CN110398734A - Distributed SAR Formation Configuration Autonomous maintenance control method - Google Patents
Distributed SAR Formation Configuration Autonomous maintenance control method Download PDFInfo
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
- G01S13/88—Radar or analogous systems specially adapted for specific applications
- G01S13/89—Radar or analogous systems specially adapted for specific applications for mapping or imaging
- G01S13/90—Radar or analogous systems specially adapted for specific applications for mapping or imaging using synthetic aperture techniques, e.g. synthetic aperture radar [SAR] techniques
- G01S13/9021—SAR image post-processing techniques
- G01S13/9023—SAR image post-processing techniques combined with interferometric techniques
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
- G01S13/88—Radar or analogous systems specially adapted for specific applications
- G01S13/89—Radar or analogous systems specially adapted for specific applications for mapping or imaging
- G01S13/90—Radar or analogous systems specially adapted for specific applications for mapping or imaging using synthetic aperture techniques, e.g. synthetic aperture radar [SAR] techniques
- G01S13/904—SAR modes
- G01S13/9058—Bistatic or multistatic SAR
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S7/00—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00
- G01S7/02—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S13/00
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Abstract
Distributed SAR Formation Configuration Autonomous maintenance control method of the present invention, includes the following steps: step 1, obtains the relative motion relation of configuration, establishes the relationship between baseline and configuration；Step 2, Autonomous maintenance control threshold is obtained；Step 3, according to control threshold and the deviation being currently configured, configuration is adjusted.Compared with prior art, the present invention is started to control with following the utility model has the advantages that 1) determining threshold value, and Satellite Formation Flying collides caused by can avoid because of mis-ignition；2) strategy that region disconnecting is maintained based on application and igniting, improves satellite service efficiency；3) satellite igniting maintains region that can not be imaged, and can avoid double star and mutually penetrates the spaceborne electronic component of damage.
Description
Technical field
It flies the present invention relates to a kind of Satellite Formation Flying and is configured maintain control method, specifically a kind of consideration maintains control
The method for carrying out Formation Configuration maintenance control strategy design is influenced on mapping baseline.
Background technique
SAR Satellites system is a kind of based on interferometry theory and method, using active microwave sensor as core
The high-precision space survey satellite system of the heart.It, can be with whole day using the SAR sensor with multi-channel function as payload
It waits, obtain to round-the-clock high-resolution interferometer radar image and corresponding auxiliary data, major product in global range and be ground
Face digital elevation model (DEM) and orthorectified SAR image meet the needs of the detailed mapping product in global key area.It is distributed
SAR satellite system Formation Configuration in orbit during, by space perturbative force and form into columns maintain control error caused by initial equilibrium state
There are Divergent Phenomenons for deviation effects, and configuration divergence can be wanted beyond SAR Satellites system imaging baseline over time
It asks, causes satellite load that can not be imaged.Therefore, the main target of Formation Configuration Autonomous maintenance control is exactly to overcome perturbation
Influence to imaging baseline, it is ensured that baseline meets mapping mission requirements always.Meanwhile it being obtained to simplify fleet system image
The design of strategy, the primary track usually revisited with stabilization, accurately are that foundation plans its imaging strategies, therefore is configured maintain control
It is mainly adjusted by from the relative orbit of star and primary and realizes.
The prior art, Chinese invention patent " a kind of satellite Autonomous control system for realizing distributed formation flight "
(publication number: 103676955B) discloses a kind of satellite Autonomous control system for realizing distributed formation flight, the autonomous control
System is made of six channels.The system is embedded in satellite controller, under the managing and control system of existing satellite, can be shifted to an earlier date
Rail control instruction is generated, provides time for the heating of engine catalytic bed, attitude maneuver, ground verification etc..The system pass through by
Channel control instruction collection is stored in the RAM of satellite controller, wherein being stored in by the channel control instruction collection of recursive call dynamic
In state data flow, avoiding problems the occupancy to resource on the stars such as database and data query.Present system is embedded in each
It is called in the form of relatively independent subprogram in satellite controller, i.e., managing and control system is in each moment poll from backbone
Control process.Present system can be used as the supplement of managing and control system on existing star, manage software systems without being directed on original star
It redesigns.Tasks and the ginsengs such as present system can be realized the formation configuration capture of satellite, formation reconfiguration, configuration maintain
Function is withdrawn with fault satellites in formation.
