CN105404148B - A kind of solar cell determines the skin satellite attitude control closed loop test system and test method of appearance - Google Patents
A kind of solar cell determines the skin satellite attitude control closed loop test system and test method of appearance Download PDFInfo
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- CN105404148B CN105404148B CN201510844327.1A CN201510844327A CN105404148B CN 105404148 B CN105404148 B CN 105404148B CN 201510844327 A CN201510844327 A CN 201510844327A CN 105404148 B CN105404148 B CN 105404148B
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Abstract
The present invention relates to skin satellite attitude control closed loop test systems and test method that a kind of solar cell determines appearance, including：Dynamics simulation module, angle and electric current conversion module, solar cell simulator, wherein dynamics simulation module, are responsible for that the angle of solar vector incidence satellite solar cell is calculated；Angle and electric current conversion module, the angle for the solar vector incidence satellite solar cell that dynamics simulation module is provided；Solar cell current information is conversed by look-up table；Solar cell simulator simulates several solar cell output currents according to solar cell quantity information and solar cell current information.The present invention has testing cost low, securely and reliably, disclosure satisfy that satellite controls the long-term running requirement of subsystem closed loop test.
Description
Technical field
The present invention relates to a kind of semi-physical simulation closed loop test system and test methods, for skin satellite control test neck
Domain.
Background technology
Skin satellite is limited while of less demanding to accuracy of attitude determination by volume weight, therefore a kind of common appearance method of determining is not
If special sun sensor part, mounts the output current of solar cell piece by satellite surface and carried out to obtain solar vector information
Posture determines.
Traditional closed loop test method is full physical simulation test method.Specifically, it is that satellite is placed on turntable,
Solar cell is irradiated using source of parallel light to carry out closed loop test.This method can largely effect on the service life of solar cell, at
This is higher, cannot meet the satellite control long-term running requirement of subsystem closed loop test.In addition this method is rotated using turntable
Mode, poor reliability is inconvenient to use.
The present invention proposes the skin satellite attitude control closed loop test method that a kind of solar cell determines appearance, belongs to semi-physical simulation and tests
Card method, it is truer than pure mathematics simulation calculation, while the experiment condition of full physical test harshness is not needed, have both high-fidelity
And economy.
Invention content
The technology of the present invention solves the problems, such as：Overcome the deficiencies of the prior art and provide the skin satellite that a kind of solar cell determines appearance
Attitude control closed loop test system and test method have testing cost low, securely and reliably, disclosure satisfy that satellite controls subsystem closed loop
Test long-term running requirement.
The technology of the present invention solution：A kind of solar cell determines the skin satellite attitude control closed loop test system of appearance, including power
Simulation algorithm model, angle and electric current conversion module, solar cell simulator are learned, wherein：
Dynamics simulation module is responsible for that the angle of solar vector incidence satellite solar cell is calculated.It acquires first
Executing agency's information on satellite, calculates by attitude dynamics, calculates present satellites posture information；Then according to where satellite
Track and present satellites posture information obtain the orientation in satellite body coordinate system, i.e. solar vector for the sunPass through
Solar cell obtains solar cell normal line vector in the mount message of satelliteFinally, according to formulaIt calculates
The angle, θ of sunny vector incidence satellite solar cell.Since satellite has several solar cells, so dynamics simulation mould
Block is carried out at the same time the operation of multiple solar cells.It includes solar cell that the module, which can configure different solar cell piece mount messages,
Piece configures quantity, solar cell piece installation site, solar cell piece setting angle.
Angle is with electric current conversion module, the solar vector incidence satellite solar cell that dynamics simulation module is provided
Angle obtain solar cell current information by tabling look-up.Solar cell current information theoretical value IL=IL0× cos θ, θ are the sun
The angle of vector incidence satellite solar cell, IL0For the current value of θ=0 ° solar cell output, IL0For constant.It can be by true
Real Physical Experiment provides reference value.Different incidence angles, which are calculated, by the formula obtains the theoretical value of one group of solar cell electric current,
After actual physical empirical value is modified, by the corresponding solar cell of angle of solar vector incidence satellite solar cell
Current information curve table is formatted storage, is used for tabling look-up.
Angle has selection environment temperature function with electric current conversion module.The module has under varying environment temperature condition
The diagram database of solar vector incidence solar cell angle and solar cell current information.The environment temperature needed according to test
Degree, angle call the curve of the database with electric current conversion module, carry out the table lookup operation of angle and electric current.Pass through one group of difference
Environment temperature under actual physical experiment, obtain and the relevant solar vector incidence satellite solar cell angle of temperature and the sun
One group of curve of battery current information, and curve table is formatted storage, this group of curve tune when needing to carry out temperature information compensation
With.Different environment temperatures can be set when use, program calls the relevant curve of the temperature according to the temperature of setting, carries out angle
Degree converts with electric current.
