CN108460218A - A kind of optical imagery class moonlet Power budgets and Energy Sources Equilibrium analysis method - Google Patents
A kind of optical imagery class moonlet Power budgets and Energy Sources Equilibrium analysis method Download PDFInfo
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- CN108460218A CN108460218A CN201810213514.3A CN201810213514A CN108460218A CN 108460218 A CN108460218 A CN 108460218A CN 201810213514 A CN201810213514 A CN 201810213514A CN 108460218 A CN108460218 A CN 108460218A
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- Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
A kind of optical imagery class moonlet Power budgets of present invention offer and Energy Sources Equilibrium analysis method first combine user's requirement, the self-defined satellite power consumption number calculated under single operating mode；Then, satellite single track total energy consumption is calculated according to single-rail working state reasonable consideration power consumption number according to satellite operation pattern；According to the type selecting and design capacity of different cell arrays, then it calculates the solar battery array design area after the solar battery array parameter for meeting Energy Sources Equilibrium requirement, including solar battery array single track least energy, solar battery array minimum power, solar battery array minimum effective area, solar battery array minimal design area, consideration allowance, the effective solar array area after consideration allowance, the solar battery array power after consideration allowance, consider solar battery array single track energy after allowance；Finally, the energy requirement of lithium battery group is calculated, and carries out battery type selecting.The actual use pattern of this method combination satellite reasonably completes whole energy source of star satisfaction degree analysis.
Description
Technical field
The present invention relates to Spacecraft guidance and control fields, particularly, are related to a kind of optical imagery class moonlet Power budgets and energy
Source Equilibrium Analysis Method.
Background technology
The Power budgets of satellite are a very important rings in satellite master-plan with Energy Sources Equilibrium analysis, it, which is determined, defends
Can the design of energy source of star system meet requirement.Power budgets are related to power demand, the satellite of satellite with Energy Sources Equilibrium analysis
The mission planning etc. of orbit parameter (illumination condition), the operating mode of satellite and payload.In the satellite master-plan stage, root
According to different satellite task mission, function and requirement, there is also many not to know with Energy Sources Equilibrium analysis for Power budgets
Property, therefore be difficult the Power budgets and Energy Sources Equilibrium analysis method for the satellite for providing a standard, therefore this respect is open literary
It offers seldom.
Invention content
For the technical characterstic of optical imagery class moonlet, in conjunction with practical engineering experience, the present invention provide a kind of optics at
As class moonlet Power budgets and Energy Sources Equilibrium analysis method, the master-plan rank of optical imagery class moonlet can be directly used for
Section, for satellite engineering, designer provides reference.
To achieve the above object, the present invention uses following technical scheme：
A kind of optical imagery class moonlet Power budgets and Energy Sources Equilibrium analysis method, include the following steps：
The first step, satellite Power budgets；
Given optical imagery class moonlet to be designed, the orbital period T of satellite is given according to design objective demand0.Needle
To given optical imagery class moonlet, the various operating modes of User Defined satellite, and define under various operating modes,
The working time of satellite under the working condition of each energy consumption equipment on satellite and each single operating mode.Next according to user
The working time of satellite, calculates each list of output satellite under the various operating modes of the satellite of input and each single operating mode
Satellite power consumption number under a operating mode, including stable state constant value power consumption, peak power, user-defined satellite power consumption, satellite
Single track total energy consumption.
(1) the satellite power consumption number under single operating mode is calculated；
If optical imagery class moonlet to be designed includes N kind energy consumption equipments, in any one user-defined satellite
Under operating mode, it is assumed that the quantity that all kinds of energy consumption equipments of satellite participate in work is xiA, the power consumption of all kinds of energy consumption equipments is respectively pi
(unit：W), then satellite power consumption P (units under the single operating mode：W) it is：
P=∑s xi·pi, i ∈ [1, N] (1)
It should be noted that under any one satellite operation pattern, the working condition of each energy consumption equipment of satellite is all to use
Family setting, the power consumption of each energy consumption equipment of satellite is that User Defined confirms.
In user-defined all satellite operation patterns, choose corresponding under working time longest satellite operation pattern
Satellite power consumption number, it is assumed that be Pw, as stable state constant value power consumption.Choose corresponding satellite under the maximum satellite operation pattern of power consumption
Power consumption number, it is assumed that be Pf, as peak power.In other user-defined satellite operation patterns, according to User Defined
The titles of other satellite operation patterns export its corresponding power consumption Pi。
(2) satellite single track total energy consumption is calculated；
Satellite single track total energy consumption is according to user-defined satellite operation pattern, according to an orbital period T0Interior satellite
The corresponding power consumption number of different working modes carry out statistics calculating.If in an orbital period T0It is same during certain interior period
When there are multiple-working mode (two kinds or two or more operating modes), then its Satellite power consumption is selected within the period
Satellite operation pattern corresponding to value maximum carries out the calculating of satellite single track total energy consumption.
