CN106771704B - A kind of agility satellite power system power supply balanced capacity closed loop test method - Google Patents
A kind of agility satellite power system power supply balanced capacity closed loop test method Download PDFInfo
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- G—PHYSICS
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- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
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- G—PHYSICS
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- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
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Abstract
The present invention relates to a kind of quick satellite power system power supply balanced capacity closed loop test methods, read the attitude of satellite telemetry parameter in ground testing system real-time data base；Attitude of satellite telemetry parameter is substituted into satellite attitude model, current solar incident angle α is calculated；Square matrix controls software and calculates output power output parameter I using power satellite model；Each square matrix of sun square formation simulator configures itself output by output power output parameter I；Satellite reads the battery group current electric quantity in ground testing system real-time data base, judges that power satellite balanced capacity is met the requirements after shadow region originates single pass.Test method of the invention can really reflect power supply capacity of the satellite under current pose, true and reliable test data is provided to the power supply equilibrium analysis of quick satellite whole star, when being accurately inferred to satellite operation on orbit, can power supply system keep power electricity balance between revenue and expenditure.
Description
Technical field
The present invention relates to a kind of quick satellite power system power supply balanced capacity closed loop test methods, belong to satellite test neck
Domain.
Background technique
As user deepens continuously to space picture mode and data volume demand, improves attitude maneuver ability, enriches into
As mission mode has become the new demand of Optical remote satellite over the ground.Quick satellite is much higher than traditional optical remote sensing satellite because of it
A wide range of rapid attitude maneuver ability, it can be achieved that quick and multi-modal imaging to observed object.Traditional optical remote sensing little Wei
Star single track task is simple, and whole star maximum power dissipation and time can be analyzed when power satellite ability is only needed by calculating imaging,
Judge whether that power supply requirement of balance can be met.And mould is imaged because of the features such as mission mode is numerous, attitudes vibration is frequent in quick satellite
Formula is complicated and changeable, and whole star change of power consumption is fast, and the variation because of solar battery array to day angle, causes solar battery array power generation output
The quick variation of power, therefore, the power supply capacity analysis mode of the non-quick moonlet of tradition have been difficult to apply to rapid posture machine
Dynamic imaging satellite needs to establish a kind of quick satellite power system analysis test method.
Summary of the invention
Technology of the invention solves the problems, such as: overcoming the deficiencies of the prior art and provide a kind of quick satellite power system power supply
Balanced capacity closed loop test method can effectively solve the problems, such as quick power satellite capability analysis test at present, carry out satellite
Balanced capacity of powering verifying.
The technical solution of the invention is as follows: a kind of satellite power system power supply balanced capacity closed loop test method is provided,
Steps are as follows:
(1) attitude of satellite telemetry parameter in ground testing system real-time data base is read；
(2) attitude of satellite telemetry parameter is substituted into satellite attitude model, calculates current solar incident angle α；
(3) square matrix control software interface module is sent by current solar incident angle α, square matrix controls software and utilizes satellite
Output power output parameter I is calculated for electric model；
(4) output power output parameter I is sent to each square matrix of sun square formation simulator, sun square formation simulator
Each square matrix configures itself output by output power output parameter I；
(5) satellite reads the storage in ground testing system real-time data base after shadow region originates single pass
Battery pack current electric quantity, judges whether present battery is full of, and indicates that power satellite balanced capacity is met the requirements if being full of, such as
Fruit battery is not full of, and shows that power satellite balanced capacity is unsatisfactory for requiring.
Preferably, satellite attitude model is as follows:Wherein SB,x、SB,y、
SB,zRespectively x-axis, y-axis, z-axis coordinate of the solar direction vector S in satellite body coordinate system.
Preferably, power satellite model is as follows:
I=PEOL/ V,
PEOL=S ' × η × FAL×FT×FRAD×FUV×F×A
Wherein PEOLThe output power of solar battery array when for lifetime of satellite latter stage；V is the current bussed supply voltage of satellite；
S ' is effective sunlight global radiation illumination；η is solar cell monolithic photonic transfer efficiency；FALFor solar battery array assembling loss because
Son；FTIt is solar battery array temperature correction factor；FRADFor solar battery array particle irradiation decay factor；FUVFor solar battery array
Ultraviolet irradiation decay factor；F is other decay factors of solar battery array；A is the effective area of solar battery array.