Solar cell simulator controls solar cell simulator output current according to solar cell current information.Sun electricity
Pond Simulator design has protective current and protection voltage, can avoid accident caused by ground checkout equipment overcurrent or overvoltage.Too
Positive battery simulator has multiple independent output channels, if each and every one channel output current can be selected as needed.
A kind of solar cell determines the skin satellite attitude control closed loop test method of appearance, realizes that steps are as follows：
(1) dynamics simulation module acquires satellite executing mechanism information, carries out attitude dynamics calculating, calculates and defend
Star present satellites posture information, and according to present satellites orbit information and several satellite solar cell mount messages, calculate
The angle of sunny vector incidence satellite solar cell；
(2) angle is conversed the angle of solar vector incidence satellite solar cell by look-up table with electric current conversion module
Solar cell current information；
(3) solar cell simulator simulates several too according to solar cell quantity information and solar cell current information
Positive cell output current.
(4) electric current of satellite power supply subsystem acquisition simulator output, and several pipe computer communications, number pipe computers according to
Size of current calculates solar vector information at this time, and then is carried out according to solar vector determining appearance operation；Number pipe computer is according to calculation
The posture information gone out, according to control targe, control satellite executing mechanism action.
The advantages of the present invention over the prior art are that：
(1) traditional full physical simulation test irradiates true solar cell using source of parallel light, and this method, which shortens, to be defended
The service life of star solar cell, testing cost is higher, and cannot meeting satellite control, subsystem closed loop test is long-term running wants
It asks.Method proposed by the present invention has carried out semi-physical simulation for solar incident angle degree with battery current transforming relationship, not by true
Real solar cell service life limitation, has long-term power of test, reduces testing cost and maintenance cost.
(2) full physical simulation closed loop test method uses the rotatable parts of turntable etc, security reliability poor.The present invention carries
The test system and method gone out does not have the rotatable parts such as turntable, improves reliability and the safety of test；
(3) incident angle and battery current relationship that test method proposed by the present invention is obtained based on full Physical Experiment summarize
It is capable of the relationship of preferable simulated solar Vector Message and solar cell electric current by look-up table at database table, there is high protect
The characteristics of true test.
(4) angle due to the electric current of solar cell output not only with sun incidence has relationship, also solar cell itself
Environment temperature have close relationship, when the higher efficiency of solar cell of temperature is lower.Change environment temperature, just test environment is carried
Very high requirement is gone out, testing cost is too high.Semi-physical simulation test method proposed by the present invention, by being changed in angle and electric current
Calculate the side that module calls solar vector incidence solar cell angle and solar cell current curve database at a temperature of varying environment
Method is preferably simulated the relationship of solar vector and solar cell electric current at a temperature of varying environment, is met under various temperature conditions
Closed loop test, while testing cost is reduced.
(5) emulation dynamics calculation module of the invention can configure different solar cell normal line vectorsIt embodies not
Include solar cell piece quantity, installation site, solar cell piece setting angle with solar cell piece mount message.The present invention can be with
Different solar cell piece installation configurations is emulated, semi-physical simulation foundation is provided for solar cell method for determining posture.
(6) test method proposed by the present invention builds system using widely applied solar cell simulator, is not required to
Custom-made is wanted, has system construction cost low, can be with fast construction the characteristics of.
(7) system that the present invention designs has protective current and protection voltage design for solar cell simulator, can keep away
Exempt from accident caused by ground checkout equipment overcurrent or overvoltage
Description of the drawings
Fig. 1 is each module composition of closed loop test system proposed by the present invention；
Fig. 2 is the workflow of closed loop test method proposed by the present invention.
Specific implementation mode
As shown in Figure 1, test system proposed by the present invention includes dynamics simulation module, angle and electric current conversion mould
Block, solar cell simulator etc..
Dynamics simulation module is responsible for that the angle of solar vector incidence satellite solar cell is calculated.The mould first
Block acquires executing agency's information on satellite, is calculated by attitude dynamics, calculates present satellites posture information；Then basis is defended
Track and present satellites posture information, obtain the orientation in satellite body coordinate system, i.e. solar vector for the sun where star
By solar cell solar cell normal line vector is obtained in the mount message of satelliteFinally, according to formula
Calculate the angle, θ of solar vector incidence satellite solar cell.Since satellite has several solar cells, so dynamics is imitative
True module is carried out at the same time the operation of multiple solar cells.Dynamics simulation module passes through different solar cell normal line vectorsIt includes solar cell piece installation site, solar cell piece setting angle that different solar cell piece mount messages, which can be embodied,.It is dynamic
Mechanics Simulation computing module specific workflow is as follows：
(1) angle, θ of solar vector incidence satellite solar cell can be calculated according to following calculation formula.
