CN106771704A - A kind of quick satellite power system is powered balanced capacity closed loop test method - Google Patents
A kind of quick satellite power system is powered 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
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
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Abstract
Powered balanced capacity closed loop test method the present invention relates to a kind of quick satellite power system, read the attitude of satellite telemetry parameter in ground testing system real-time data base；By in attitude of satellite telemetry parameter substitution satellite attitude model, current solar incident angle α is calculated；Square formation control software calculates output power output parameter I using power satellite model；Each square formation of sun square formation simulator configures itself and exports by output power output parameter I；After satellite is through shadow region starting single pass, the batteries current electric quantity in ground testing system real-time data base is read, judge that power satellite balanced capacity meets and require.Method of testing of the invention can really reflect power supply capacity of the satellite under current pose, equilibrium analysis of being powered to the whole star of quick satellite provides true and reliable test data, when being accurately inferred to satellite operation on orbit, can electric power system keep power electricity balance between revenue and expenditure.
Description
Technical field
Powered balanced capacity closed loop test method the present invention relates to a kind of quick satellite power system, belong to satellite test neck
Domain.
Background technology
As user deepens continuously to space picture pattern and data volume demand, improve attitude maneuver ability, enrich into
The new demand of Optical remote satellite over the ground is had become as mission mode.Quick satellite is far above traditional optical remote sensing satellite because of it
Rapid attitude maneuver ability on a large scale, be capable of achieving to the quick and multi-modal imaging of observed object.Traditional optical remote sensing little Wei
Star single track task is simple, power satellite ability only need by be calculated as when whole star maximum power dissipation and be analyzed by the time,
Judge whether that power supply requirement of balance can be met.And quick satellite is because the features such as mission mode is numerous, attitudes vibration is frequent, being imaged mould
Formula is complicated and changeable, and whole star change of power consumption is fast, and the change because of solar battery array to day angle, causes solar battery array to generate electricity and exports
The quick change of power, therefore, the power supply capacity analysis mode of the non-quick moonlet of tradition has been difficult to apply to rapid posture machine
Dynamic imaging satellite is, it is necessary to set up a kind of quick satellite power system analysis test method.
The content of the invention
Technology solve problem of the invention：Overcome the deficiencies in the prior art, there is provided a kind of quick satellite power system is powered
Balanced capacity closed loop test method, can effectively solve the problems, such as agility power satellite capability analysis test at present, carry out satellite
Power supply balanced capacity checking.
Technical solution of the invention is：A kind of satellite power system is provided to power balanced capacity closed loop test method,
Step is as follows：
(1) attitude of satellite telemetry parameter in ground testing system real-time data base is read；
(2) by attitude of satellite telemetry parameter substitution satellite attitude model, current solar incident angle α is calculated；
(3) current solar incident angle α is sent to square formation control software interface module, square formation control software utilizes satellite
Power supply model calculates output power output parameter I；
(4) output power output parameter I is sent to each square formation of sun square formation simulator, sun square formation simulator
Each square formation configures itself and exports by output power output parameter I；
(5) after satellite is through shadow region starting single pass, the storage in ground testing system real-time data base is read
Battery pack current electric quantity, judges whether present battery is full of, and is required if filled with then representing that power satellite balanced capacity meets, 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 during for lifetime of satellite latter stage；V is the current bussed supply voltage of satellite；
S ' is effective sunshine global radiation illumination；η is solar cell monolithic photonic conversion efficiency；FALFor solar battery array assembling loss because
Son；FTIt is solar battery array temperature correction factor；FRADIt is solar battery array particle irradiation decay factor；FUVIt is 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) is additionally included in during satellite orbiting, the reality of Real-time Collection sun square formation simulator
Border output parameter.
Preferably, as | I-I ' |≤3%I, judge that sun square formation simulator output is normal；As | I-I ' | ＞ 3%I,
Judge that sun square formation simulator output is present abnormal.