The prior art is to control in itself from the maintenance to configuration, does not consider influence of the control to imaging baseline, nothing
The mapping demand of method guarantee system.
Summary of the invention
For the defects in the prior art, the object of the present invention is to provide a kind of distributions for solving above-mentioned technical problem
SAR Formation Configuration Autonomous maintenance control method.
In order to solve the above-mentioned technical problem, distributed SAR Formation Configuration Autonomous maintenance control method of the present invention, including such as
Lower step:
Step 1, the relative motion relation for obtaining configuration establishes the relationship between baseline and configuration；
Step 2, Autonomous maintenance control threshold is obtained；
Step 3, according to control threshold and the deviation being currently configured, configuration is adjusted.
Preferably, step 1 includes:
Step 1.1, the relative motion relation of configuration is obtained；
Step 1.2, the relationship between baseline and configuration is established；
Step 1.3, the relationship between space perturbative force and configuration is obtained；
Step 1.4, path in elevation is obtained to baseline maximum deviation amount and along course made good baseline maximum deviation amount.
Preferably, step 1.1 includes: that the description vectors δ α of definition configuration meets:
In formula, a is main star semi-major axis of orbit, adFor from star semi-major axis of orbit, e is primary eccentricity, edIt is eccentric from star
Rate, i are main star orbital road inclination, and M is main star orbital road mean anomaly, and f is main star orbital road true anomaly, and ω is primary perigee width
Angle, ωdFor from star argument of perigee, Ω is primary right ascension of ascending node, ΩdFor from star right ascension of ascending node, u is main star orbital latitude
Argument；udFor from star orbital latitude argument；ex=ecos ω, ey=esin ω；
exd=ed cosωd,eyd=edsinωd；δ is formation double star orbit element differences, and δ a is from star and primary semi-major axis
Difference, δ λ are, δ e poor along track from star and primaryxFor double star E vector difference x to component, δ eyThe y of double star E vector difference to component,
δixFor double star I vector difference x to component, δ iyFor double star I vector difference y to component.
Preferably, step 1.2 includes:
BECT=| δ rrsinφ+δrncosφ|
In formula, BECTFor vertical virtual base, BATFor along track baseline, φ is radar beam projectional angle, δ rr、 δrnAnd δ rt
Meet respectively:
In formula,For the initial phase in configuration plane, andθ
=arctan (δ iy/δix) be configuration plane outside initial phase；
Preferably, step 1.3 includes:
Influence of the analysis space perturbative force for configuration, available configuration is by analysis space perturbative force Perturbation Effect are as follows:
In formula:
Atmospheric drag may be expressed as: configuration affect
In formula,Δ B is that two area-to mass ratio of satellite are poor, and ρ is atmospheric density, v
For satellite, speed, J2 are the humorous constant of earth aspheric, R in orbiteFor terrestrial equator radius；N is formation primary angular speed, u
It (t) is t moment primary latitude argument, u0For initial time primary latitude argument, t indicates to form into columns and run from initial time
Time.
Preferably, step 1.4 includes:
Path in elevation is obtained to baseline maximum deviation
In formula,For configuration plane internal phase angle divergence, Δ iyFor divergence outside configuration plane；
It obtains along course made good baseline maximum deviation amount
In formula, δ rr2It is perturbation configuration along track long term bias amount, δ rraIt is controlled for semi-major axis long along track caused by residual error
Phase offset, δ rrFor atmospheric drag long term bias amount.
Preferably, step 2 includes:
Step 2.1, it obtains and maintains control threshold in plane；
Step 2.2, it obtains and maintains control threshold outside plane.
Preferably, it is T that step 2.1, which includes: that configuration maintains the control period in selected plane,i, TiMeet:
It then can be obtained and control Ct value in plane
In formula, Δ B 'ECTxVertical effective divergence caused by be configured radially, k are reserved safety coefficient,For
Maintain control cycle TiIt is configured caused by J2 perturbation along track long term bias amount in time,To maintain to control cycle TiWhen
Along track long term bias amount caused by interior semi-major axis control residual error,To maintain to control cycle TiAtmospheric drag in time
Long term bias amount；
Step 2.2 includes: to obtain to maintain control threshold outside plane
In formula, Δ B 'ECTzThe vertical virtual base variable quantity dissipated for amplitude outside plane.
Preferably, step 3 includes:
Step 3.1, control in plane；
Step 3.2, it is controlled outside plane.