In formula (i),For solar cell normal line vector,For orientation of the sun in satellite body coordinate system.
(2) solar cell normal line vectorFor known quantity, the installation according to solar cell on satellite health surface
Information is calculated.
Orientation of the sun in satellite body coordinate systemCalculation formula is
A in formula (ii)bo(q) it is orbital coordinate system to the posture changing matrix of satellite body coordinate system, i.e. the attitude of satellite is believed
Breath.
(3.) sometime the sun is in the orientation of orbital coordinate system
In formula (iii), Sxo,Syo,SzoRespectivelyIn orbital coordinate system (xo,yo,zo) under triaxial coordinate.αo,βo,γo
RespectivelyIn orbital coordinate system (xo,yo,zo) under three axis azimuths.
cosαo、cosβo、cosγoCan according to orbit parameter u, Ω of satellite,ε, i are found out by following relational expression.
Formula (iv) (v) (vi) middle orbit parameter u, Ω,The definition of ε, i is：
U--- satellite arguments, i.e. satellite and angle of the ascending node relative to the earth's core.
Ω --- right ascension of satellite ascending node.
--- sun mean longitude.
The angle of ε --- equatorial plane and ecliptic plan, ε=23.4393 degree.
The angle of i--- satellite orbits plane and the equatorial plane.
Angle is mainly responsible for the solar vector incidence satellite for providing dynamics simulation module with electric current conversion module
The angle of solar cell obtains solar cell current information by tabling look-up.Solar cell current information theoretical value IL=IL0×cos
θ, θ are the angle of solar vector incidence satellite solar cell, IL0For constant value.
IL0=(SC η/VL0)·A (vii)
SC is solar constant in formula (vii), and A is solar cell piece area, and η is transfer efficiency, VL0When for incidence angle being zero
Equivalent photovoltage.By formula as can be seen that the certain solar cell of area, parameter IL0=(SC η/VL0) A is normal
Value can be tested by actual physical and provide reference value.
Different incidence angles are calculated by the formula and obtain the theoretical value of one group of solar cell electric current, by actual physical reality
It tests after numerical value is modified, by the corresponding solar cell current information curve table of the angle of solar vector incidence satellite solar cell
It formats storage, is used for tabling look-up.Angle directly invokes the table with electric current conversion module, according to solar vector incidence satellite sun electricity
The angle in pond tables look-up to obtain corresponding solar cell current value.
Angle has selection environment temperature function with electric current conversion module.By true under a different set of environment temperature
Physical Experiment obtains one group with the relevant solar vector incidence satellite solar cell angle of temperature and solar cell current information
Curve, and curve table is formatted storage, for routine call.The environment temperature that angle is needed with electric current conversion module according to test,
Call the curve data of solar vector the incidence solar cell angle and solar cell current information under varying environment temperature condition
Library carries out the table lookup operation of angle and electric current according to the curve of the database.
Solar cell simulator has several current output channels, can simulate several solar cells.Solar cell
Simulator selects suitable channel output solar cell electric current according to solar cell current information and solar cell quantity.The sun
For battery simulator by setting output current current limit threshold and pressure limiting threshold value, to ensure to broadcast TV programs by satellite, electric current is no more than prescribed limit, protects
Protect product safety on star.
Satellite power supply subsystem acquires the electric current of solar cell simulator output, and current information is passed to satellite number pipe
Computer, by several pipe computers according to the sunny vector incidence solar cell angle of Current calculation of several solar cells, knot
Solar cell mount message and satellite-orbit information are closed, calculates solar vector in the orientation of satellite body coordinate system, and according to
The information that solar vector information and other sensors obtain carries out determining appearance operation.
As shown in Fig. 2, the workflow step of the present invention is as follows：
(1) dynamics simulation module acquires satellite executing mechanism information, carries out attitude dynamics calculating, calculates and defend
Star present satellites posture information, and according to present satellites orbit information and several satellite solar cell mount messages, calculate
The angle of sunny vector incidence satellite solar cell；
(2) angle and electric current convert module by the angle of solar vector incidence satellite solar cell by tabling look-up, obtain too
Positive electricity pond current information；
(3) solar cell simulator simulates several too according to solar cell quantity information and solar cell current information
Positive cell output current；
(4) electric current of satellite power supply subsystem acquisition simulator output, and several pipe computer communications, number pipe computers according to
Size of current calculates solar vector information at this time, and then is carried out according to solar vector determining appearance operation；Number pipe computer is according to calculation
The posture information gone out, according to control targe, control satellite executing mechanism action.