One orbital period T0It is interior, it is assumed that working time of the satellite under a variety of different working modes is respectively ti(unit：
S), ∑ ti=T0, in an orbital period T0Power consumption of the interior satellite under various different working modes is respectively Pi, then satellite list
Rail total energy consumption E (units：Wh) it is：
Ew=∑ (ti/3600)·Pi, i ∈ [1, n] (2)
Wherein n is satellite in an orbital period T0The number of interior operating mode.
Second step, satellite Energy Balance Analysis and power-supply system are analyzed；Calculate solar battery array single track energy, sun electricity
The energy requirement of pond battle array power, effective solar array area, solar battery array design area and accumulator, and corresponded to
Solar battery array and accumulator type selecting.
Assuming that known satellite is averagely T by the time is shones(unit s), satellite single track total energy consumption Ew(unit Wh) is (in the first step
Satellite single track total energy consumption result of calculation).
Assuming that electricity-change transfer efficiency percentage is ηdh, it is defaulted as 90%；
Optical-electronic transfer efficiency percentage is ηgd, it is defaulted as 90%；
Design solar battery array type selecting：
Here two kinds of solar battery array types are designed to select for user：The first, three-junction gallium arsenide, cell array efficiency
Percentage is ηpEfficiency acquiescence 27%.Second, silicon, cell array Percent efficiency is ηpAcquiescence 14%.
Solar energy density Q, is taken as 1353.0W/m2；
Design energy nargin percentage x, user can customize, and be defaulted as 50%；
Cell array pieces of cloth Percent efficiency ηb, user can customize, and be defaulted as 80%；
Battery discharging Percent efficiency ηc, it is defaulted as 90%；
Battery discharging percent depth ηd, user can customize, and be defaulted as 30%.
Then have：
Solar battery array single track least energy Ep(unit Wh) is：
Ep=Ew/ηdh/ηgd (3)
Solar battery array minimum power Pp(unit W) is：
Pp=Ep/(Ts/3600) (4)
Solar battery array minimum effective area SE(unit m2) be：
SE=Pp/ηp/Q (5)
Solar battery array minimal design area Sd(unit m2) be：
Sd=SE/ηb (6)
Solar battery array design area S after consideration allowanced2(unit m2) be：
Sd2=Sd·(1+x) (7)
Effective solar array area S after consideration allowanceE2(unit m2) be：
SE2=Sd2·ηb (8)
Solar battery array power P after consideration allowancep2(unit W) is：
Pp2=SE2·ηp·Q (9)
Solar battery array single track ENERGY E after consideration allowancep2(unit Wh) is：
Ep2=Pp2·(Ts/3600) (10)
The energy requirement E of lithium battery groupb(unit Wh) is：
Eb=Ew/ηc/ηd (11)
Accumulator type selecting can user according to busbar voltage V (user can customize), according to the energy requirement E of lithium battery groupb,
Export the capacity E of accumulator groupb/ V (rounding) is suitable accumulator model, and type selecting is according to mono- grade of carry choosing of every 10Ah
It selects.
Compared with the existing technology, present invention produces following advantageous effects：
The present invention gives the analysis sides of the energy resource system satisfaction in optical imagery class moonlet collectivity Scheme Design stage
Method and process.The characteristics of optical imagery class satellite is combined in method and mission mode, establish Power budgets and Energy Sources Equilibrium point
The mathematical model of analysis, quantitative description satellite Energy Balance Analysis and power-supply system analysis method.This method orderliness is clear, correct
Rationally, design considerations can be provided for satellite master-plan personnel and power subsystem designer, in design of satellites and the field of development
With good application prospect.
Description of the drawings
Fig. 1 is the flow chart of the present invention
Specific implementation mode
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation describes, and is described in further details, but embodiments of the present invention are not limited only to this.