The present invention has advantages below compared with prior art：
(1) existing satellite power system capability analysis method, is the satellite based on the non-quick mode of operation of tradition, because defending
Star mode of operation demand, the analysis method is more succinct, can not be applied to the quick satellite of complex task pattern.The present invention is carried
The quick satellite power system closed loop test method for going out, when fully combining quick attitude maneuver solar battery array output energy and
The change of whole star power demand during complicated imaging pattern, sets up the quick attitude of satellite and electric power system model, by collection
Telemetry parameter, calculates and controls the power supply of each sun square formation simulator point battle array to export in real time, can really reflect satellite current
Power supply capacity under attitude.
(2) because of the rapid attitude maneuver and complicated imaging pattern of quick satellite the features such as, it is difficult to its in-orbit power supply balance
Ability is analyzed.Using electric power 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 present satellites attitude to the power supply output parameter of sun square formation simulator system, is imitated
True single track or many rail power satellite changed powers, equilibrium analysis of being powered to the whole star of quick satellite provide true and reliable test number
According to when being accurately inferred to satellite operation on orbit, can electric power system keep power electricity balance between revenue and expenditure.
(3) method of the present invention is used, can be flexibly set up based on different quick satellites by changing satellite configuration parameter
Attitude and power supply model, it is adaptable in the electric power system test process of different satellites, emulated to quick power satellite ability
Analysis and test is verified.Meanwhile, this method is also applied for the satellite of non-quick attitude maneuver mode of operation, can be relatively in the past trueer
It is real that capability analysis accurately are powered to it.
(4) present invention, can be by running satellite single track or many rail imaging task patterns, intuitively by software programming realization
Power satellite balanced capacity is easily analyzed, judges whether present satellites electric power system can meet its operation on orbit demand, greatly
Improve operating efficiency greatly.
Brief description of the drawings
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 of the invention and solar battery array normal；
Fig. 4 is electric power 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 system 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 storehouse, by attitude of satellite telemetry parameter substitution satellite attitude model, the current sun is calculated
Incident angle α；Current solar incident angle α is sent to square formation control software interface module, square formation control software is 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
Battle array, each square formation of sun square formation simulator configures itself and exports by output power output parameter I；Real-time Collection sun square formation mould
Intend the reality output parameter I ' of device；It is artificial to read ground testing system reality after satellite is through shadow region starting single pass
When database in batteries current electric quantity, judge whether present battery is full of, if filled with then represent power satellite balance
Ability meets requirement, if battery is not full of, shows that power satellite balanced capacity is unsatisfactory for requiring.
Quick satellite attitude model operation principle is as shown in Figure 2.When can be calculated measurement 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 be given, 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.
So coordinate S of the solar direction vector S in orbital coordinate systemOCan 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 be given.In general, the corresponding Eulerian angles of attitude matrix are relevant with the order for rotating.It is secondary when rotating for the sake of for difference
Sequence is ZB→XB→YBWhen, corresponding Eulerian angles are designated as ψ,θ, then attitude matrix can write CBO,(Z-X-Y)
In formula,It is roll angle, θ is the angle of pitch, and ψ is yaw angle.
Convolution (3) and (4) are the coordinate S that can obtain solar direction vector S in satellite body coordinate systemB
SB=CBOSO=[SB,x SB,y SB,z]T (5)
Assume that solar battery array is fixed on satellite body and parallel to satellite body coordinate system X hereinB-YBPlane, then can be by
Formula (5) is calculated the angle of solar incident angle α, i.e. solar direction vector and solar battery array normal, as shown in Figure 3.
Then the computing formula of solar incident angle α is
During attitude mode foundation, coordinate system conversion calculation, solar battery array need to be solidified relative to satellite
The information such as coordinate, when attitude parameter remote measurement is received, bring attitude mode into and are calculated, and solve sunshine relative to sun electricity
The incidence angle of Chi Zhen.