Preferably, step (4) further includes acquiring the reality of sun square formation simulator in real time during satellite orbiting
Border output parameter.
Preferably, as | I-I ' | when≤3%I, determine that sun square formation simulator output is normal；When | I-I ' | when > 3%I,
It is abnormal to determine that sun square formation simulator output exists.
Compared with the prior art, the present invention has the following advantages:
(1) existing satellite power system capability analysis method is the satellite based on the non-quick operating mode of tradition, because defending
Star operating mode demand, the analysis method is more succinct, can not be suitable for the quick satellite of complex task mode.The present invention mentions
Quick satellite power system closed loop test method out, when sufficiently combining quick attitude maneuver solar battery array output energy and
The variation of whole star power demand during complicated imaging pattern establishes the quick attitude of satellite and power supply system model, passes through acquisition
Telemetry parameter, calculate in real time and control each sun square formation simulator point battle array for electricity output, can really reflect satellite current
Power supply capacity under posture.
(2) because of the rapid attitude maneuver of quick satellite and complicated imaging pattern the features such as, it is difficult in-orbit for electric equilibrium to its
Ability is analyzed.Using power supply system closed loop test method of the invention, can be tested in quick Satellite Simulation flight test
Cheng Zhong is calculated and is adjusted in real time according to power supply output parameter of the present satellites posture to sun square formation simulator system, is imitated
True single track or more rail power satellite changed powers provide true and reliable test number to the power supply equilibrium analysis of quick satellite whole star
According to when being accurately inferred to satellite operation on orbit, can power supply system keep power electricity balance between revenue and expenditure.
(3) method of the invention is used, can flexibly be established by modifying satellite configuration parameter based on different quick satellites
Posture and for electric model, suitable for the power supply system test process of different satellites, emulates quick power satellite ability
Analysis and test verifying.Meanwhile this method is also applied for the satellite of non-quick attitude maneuver operating mode, it can be relatively previous more true
It is real that capability analysis accurately is powered to it.
(4) present invention is realized by software programming, can be by operation satellite single track or more rail imaging task modes, intuitively
Easily analysis power satellite balanced capacity, judges whether present satellites power supply system can satisfy its operation on orbit demand, greatly
It improves work efficiency greatly.
Detailed description of the invention
Fig. 1 is quick satellite ground test system configurations schematic diagram；
Fig. 2 is quick satellite attitude model schematic diagram of the invention；
Fig. 3 is the angle schematic diagram of solar direction vector and solar battery array normal of the invention；
Fig. 4 is power supply system closed loop test functional module structure figure of the invention.
Specific embodiment
It is as shown in Figure 1 quick satellite ground test system configurations schematic diagram, quick satellite ground test macro includes distant
Survey remote control front end, console, ground testing system real-time data base, sun square formation simulator；
Remote measuring and controlling front end receiver satellite is simultaneously sent to console, and console is sent to ground test after carrying out real-time resolving
System real-time database stores telemetry parameter；The testing control module of sun square formation simulator reads ground testing system and counts in real time
According to the attitude of satellite telemetry parameter in library, attitude of satellite telemetry parameter is substituted into satellite attitude model, the current sun is calculated
Incident angle α；Square matrix control software interface module is sent by current solar incident angle α, square matrix is controlled software and supplied using satellite
Electric model calculates output power output parameter I；Output power output parameter I is sent to each side of sun square formation simulator
Each square matrix of battle array, sun square formation simulator configures itself output by output power output parameter I；Acquisition sun square matrix mould in real time
The reality output parameter I ' of quasi- device；Satellite is artificial to read ground testing system reality after shadow region originates single pass
When database in battery group current electric quantity, judge whether present battery is full of, if be full of if indicate power satellite balance
Ability is met the requirements, if battery is not full of, shows that power satellite balanced capacity is unsatisfactory for requiring.