Claims (5)
1. a kind of solar cell determines the skin satellite attitude control closed loop test system of appearance, it is characterised in that including：Dynamics simulation
Module, angle and electric current conversion module, solar cell simulator, wherein：
Dynamics simulation module is responsible for that the angle of solar vector incidence satellite solar cell is calculated；
Angle and electric current conversion module, the angle for the solar vector incidence satellite solar cell that dynamics simulation module is provided
Degree；Utilize IL=IL0× cos θ calculate different incidence angles and obtain the theoretical value of one group of solar cell electric current, by actual physical reality
It tests after numerical value is modified, by the solar cell current information curve corresponding to the angle of solar vector incidence satellite solar cell
Tabular stores, and solar cell current information is conversed by tabling look-up；
Solar cell simulator simulates several solar cells according to solar cell quantity information and solar cell current information
Output current；
Wherein, the dynamics simulation module is embodied as：Executing agency's information on satellite is acquired first, by posture power
It learns and calculates, calculate present satellites posture information；Then it according to track where satellite and present satellites posture information, obtains as too
Orientation of the sun in satellite body coordinate system, i.e. solar vectorMount message by solar cell in satellite obtains the sun
Battery normal line vectorFinally, according to formulaCalculate the angle, θ of solar vector incidence satellite solar cell；
Solar cell includes solar cell piece configuration quantity, solar cell piece installation site, solar cell piece in the mount message of satellite
Setting angle, dynamics simulation module realize the angle calculation of several solar cells simultaneously.
2. solar cell according to claim 1 determines the skin satellite attitude control closed loop test system of appearance, it is characterised in that：Pass through
Different solar cells is inputted in the mount message of satellite, then obtains different solar cell normal line vectorsIt can emulate not
Same solar cell piece installation configuration, semi-physical simulation foundation is provided for solar cell method for determining posture.
3. solar cell according to claim 2 determines the skin satellite attitude control closed loop test system of appearance, it is characterised in that：It is described
Angle is also equipped with selection environment temperature function with electric current conversion module, disclosure satisfy that the testing requirement at a temperature of varying environment；It is logical
The actual physical experiment under a different set of environment temperature is crossed, is obtained and the relevant solar vector incidence satellite solar cell of temperature
One group of curve of angle and solar cell current information, and curve table is formatted storage, this group of curve is needing to believe into trip temperature
It is called when breath compensation, when use sets different environment temperatures, and angle is called with electric current conversion module according to the temperature of setting should
The relevant curve of temperature carries out angle and converts with electric current.
4. solar cell according to claim 1 determines the skin satellite attitude control closed loop test system of appearance, it is characterised in that：It is described
Solar cell simulator has several separate current output channels, selector channel as needed to simulate several solar cells；Together
When solar cell simulator be also devised with protective current and protection voltage, ground checkout equipment overcurrent or overvoltage can be avoided to cause
Accident.
5. a kind of solar cell determines the skin satellite attitude control closed loop test method of appearance, it is characterised in that realize that steps are as follows：
(1) dynamics simulation module acquires satellite executing mechanism information, carries out attitude dynamics calculating, calculates satellite and work as
Preceding satellite posture information, and according to present satellites orbit information and several satellite solar cell mount messages, be calculated too
The angle of positive vector incidence satellite solar cell；
(2) angle converts module by the angle of solar vector incidence satellite solar cell with electric current, utilizes IL=IL0× cos θ meters
It calculates different incidence angles and obtains the theoretical value of one group of solar cell electric current, it, will too after actual physical empirical value is modified
Solar cell current information curve table corresponding to the angle of positive vector incidence satellite solar cell is formatted storage, and look-up table is passed through
Calculate solar cell current information；
(3) solar cell simulator simulates several sun electricity according to solar cell quantity information and solar cell current information
Pond output current；
(4) electric current of satellite power supply subsystem acquisition simulator output, with several pipe computer communications, number pipe computer is according to electric current
Size calculates solar vector information at this time, and then is carried out according to solar vector determining appearance operation；Number pipe computer is according to calculating
Posture information, according to control targe, control satellite executing mechanism action.
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| CN104503421A (en) * | 2014-10-30 | 2015-04-08 | 航天东方红卫星有限公司 | Test system used for satellite power supply and distribution system |
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| "基于太阳矢量的皮卫星姿态角测量误差分析";郁发新等;《吉林大学学报（工学版）》;20080731;第38卷(第4期);正文第1节，第2.5节，图7 * |
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