Referring to Fig.1, it is the flow chart of the present invention.The target of Satellite energy balance of the present invention is that single station single track carries out task
Operation, the electric energy of consumption can realize energy balance in single track.The present invention is from optical imagery class moonlet feature, first
In conjunction with user's requirement, the self-defined satellite power consumption number calculated under single operating mode；Then, according to satellite operation pattern,
According to single-rail working state reasonable consideration power consumption number (pattern containing full load), satellite single track total energy consumption is calculated；According to different batteries
The type selecting and design capacity of battle array, then calculate the solar battery array parameter for meeting Energy Sources Equilibrium requirement, including solar battery array list
Rail least energy, solar battery array minimum power, solar battery array minimum effective area, solar battery array minimal design area,
Consider allowance after solar battery array design area, consider allowance after effective solar array area, consider allowance after too
Positive cell array power considers solar battery array single track energy after allowance；Finally, the energy requirement of lithium battery group is calculated, and is carried out
Battery type selecting.The actual use pattern of this method combination satellite reasonably completes whole energy source of star satisfaction degree analysis.Engineering is practical
It proves that this method design procedure is progressive clearly, result holds water, desin speed is fast in, can be that the master-plan of satellite be established
Determine solid foundation.
With reference to specific implementation example, the present invention is further illustrated：
The first step, satellite Power budgets；
According to a kind of optical imagery class moonlet Power budgets provided by the invention and the in Energy Sources Equilibrium analysis method
It is as shown in the table to count the present embodiment Satellite power consumption for method in one step：
1 power consumption allocation table of table
As can be seen that each energy consumption equipment of satellite includes power management subsystem, generalized information management subsystem, appearance in table 1
Control the equipment in subsystem, load subsystem, data transmission subsystem and thermal control subsystem.User-defined satellite operation pattern
Including standby, run-up mode, autonomous video staring imaging pattern, data down transmission pattern, people in circuit video staring imaging
Pattern.
The distribution of satellite operation pattern and average power consumption at any time is as shown in table 2.In a task operating window, according to
Autonomous video staring imaging and data down transmission were calculated according to 5 minutes, and people calculated in circuit video staring imaging according to 3 minutes, were appointed
Business preparation was calculated according to 1 minute.Therefore, according to the real work pattern of satellite, choosing satellite standby, (i.e. earth station can not
Manipulation section), the satellite operation pattern corresponding to task run-up mode and task phase Satellite power consumption number maximum calculate and defends
The single track total energy consumption of star.With reference to table 2, in task phase, autonomous video staring imaging pattern, data down transmission pattern, people are in circuit
Satellite operation pattern corresponding to video staring imaging pattern Three models Satellite power consumption number maximum is that autonomous video is stared into
Picture, therefore power consumption corresponding under autonomous video staring imaging pattern during task is taken to be calculated, obtain the maximum in single track
Energy consumption is 244Wh.
2 satellite power consumption of table is distributed at any time
| Project | Power consumption (W) | Time (s) | Accumulative energy consumption (Wh) |
| It awaits orders | 128.8 | 5356 | 191.6 |
| Preparation | 465.6 | 60 | 7.76 |
| Autonomous video staring imaging | 535.8 | 300 | 44.65 |
| Data down transmission | 382.8 | 300 | 31.9 |
| People is in circuit video staring imaging | 722.8 | 180 | 36.14 |
| The satellite transit complete period | —— | 5716 | Maximum 244.01 |
The maximum value for taking three kinds of power consumption states, during single track is shone, the main battle array of solar cell should generate the energy of 244Wh.
Second step, satellite Energy Balance Analysis and power-supply system are analyzed
According to a kind of optical imagery class moonlet Power budgets provided by the invention and the in Energy Sources Equilibrium analysis method
Method in two steps, and the single track total energy consumption 244Wh that is the previously calculated carry out Energy Balance Analysis and power-supply system point
Analysis, the results are shown in table below：
3 satellite energy balance budget of table
According to the above power satellite design result, under the main battle array normal operating conditions of solar cell, in the pattern of operating at full capacity
Under can also realize the energy balance of single track.
In conclusion although the present invention has been disclosed as a preferred embodiment, however, it is not to limit the invention, any
Those of ordinary skill in the art, without departing from the spirit and scope of the present invention, when can make it is various change and retouch, therefore this hair
Bright protection domain is subject to the range defined depending on claims.
Claims (6)
1. a kind of optical imagery class moonlet Power budgets and Energy Sources Equilibrium analysis method, which is characterized in that include the following steps：
The first step, satellite Power budgets；
Given optical imagery class moonlet to be designed, the orbital period T of satellite is given according to design objective demand0；For given
Optical imagery class moonlet, various operating modes of User Defined satellite, and defining under various operating modes, on satellite
Each energy consumption equipment working condition and satellite under each single operating mode working time；Next according to input by user
The working time of satellite under the various operating modes and each operating mode of satellite, under the various operating modes for calculating output satellite
Satellite power consumption number, include the single track total energy consumption of stable state constant value power consumption, peak power, user-defined satellite power consumption, satellite；
Second step, satellite Energy Balance Analysis are analyzed with power-supply system；Calculate solar battery array single track energy, solar battery array
The energy requirement of power, effective solar array area, solar battery array design area and accumulator, and carry out it is corresponding too
The type selecting of positive cell array and accumulator.