Quick satellite attitude model working principle is as shown in Figure 2.When measurement can be calculated from sun ephemeris data
Longitude of the sun on ecliptic is carved, it is possible thereby to determine coordinate S of the solar direction vector S in the inertial coodinate system of the earth's core equatorI。
If with right ascension αSWith declination δSForm provide, then have
The orbit parameter of given measurement moment satellite: right ascension of ascending node Ω, inclination angle i, argument of perigee ω, true anomaly f,
So orbital coordinate system can be write with respect to the transition matrix of the earth's core equator inertial coodinate system
In formula, u is satellite argument, there is u=ω+f.
Coordinate S of the solar direction vector S in orbital coordinate system in this wayOIt can write
SO=COISI (3)
Satellite body coordinate system can be turned relative to the attitude matrix of orbital coordinate system by the Euler around satellite body reference axis
It is dynamic to provide.Under normal circumstances, the corresponding Eulerian angles of attitude matrix are related with the order of rotation.For the sake of difference, when rotation time
Sequence is ZB→XB→YBWhen, corresponding Eulerian angles are denoted as ψ,θ, then attitude matrix can write CBO,(Z-X-Y)
In formula,For roll angle, θ is pitch angle, and ψ is yaw angle.
Coordinate S of the solar direction vector S in satellite body coordinate system can be obtained in convolution (3) and (4)B
SB=CBOSO=[SB,x SB,y SB,z]T (5)
Assume that solar battery array is fixed on satellite body and is parallel to satellite body coordinate system X hereinB-YBPlane, then can be by
Solar incident angle α, the i.e. angle of solar direction vector and solar battery array normal is calculated in formula (5), as shown in Figure 3.
Then the calculation formula of solar incident angle α is
In attitude mode establishment process, coordinate system conversion calculation, solar battery array need to be solidified relative to satellite
The information such as coordinate are brought attitude mode into and are calculated when receiving attitude parameter telemetering, solve sunlight relative to sun electricity
The incidence angle of Chi Zhen.
Quick power satellite model is then the ginsengs such as area, the photoelectric conversion efficiency of the current quick Satellite vapour image of configuration
Number, determines the calculation of solar battery array output power.It is usually main to consider the lifetime of satellite when satellite power supply subsystem designs
The output power P of solar battery array when latter stageEOL, PEOLCalculation it is as follows:
PEOL=S ' × η × FAL×FT×FRAD×FUV×F×A (7)
Wherein,
S ' is effective sunlight global radiation illumination；η is solar cell monolithic photonic transfer efficiency；FALFor solar battery array group
Loss factor is closed, generally takes 0.97~0.99；FTIt is solar battery array temperature correction factor；FRADFor solar battery array particle spoke
According to decay factor；FUVFor solar battery array ultraviolet irradiation decay factor；F is other decay factors of solar battery array, is generally taken
0.99~1.00；A is the effective area of solar battery array.
It can be seen that in formula (7), η, FALEtc. parameters be different type solar battery array intrinsic parameter, can be by specific ginseng
Number is configured, and influences output power PEOLVariable element it is main there are two, i.e., effective sunlight global radiation illumination S ' and the sun
The effective area A of cell array, calculation are shown in formula (8), (9) respectively:
S '=S0×cosα×X×XS×Xe (8)
A=A0×FS×Fj (9)
In formula (8), S0For solar constant, 1353W/m2；α is the angle of sunlight and solar battery array normal direction, i.e., too
Positive incidence angle；X is that modifying factor when sunlight casts oblique rays on solar battery array works as solar incident angle generally between 0.95~1.0
1.0 are taken when less than 50 °；XSFor the sun light intensity seasonal variety factor, spring and autumn timesharing takes 1.0, and the Summer Solstice takes 0.9673, and Winter Solstice takes
1.0327；XeIt is earth reflection light to the gain factor of solar battery array output power.
In formula (9), A0For the gross area of solar battery array, m2；FSIt is geometrical factor, i.e., solar battery array is perpendicular to too
The ratio between projected area and the solar battery array gross area on sunlight direction, flat solar battery array generally takes 1, answers if blocking
It is appropriate to reduce；FjFor solar battery array pieces of cloth coefficient, i.e. the ratio between the solar cell piece gross area and the solar battery array gross area, generally
Take 0.85~0.95.
