 2021-12-20 | 2022-04-01 | 中国科学院空间应用工程与技术中心 | Satellite cluster control method and system based on earth orbit |
| CN114460952A (en) * | 2022-01-17 | 2022-05-10 | 上海卫星工程研究所 | Double-satellite cooperative orbit transfer method and system for initializing orbit tracing configuration |
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