2. optical imagery class moonlet Power budgets according to claim 1 and Energy Sources Equilibrium analysis method, feature exist
In：In the first step,
(1) the satellite power consumption number under single operating mode is calculated；
Under any one user-defined satellite operation pattern, it is assumed that the quantity that all kinds of energy consumption equipments of satellite participate in work is
xiA, the power consumption of all kinds of energy consumption equipments is respectively pi, then satellite power consumption P is under the single operating mode：
P=∑s xi·pi, i ∈ [1,N] (1)
Wherein N is the quantity of energy consumption equipment type；
In user-defined all satellite operation patterns, corresponding under working time longest satellite operation pattern defend is chosen
Star power consumption number, it is assumed that be Pw, as stable state constant value power consumption；
Choose corresponding satellite power consumption number under the maximum satellite operation pattern of power consumption, it is assumed that be Pf, as peak power；
In other user-defined satellite operation patterns, the title according to other user-defined satellite operation patterns is defeated
Go out its corresponding power consumption Pi；
(2) satellite single track total energy consumption is calculated；
Satellite single track total energy consumption is according to user-defined satellite operation pattern, according to an orbital period T0Interior satellite is not
With operating mode, corresponding power consumption number carries out statistics calculating；If in an orbital period T0It is deposited simultaneously during certain interior period
In multiple-working mode, then the satellite operation pattern corresponding to its Satellite power consumption number maximum is selected to be defended within the period
The calculating of star single track total energy consumption；
In an orbital period T0It is interior, it is assumed that working time of the satellite under a variety of different working modes is respectively ti, ∑ ti=T0,
Power consumption of the satellite under various different working modes is respectively Pi, then satellite single track total energy consumption be：
Ew=∑ (ti/3600)·Pi, i ∈ [1, n] (2)
Wherein n is satellite in an orbital period T0The number of interior operating mode.
3. optical imagery class moonlet Power budgets according to claim 2 and Energy Sources Equilibrium analysis method, feature exist
In：In second step, if known satellite is averagely T by the time is shones, electricity-change transfer efficiency percentage is ηdh, optical-electronic transfer efficiency
Percentage is ηgd, efficiency of solar array percentage is ηp, solar energy density Q, energy margin percentage x, cell array pieces of cloth
Percent efficiency ηb, battery discharging Percent efficiency ηc, battery discharging percent depth ηd；
Then have：
Solar battery array single track least energy EpFor：
Ep=Ew/ηdh/ηgd (3)
Solar battery array minimum power PpFor：
Pp=Ep/(Ts/3600) (4)
Solar battery array minimum effective area SEFor：
SE=Pp/ηp/Q (5)
Solar battery array minimal design area SdFor：
Sd=SE/ηb (6)
Solar battery array design area S after consideration allowanced2For：
Sd2=Sd·(1+x) (7)
Effective solar array area S after consideration allowanceE2For：
SE2=Sd2·ηb (8)
Solar battery array power P after consideration allowancep2For：
Pp2=SE2·ηp·Q (9)
Solar battery array single track ENERGY E after consideration allowancep2For：
Ep2=Pp2·(Ts/3600) (10)
The energy requirement E of lithium battery groupbFor：
Eb=Ew/ηc/ηd (11)
Wherein accumulator type selecting by user according to busbar voltage V, according to the energy requirement E of lithium battery groupb, output accumulator group
Capacity Eb/ V (rounding) is suitable accumulator model, and type selecting is according to mono- grade of carry select of every 10Ah.
4. according to optical imagery class moonlet Power budgets and Energy Sources Equilibrium analysis method described in claim 3, feature
It is：In second step, electricity-change transfer efficiency percentage ηdhIt is 90%；Optical-electronic transfer efficiency percentage ηgdIt is 90%；Solar energy
Metric density Q is taken as 1353.0W/m2, energy margin percentage x is 50%；Cell array pieces of cloth Percent efficiency ηbIt is 80%；Electric power storage
Tank discharge Percent efficiency ηcIt is 90%；Battery discharging percent depth ηdIt is 30%.
5. optical imagery class moonlet Power budgets according to claim 3 or 4 and Energy Sources Equilibrium analysis method, feature
It is：In second step, solar battery array type is three-junction gallium arsenide solar battery battle array, cell array Percent efficiency ηpFor
27%.
6. optical imagery class moonlet Power budgets according to claim 3 or 4 and Energy Sources Equilibrium analysis method, feature
It is：In second step, solar battery array type is Silicon solar array, cell array Percent efficiency ηpIt is 14%.
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