In formula (8), (9), S0、X、A0Etc. parameters be intrinsic parameter or different Satellite vapour image design parameter, can press
According to satellite actual design situation approximation value.Pass through analysis mode (7), (8), (9), it can be deduced that, it is main to change output power PEOL
Design parameter be α, i.e., the solar incident angle α solved by attitude mode before.By the parameter substitution formula (7), in conjunction with defending
Power supply buses the voltage V, available current solar battery array supply current I of star.
I=PEOL/V (10)
Power supply capacity analytic function, need to by acquiring satellite telemetry parameters in real time, according to the quick attitude of satellite established and
For electric model, calculate and control each battle array sun square formation simulator for electricity output, can more actually, quickly react satellite and work as
Power supply capacity under preceding posture.
Power supply equilibrium analysis function emulates satellite by this method in quick Satellite Simulation flight test test process
The variation of in-orbit solar battery array supply current, can it is intuitive by satellite power supply controller working condition, easily to power satellite
Balance is analyzed and determined, true and reliable test data is provided.
Export result comparison function.In this method course of work, sun square formation simulator can be exported during the test
Power parameter is saved to local file.By emulating to the attitude of satellite, solar battery array incidence is calculated to obtain according to attitude data
The theoretical value of angle, further theory of solving power output parameter I are compared with reality output parameter I ' in test process,
Judge whether current closed loop test mode setting is correct, whether the attitude of satellite and power supply model foundation are reasonable.It is real in quick satellite
In the testing engineering of border, when | I-I ' | when≤3%I, determine that sun square formation simulator output is normal；When | I-I ' | when > 3%I, too
There is exception in positive square matrix simulator output, sun square formation simulator configuration parameter need to be corrected, again to power satellite ability and confession
Electric equilibrium carries out closed loop test.
As shown in figure 4, power supply system closed loop test functional module of the invention mainly includes Telemetry Data Acquisition module, too
Solar angle computing module, sun square formation simulator system controlling software input interface module, power supply parameter computing module and
Power supply output control module etc..
Wherein, Telemetry Data Acquisition module is used to acquire the telemetry of real-time data base broadcast, when therefrom choosing UTC
Between, right ascension of ascending node, inclination angle, argument of perigee, the information needed such as true anomaly.Angle of incidence of sunlight computing module, being used for will
Telemetry needed for collected, substitutes into established attitude mode, by modes such as transformed coordinate systems, resolves the current sun
Light is to the incidence angle of solar battery array and sends it to corresponding ports.Sun square formation simulator system controlling software input interface
Module is mainly used for realizing the angle of incidence of sunlight parameter for receiving and acquiring and having resolved.Power supply parameter computing module will receive
The angle of incidence of sunlight parameter arrived, substitute into foundation in electric model, according to solar battery array area, the photoelectricity pre-set
The configuration parameters such as transfer efficiency calculate the corresponding solar battery array general power supply current of current incidence angle, according to the sun electricity of satellite
Pond battle array number, calculate each sun square formation simulator point battle array specific output current parameters, send it to for electricity output control
Module, and it is stored in local report file, for subsequent query reference and comparing.Power supply output module, calculates receiving
When obtained each sun square formation simulator power supply parameter, each point of battle array receiving port, each point of battle array are sent it to by gpib bus
Power output is adjusted in real time according to the parameter received.
When quick satellite power system starts test, need to configure to the posture of present satellites and for electric model first,
Confirm that parameter setting is errorless, can be used for power supply system closed loop test.For the ease of the beginning and end of control test, setting pause
Control mark terminates closed loop test process when needing to suspend；If entering next step without pause demand.Needed for acquisition
Attitude of satellite telemetry parameter calculates angle of incidence of sunlight, i.e. sunlight and solar cell according to configured satellite attitude model
The angle of tactical deployment of troops line.Angle of incidence of sunlight α is sent to the corresponding interface of sun square formation simulator system controlling software, judgement is
No correct transmission enters next step if successfully transmitting；If transmission is unsuccessful, maintain each battle array currently to export constant, guarantees
Satellite is able to normal power supply, and misregistration information simultaneously enters the work of acquisition calculating next time.The control of sun square formation simulator system
Software brings the angle of incidence of sunlight parameter received into according to established for electric model, resolves each sun square formation simulator point
The power supply output parameter of battle array.Each battle array power supply parameter is sent to corresponding interface, according to collected simulator power output parameter,
Judge whether successfully to adjust each battle array for electricity output, if successfully adjusting, enters calculating process next time；If adjustment is unsuccessful,
Each battle array is maintained currently to export constant, misregistration information simultaneously enters the work of acquisition calculating next time.After test, ground is read
Battery group current electric quantity parameter in test macro real-time data base is powered balanced capacity analysis.