Preferably, step 3.1 includes: the desired value δ e obtained after pulse control twiceman；
δemanMeet:
In formula,For the maximum allowable offset of relative eccentric ratio argument of vector, nom is the nominal change for maintaining control reference
Amount；
Step 3.2 includes: to obtain desired value δ i after ignitingman；
δimanMeet:
Compared with prior art, the present invention have it is following the utility model has the advantages that
1) determine threshold value to start to control, Satellite Formation Flying collides caused by can avoid because of mis-ignition；
2) strategy that region disconnecting is maintained based on application and igniting, improves satellite service efficiency；
3) satellite igniting maintains region that can not be imaged, and can avoid double star and mutually penetrates the spaceborne electronic component of damage.
Detailed description of the invention
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention
Objects and advantages will become more apparent upon.
Fig. 1 is flow diagram of the present invention；
Fig. 2 is that E vector of the present invention is taken the photograph variation schematic diagram；
Fig. 3 is that I vector of the present invention is taken the photograph variation schematic diagram.
Specific embodiment
The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the common skill of this field
For art personnel, without departing from the inventive concept of the premise, several changes and improvements can also be made.These belong to this
The protection scope of invention.
As shown in FIG. 1 to 3, the present invention includes the following steps:
(1) Formation Configuration mathematical description
According to Formation Configuration relative kinematic C-W equation, compiled using the distributed SAR near-circular orbit of orbit element differences description
Team's configuration can be described as
In formula, rrIndicate configuration x to scale, rtIndicate configuration y to scale, rnIndicate configuration z to scale；A is main star orbital
Road semi-major axis, e are primary eccentricity, and i is main star orbital road inclination, and M is main star orbital road mean anomaly, and f is the main true near point in star orbital road
Angle, ω are primary argument of perigee.Δ indicate configuration primary with from star orbital road parameter difference.By shown in formula (1), define new
Being configured description vectors δ α is
In formula, no subscript indicates primary orbit parameter, and subscript d is indicated from star orbit parameter.Ω is primary right ascension of ascending node,
U=ω+f is main star orbital latitude argument；ex=ecos ω, ey=esin ω；δ indicates formation double star orbit element differences, δ a table
It is poor from star and primary semi-major axis to show, δ λ indicates, δ e poor along track from star and primaryxIndicate the x of double star E vector difference to component, δ ey
The y of double star E vector difference is to component, δ ixIndicate the x of double star I vector difference to component, δ iyIndicate the y of double star I vector difference to component.
δ λ is compositional variable, describes in formula 2, no longer describes.In near-circular orbit short distance formation constraint condition, δ exWith δ eyIt can simplify
For
Formula (3), which are substituted into after formula (1) simplifies, which can obtain the Formation Configuration kinematical equation based on E/I vector description, is
Further the formula can simplify for
In formula,For the initial phase in configuration plane, andθ
=arctan (δ iy/δix) be configuration plane outside initial phase, equally haveDefinitionIt is nominal
Configuration parameters, i=1 in formula, 2 ..., 6.
(1) Formation Configuration baseline defines
By SAR Satellites system DEM mapping and GMTI mission requirements, the interference baseline that Formation Configuration generates has two
Kind, first is that being used for the vertical virtual base (EffectiveCrossTrackBaseline) of DEM, relative position is in thunder between star
The vertical direction for projecting to wave beam radial direction again is projected in up to wave beam sagittal plane；Second is that for GMTI along track baseline
(AlongTrackBaseline), between star relative position in the projection along track direction.It can according to the definition of interference baseline
Know, vertical virtual base BECTFor
BECT=| δ rrsinφ+δrncosφ| (12)
In formula, φ is radar beam projectional angle, takes "+" number to left side projection, takes "-" number to the right projection.
Along track baseline BATIs defined as:
(2) configuration is taken the photograph emission analysis
Following influence of the analysis space perturbative force for configuration.In general, median orbital elements caused by being perturbed as J2 becomes
Changing situation can be described as
In formula,J2 is the humorous constant of earth aspheric, ReFor terrestrial equator radius.
Formula (18), which are substituted into after (2) simplify, to be obtained:
Variation situation is taken the photograph based on above formula configuration parameters, the J2 perturbation configuration ginseng based on E/I vector description can be obtained after integral
Number changes situation
In formula:
δ a indicates poor from star and primary semi-major axis,For initial phase in configuration plane, n is formation primary angular speed, u (t)
For t moment primary latitude argument, u0For initial time primary latitude argument, t indicates to form into columns when having run from initial time
Between.