Quick power satellite model is then the ginsengs such as area, the photoelectric transformation efficiency of the current agility Satellite vapour image of configuration
Number, determines the calculation of solar battery array power output.It is generally main to consider the lifetime of satellite when satellite power supply subsystem is designed
The output power P of solar battery array during latter stageEOL, PEOLCalculation it is as follows：
PEOL=S ' × η × FAL×FT×FRAD×FUV×F×A (7)
Wherein,
S ' is effective sunshine global radiation illumination；η is solar cell monolithic photonic conversion efficiency；FALIt is solar battery array group
Loss factor is closed, 0.97~0.99 is typically taken；FTIt is solar battery array temperature correction factor；FRADIt is solar battery array particle spoke
According to decay factor；FUVIt is solar battery array ultraviolet irradiation decay factor；F is other decay factors of solar battery array, is typically taken
0.99~1.00；A is the effective area of solar battery array.
It can be seen that in formula (7), η, FALEtc. the intrinsic parameter that parameter is different type solar battery array, can be by specific ginseng
Number is configured, influence output power PEOLVariable element mainly have two, i.e., effective sunshine global radiation illumination S ' and the sun
The effective area A of cell array, calculation is shown in formula (8), (9) respectively：
S '=S0×cosα×X×XS×Xe (8)
A=A0×FS×Fj (9)
In formula (8), S0It is solar constant, 1353W/m2；α is the angle of sunshine and solar battery array normal direction, i.e., too
Positive incidence angle；Modifying factor when X is sunshine setting sun solar battery array, typically between 0.95~1.0, works as solar incident angle
1.0 are taken during less than 50 °；XSIt is 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 power output.
In formula (9), A0It is 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 typically takes 1, if block should
It is appropriate to reduce；FjThe ratio between be solar battery array pieces of cloth coefficient, i.e. the solar cell piece gross area with solar battery array gross area, typically
Take 0.85~0.95.
In formula (8), (9), S0、X、A0Etc. the design parameter that parameter is intrinsic parameter or different Satellite vapour images, can press
According to the satellite approximate value of actual design situation.By 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 that obtains is solved by attitude mode before.By the parameter substitution formula (7), with reference to defending
The power supply buses voltage V of star, can obtain current solar battery array supply current I.
I=PEOL/V (10)
Power supply capacity analytic function, need to by Real-time Collection satellite telemetry parameters, according to set up the quick attitude of satellite and
Power supply model, calculates and controls the power supply of each battle array sun square formation simulator to export, and can relatively real, quickly react satellite and work as
Power supply capacity under preceding attitude.
Power supply equilibrium analysis function, in quick Satellite Simulation flight test test process, satellite is emulated by this method
The change of in-orbit solar battery array supply current, can it is directly perceived by satellite power supply controller working condition, easily to power satellite
Balance is analyzed judgement, there is provided true and reliable test data.
Output result comparison function.In this method course of work, sun square formation simulator can be exported in test process
Power parameter is preserved to local file.Emulated by 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 compares with reality output parameter I ' in test process,
Judge that whether correct current closed loop test pattern sets, whether reasonable the attitude of satellite and power supply model set up.In quick satellite reality
In the testing engineering of border, as | I-I ' |≤3%I, judge that sun square formation simulator output is normal；As | I-I ' | ＞ 3%I, too
There is exception in positive square formation 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, electric power 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 gather 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, for inciting somebody to action
The required telemetry for collecting, in the attitude mode that substitution has been set up, 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 in realizing receiving the angle of incidence of sunlight parameter that collection has been resolved.Power supply parameter computing module, will receive
The angle of incidence of sunlight parameter for arriving, in the power supply model that substitution is set up, according to the solar battery array area, the photoelectricity that pre-set
The configuration parameters such as conversion 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, calculates the specific output current parameter of each sun square formation simulator point battle array, sends it to power supply output control
Module, and local report file is stored in, for subsequent query reference and comparing.Power supply output module, is receiving calculating
During each sun square formation simulator power supply parameter for obtaining, each point of battle array receiving port, each point of battle array are sent it to by gpib bus
According to the parameter real-time adjustment power output for receiving.