Claims (5)
- The balanced capacity closed loop test method 1. a kind of satellite power system is powered, it is characterised in that steps are as follows:(1) attitude of satellite telemetry parameter in ground testing system real-time data base is read；(2) attitude of satellite telemetry parameter is substituted into satellite attitude model, calculates current solar incident angle α；(3) square matrix control software interface module is sent by current solar incident angle α, square matrix controls software and utilizes power satellite Model calculates output power output parameter I；(4) output power output parameter I is sent to each square matrix of sun square formation simulator, sun square formation simulator it is each Square matrix configures itself output by output power output parameter I；(5) satellite reads the battery in ground testing system real-time data base after shadow region originates single pass Group current electric quantity, judges whether present battery is full of, and indicates that power satellite balanced capacity is met the requirements if being full of, if electric Pond is not full of, and shows that power satellite balanced capacity is unsatisfactory for requiring.
- The balanced capacity closed loop test method 2. satellite power system as described in claim 1 is powered, which is characterized in that Satellite Attitude States model is as follows:Wherein SB,x、SB,y、SB,zRespectively solar direction vector S X-axis, y-axis, z-axis coordinate in satellite body coordinate system.
- The balanced capacity closed loop test method 3. satellite power system as claimed in claim 1 or 2 is powered, which is characterized in that defend Star is as follows for electric model:I=PEOL/ V,PEOL=S ' × η × FAL×FT×FRAD×FUV×F×AWherein PEOLThe output power of solar battery array when for lifetime of satellite latter stage；V is the current bussed supply voltage of satellite；S ' is Effective sunlight global radiation illumination；η is solar cell monolithic photonic transfer efficiency；FALFor the solar battery array assembling loss factor； FTIt is solar battery array temperature correction factor；FRADFor solar battery array particle irradiation decay factor；FUVIt is ultraviolet for solar battery array Irradiate decay factor；F is other decay factors of solar battery array；A is the effective area of solar battery array.
- The balanced capacity closed loop test method 4. satellite power system as described in claim 1 is powered, step (4) further includes defending During star orbiting, the reality output parameter I ' of sun square formation simulator is acquired in real time.
- The balanced capacity closed loop test method 5. satellite power system as claimed in claim 4 is powered, further includes step (6), when | I-I ' | when≤3%I, determine that sun square formation simulator output is normal；When | I-I ' | when > 3%I, determine that sun square formation simulator is defeated Exist out abnormal.
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| CN109756103B (en) * | 2018-12-27 | 2020-09-18 | 中国空间技术研究院 | Power supply and distribution control system and control method for space flight verification platform |
| CN110991008B (en) * | 2019-11-08 | 2023-08-22 | 上海卫星工程研究所 | High-fidelity reconfigurable satellite energy supply test equipment design system |
| CN113949117A (en) * | 2021-08-26 | 2022-01-18 | 中国空间技术研究院 | Remote sensing satellite storage battery autonomous undervoltage protection method |
| CN114417494A (en) * | 2021-12-08 | 2022-04-29 | 北京航空航天大学 | Energy balance analysis method of small satellite power supply system |
| CN117498516A (en) * | 2023-10-10 | 2024-02-02 | 湖南大学 | Satellite power supply system energy balance calculation method based on digital twin simulation |
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| CN101950002A (en) * | 2010-08-13 | 2011-01-19 | 航天东方红卫星有限公司 | Comprehensive test method of small satellite power subsystem |
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