(a) E vector is taken the photograph variation (b) I vector and is taken the photograph variation
E/I vector is perturbed by J2 to be changed, although the atmospheric density of Near Earth Orbit Satellites environment is relatively thin, satellite
It still is influenced to influence in the presence of drop rail by atmospheric drag when in orbit.Generally, Near Earth Orbit Satellites are by atmospheric drag shadow
It can be described as caused by sound along course made good diverging acceleration
In formula, ρ is atmospheric density, and v is satellite speed in orbit, B=CDA/m is area-to mass ratio of satellite.It is resulting from
Radial (semi-major axis) drift rate and its long term drift error caused by along course made good are represented by
Δ B is that two area-to mass ratio of satellite are poor.
(3) baseline dissipates Analysis on Mechanism
From vertical virtual base and along track baseline definition it is found that influence of the space perturbative force to Formation Configuration will cause
The variation of baseline maintains the target of control to be to ensure that in the satellite life-span in-orbit period that providing satisfaction mapping always appoints based on configuration
The baseline that business requires.Therefore it maintains the selection of control strategy and the situation of change of baseline to have direct relation, needs to send out baseline
Scattered mechanism is analyzed.
1. vertical virtual base dissipates mechanism
It is found that under the influence of the perturbative force of space, vertical virtual base is mainly configured for definition according to vertical virtual base
Initial phase in plane(YES) and path in elevation are to δ iyIt is influenced by variable quantity is taken the photograph.Two classes are taken the photograph into variable quantity and substitute into formula
(12) it can be obtained after simplifying processing
In formula,For configuration plane internal phase angle divergence, Δ iyFor divergence outside configuration plane.It can according to formula (24)
Know, with the in-orbit flight of fleet system, path in elevation can be further simplified as to baseline maximum deviation amount
From above formula it is found that vertical effectively divergence Δ B ' caused by being configured radiallyECTxMainly by configuration plane
It is configured scale and phase angular displacement caused by the control period is maintained to determine；Vertical effectively hair caused by being dissipated outside configuration plane
Dissipate amount Δ B 'ECTzMainly by configuration plane outside dimensional variation amount determine.
2. dissipating mechanism along track baseline
Similarly, define according to along course made good baseline it is found that under the influence of the perturbative force of space, along track virtual base mainly by
It is configured radial phaseVariable quantity, J2 perturbation configuration are taken the photograph along track long term bias amount δ rr2, semi-major axis control residual error caused by
Along track long term bias amount δ rraWith atmospheric drag long term bias amount δ rrInfluence.Several classes are taken the photograph into variable quantity and substitute into formula (13)
It can be obtained after simplifying processing
According to above formula it is found that with the in-orbit flight of fleet system, can be further simplified along course made good baseline maximum deviation amount
For
From above formula it is found that along track baseline maximum deviation amount perturbed respectively as J2 caused by configuration plane periodically deviation
Amount, along track long term drift amount；Semi-major axis controls caused by residual error caused by the track long term drift amount and atmospheric drag along boat
Three parts of mark long term drift amount form.
(4) configuration Autonomous maintenance control threshold is chosen
Mechanism result of study is dissipated according to two class baseline of distributed SAR fleet system, configuration maintains control threshold both can be with
Select using vertical virtual base as target, also can choose using along course made good baseline as target；It even can be with All factors being equal, preference will be give to grade
Vertical virtual base is judged respectively or whether exceeds mapping mission requirements along track virtual base, and is planned in any case
Maintain control firing pulse.But from the relative stability angle for maintaining the control period is ensured, due to being configured along track
It is controlled residual error by configuration semi-major axis to baseline offset to be affected, there are biggish uncertainties, therefore are configured maintain control threshold
It selects to meet based on vertical virtual base application demand, the requirement along track baseline is combined, so that distributed SAR is defended
When star system maintain control according to vertical virtual base, it can satisfy mapping mission requirements always along track virtual base.
Principle accordingly is planned in plane separately below and is configured maintain control threshold Selection Strategy outside plane.