When quick satellite power system starts test, need to configure the attitude and power supply model of present satellites first,
Confirm that parameter setting is errorless, can be used for electric power system closed loop test.For the ease of the beginning and end of control test, pause is set
Control mark, when pause is needed, terminates closed loop test process；If without pause demand, into next step.Needed for collection
Attitude of satellite telemetry parameter, according to the satellite attitude model for having configured, calculates angle of incidence of sunlight, i.e. sunshine and solar cell
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, if successfully transmitting, is put into next step；If transmission is unsuccessful, each battle array is maintained currently to export constant, it is ensured that
Satellite is able to normal power supply, and misregistration information simultaneously enters and gathers evaluation work next time.Sun square formation simulator system is controlled
Software, according to the power supply model for establishing, brings the angle of incidence of sunlight parameter for receiving into, 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, is powered output parameter according to the simulator for collecting,
Judge whether successfully to adjust each battle array to power output, if successfully adjusting, into calculating process next time；If adjustment is unsuccessful,
Maintain each battle array currently to export constant, misregistration information and enter gather evaluation work next time.After test terminates, ground is read
Batteries current electric quantity parameter in test system real-time data base, is powered balanced capacity analysis.
Claims (5)
1. a kind of satellite power system is powered balanced capacity closed loop test method, it is characterised in that step is as follows：
(1) attitude of satellite telemetry parameter in ground testing system real-time data base is read；
(2) by attitude of satellite telemetry parameter substitution satellite attitude model, current solar incident angle α is calculated；
(3) current solar incident angle α is sent to square formation control software interface module, square formation control software utilizes power satellite
Model calculates output power output parameter I；
(4) output power output parameter I is sent to each square formation of sun square formation simulator, sun square formation simulator each
Square formation configures itself and exports by output power output parameter I；
(5) after satellite is through shadow region starting single pass, the battery in ground testing system real-time data base is read
Group current electric quantity, judges whether present battery is full of, and is required if filled with then representing that power satellite balanced capacity meets, if electric
Pond is not full of, and shows that power satellite balanced capacity is unsatisfactory for requiring.
2. satellite power system as claimed in claim 1 is powered balanced capacity closed loop test method, it is characterised 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.
3. satellite power system as claimed in claim 1 is powered balanced capacity closed loop test method, it is characterised in that satellite is supplied
Electric model is as follows：
I=PEOL/ V,
PEOL=S ' × η × FAL×FT×FRAD×FUV×F×A
Wherein PEOLThe output power of solar battery array during for lifetime of satellite latter stage；V is the current bussed supply voltage of satellite；S ' is
Effective sunshine global radiation illumination；η is solar cell monolithic photonic conversion efficiency；FALIt is the solar battery array assembling loss factor；
FTIt is solar battery array temperature correction factor；FRADIt is solar battery array particle irradiation decay factor；FUVFor solar battery array is ultraviolet
Irradiation decay factor；F is other decay factors of solar battery array；A is the effective area of solar battery array.
4. satellite power system as claimed in claim 1 is powered balanced capacity closed loop test method, and step (4) is additionally included in be defended
During star orbiting, the reality output parameter of Real-time Collection sun square formation simulator.
5. satellite power system as claimed in claim 4 is powered balanced capacity closed loop test method, also including step (6), when |
I-I ' | during≤3%I, judge that sun square formation simulator output is normal；As | I-I ' | ＞ 3%I, sun square formation simulator is judged
Output exists abnormal.
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| 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 |
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| 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 |
| CN114417494B (en) * | 2021-12-08 | 2024-06-25 | 北京航空航天大学 | Energy balance analysis method of small satellite power supply system |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109756103A (en) * | 2018-12-27 | 2019-05-14 | 中国空间技术研究院 | A kind of power distribution and supply control system and control method for space flight verification platform |
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| 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 |
| CN114417494B (en) * | 2021-12-08 | 2024-06-25 | 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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|---|---|
| CN106771704B (en) | 2019-04-30 |
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