1. maintaining control threshold to choose in plane
It is only made from vertical virtual base and configuration diverging mechanism result of study it is found that being configured initial phase divergence in plane
At some factors that vertical virtual base dissipates, but it is relatively slow because being configured scale divergence speed outside plane, it can be ensured that and configuration is flat
Control effect is maintained within this range outside face.Assuming that vertical effectively diverging caused by being configured radially when task design
Amount is Δ B 'ECTx, it is Δ B ' by the vertical virtual base variable quantity that amplitude outside configuration plane dissipatesECTz, desired configuration maintenance
The control period is Ti, and above-mentioned variable substitution (25) can be obtained and maintain control threshold δ e in configuration planemaxFor
In formula, k >=1 is that reserved safety coefficient generally takes k=1.5.From formula (28) it is found that configuration maintains control threshold in plane
Value δ emaxCycle T is controlled with maintenanceiLinearly proportional, proportionality coefficient dissipates rate by being configured scale and phase in plane
It determines.At this time, it is desirable that configuration is along the vertical virtual base divergence Δ B ' of course made goodATMeet
In formula,It indicates to maintain control cycle TiIt is configured caused by J2 perturbation along track long term bias amount in time,It indicates to maintain control cycle TiAlong track long term bias amount caused by semi-major axis control residual error in time,It indicates
Maintain control cycle TiAtmospheric drag long term bias amount in time.
2. maintaining control threshold to choose outside plane
Equally, from vertical virtual base and configuration diverging mechanism result of study it is found that being configured scale divergence outside plane is
Cause another part factor of vertical virtual base diverging.If maintaining control threshold to estimate when choosing according to configuration in plane
Baseline variation delta B 'ECTz, then it is configured maintain control threshold δ i outside planemaxFor
According to above formula, if dissipating rate in conjunction with configuration plane external measurement, when maintaining control threshold outside given plane,
Control cycle T is maintained given configuration outside configuration plane indirectlyo。
(5) Autonomous maintenance control strategy
State metric data calculates configuration dynamic parameter δ α between distributed SAR system is first depending on stari(i=1,2 ...,
6), and according to star the nominal configuration parameters that big circuit uploadsIt is inside and outside partially that configuration plane is generated respectively
Difference；Current configuration deviation is judged secondly, being based on perturbation by star upper rail control system and starting to control threshold value, and in structure
Starting configuration maintains to control operation when shape deviation exceeds given threshold, maintains control algolithm to calculate generation by configuration and maintains control
Firing pulse amount processed and moment.Finally, driving hydrazine propeller carries out maintaining control ignition operation, complete to maintain control task.
1. control in plane
When | | δ e- δ enom| | exceed δ emaxWhen open control, nom indicates to maintain the nominal data of control reference.
According to Gauss perturbation equation, igniting pulsed quantity δ v can be controlled to two in planet1、δvt2And its at the time of corresponding
Are as follows:
In formula, δ eman、δamanIt is the desired value twice after pulse control, δ e, δ a are true before first time pulse control
Value, uM1And uM2Respectively apply the latitude argument of two subpulses, δ emanSpecifically:
In formula,It is the maximum allowable offset of relative eccentric ratio argument of vector:
δamanSpecifically:
In formula,Indicate J2The variable quantity of δ u in the period is controlled at one caused by, and is had:
Δ t is the control period.δuDIt indicates to control the variable quantity of δ u in the period at one caused by atmospheric drag, and has:
2. being controlled outside plane
When | | δ i- δ inom| | exceed δ imaxWhen open control.
According to Gauss perturbation equation, out-of-plane control igniting pulsed quantity and moment can be arrived are as follows:
In formula, δ imanFor desired value after igniting, have:
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make a variety of changes or modify within the scope of the claims, this not shadow
Ring substantive content of the invention.In the absence of conflict, the feature in embodiments herein and embodiment can any phase
Mutually combination.
Claims (10)
1. a kind of distributed SAR Formation Configuration Autonomous maintenance control method, which comprises the steps of:
Step 1, the relative motion relation for obtaining configuration establishes the relationship between baseline and configuration；
Step 2, Autonomous maintenance control threshold is obtained；
Step 3, according to control threshold and the deviation being currently configured, configuration is adjusted.
2. distributed SAR Formation Configuration Autonomous maintenance control method according to claim 1, which is characterized in that step 1 packet
It includes:
Step 1.1, the relative motion relation of configuration is obtained；
Step 1.2, the relationship between baseline and configuration is established；
Step 1.3, the relationship between space perturbative force and configuration is obtained；
Step 1.4, path in elevation is obtained to baseline maximum deviation amount and along course made good baseline maximum deviation amount.
3. distributed SAR Formation Configuration Autonomous maintenance control method according to claim 2, which is characterized in that
Step 1.1 includes: that the description vectors δ α of definition configuration meets:
In formula, a is main star semi-major axis of orbit, adFor from star semi-major axis of orbit, e is primary eccentricity, edFor from star eccentricity, i is
Primary orbit inclination angle, M are main star orbital road mean anomaly, and f is main star orbital road true anomaly, and ω is primary argument of perigee, ωdFor
From star argument of perigee, Ω is primary right ascension of ascending node, ΩdFor from star right ascension of ascending node, u is main star orbital latitude argument；udFor
From star orbital latitude argument；ex=ecos ω, ey=esin ω；
δ be formation double star orbit element differences, δ a be from star and primary semi-major axis it is poor,
δ λ is, δ e poor along track from star and primaryxFor double star E vector difference x to component, δ eyThe y of double star E vector difference is to component, δ ixFor
The x of double star I vector difference is to component, δ iyFor double star I vector difference y to component.
4. distributed SAR Formation Configuration Autonomous maintenance control method according to claim 3, which is characterized in that step 1.2
Include:
BECT=| δ rrsinφ+δrncosφ|
In formula, BECTFor vertical virtual base, BATFor along track baseline, φ is radar beam projectional angle, δ rr、δrnAnd δ rtRespectively
Meet:
In formula,For the initial phase in configuration plane, andθ=
arctan(δiy/δix) be configuration plane outside initial phase；
5. distributed SAR Formation Configuration Autonomous maintenance control method according to claim 4, which is characterized in that step 1.3
Include:
Influence of the analysis space perturbative force for configuration, available configuration is by analysis space perturbative force Perturbation Effect are as follows:
In formula:
Atmospheric drag may be expressed as: configuration affect
In formula,Δ B is that two area-to mass ratio of satellite are poor, and ρ is atmospheric density, and v is to defend
Speed, J2 are the humorous constant of earth aspheric, R to star in orbiteFor terrestrial equator radius；N is formation primary angular speed, and u (t) is t
Moment primary latitude argument, u0For initial time primary latitude argument, t is indicated to form into columns from initial time runing time.
6. distributed SAR Formation Configuration Autonomous maintenance control method according to claim 5, which is characterized in that step 1.4
Include:
Path in elevation is obtained to baseline maximum deviation
In formula,For configuration plane internal phase angle divergence, Δ iyFor divergence outside configuration plane；
It obtains along course made good baseline maximum deviation amount
In formula, δ rr2It is perturbation configuration along track long term bias amount, δ rraIt is controlled for semi-major axis inclined for a long time along track caused by residual error
Shifting amount, δ rrFor atmospheric drag long term bias amount.
7. distributed SAR Formation Configuration Autonomous maintenance control method according to claim 6, which is characterized in that step 2 packet
It includes:
Step 2.1, it obtains and maintains control threshold in plane；
Step 2.2, it obtains and maintains control threshold outside plane.
8. distributed SAR Formation Configuration Autonomous maintenance control method according to claim 7, which is characterized in that step 2.1
It include: to be configured maintain the control period in selected plane to be Ti, TiMeet:
It then can be obtained and control Ct value in plane
In formula, Δ B 'ECTxVertical effective divergence caused by be configured radially, k are reserved safety coefficient,To maintain
Control cycle TiIt is configured caused by J2 perturbation along track long term bias amount in time,To maintain to control cycle TiHalf in time
Long axis controls caused by residual error along track long term bias amount,To maintain to control cycle TiAtmospheric drag is inclined for a long time in time
Shifting amount；
Step 2.2 includes: to obtain to maintain control threshold outside plane
In formula, Δ B 'ECTzThe vertical virtual base variable quantity dissipated for amplitude outside plane.
9. distributed SAR Formation Configuration Autonomous maintenance control method according to claim 8, which is characterized in that step 3 packet
It includes:
Step 3.1, control in plane；
Step 3.2, it is controlled outside plane.
10. distributed SAR Formation Configuration Autonomous maintenance control method according to claim 9, which is characterized in that step
3.1 include: the desired value δ e obtained after pulse control twiceman；
δemanMeet:
In formula,For the maximum allowable offset of relative eccentric ratio argument of vector, nom is the nominal data for maintaining control reference；
Step 3.2 includes: to obtain desired value δ i after ignitingman；
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
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| CN114933028B (en) * | 2022-07-21 | 2022-11-11 | 北京航天驭星科技有限公司 | Dual-star-orbit control strategy control method and device, electronic equipment and storage medium |
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