CN108491610A - A kind of optical imagery class moonlet master-plan and task analysis method - Google Patents
A kind of optical imagery class moonlet master-plan and task analysis method Download PDFInfo
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Abstract
A kind of optical imagery class moonlet master-plan of present invention offer and task analysis method have carried out mass budget, Power budgets, TTC channel budget, number biography link budget and cost budgeting first from optical imagery class moonlet feature；Satellite Energy Balance Analysis is carried out then in conjunction with task to analyze with power-supply system, satellite imagery capability analysis, the attitude of satellite determines precision, pointing accuracy and stability precision analysis, is finally to carry out satellite electric interfaces statistics, satellite data interface statistics, satellite hot interface statistics.This method content is comprehensive, orderliness is clear, simplifies, and can provide mentality of designing for satellite master-plan personnel, has good application prospect in design of satellites and the field of development.
Description
Technical field
The present invention relates to Spacecraft guidance and control fields, particularly, are related to a kind of optical imagery class moonlet master-plan and appoint
Business analysis method.
Background technology
Satellite master-plan is related to examine in multi-subject design, analysing content and engineering practice with task analysis
The a variety of design factors considered, are a comprehensive, complicated system engineerings.Selected by each population parameter of satellite master-plan
Numerical value to the overall performance of satellite, the reliability of satellite system, the expense of satellite system and develop difficulty suffer from it is decisive
Effect.
For the satellite master-plan stage, system design goal has the characteristics that ambiguity, subjectivity lead to satellite system
The design parameter of master-plan there are many uncertainties, therefore be difficult to provide the satellite master-plan of a standard and appoint
Business analysis method, therefore the open source literature of this respect is 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 the master-plan of class moonlet and task analysis method, the master-plan stage of optical imagery class moonlet is can be directly used for, is
Satellite engineering designer provides reference.The method achieve the item of design of satellites threads to analyze, and simplifies, solves satellite and grind
Coupling during hair and complexity problem are proving the progressive clear, result of this method design procedure in practical implementation just
Really rationally, desin speed it is fast, can be further satellite engineering development establish solid foundation.
To achieve the above object, the present invention uses following technical scheme：
A kind of optical imagery class moonlet master-plan and task analysis method, include the following steps：
The first step, satellite mass budget
If optical imagery class moonlet to be designed is made of N kind components, the quantity of various parts is respectively xiIt is a, it is various
The substance of component is respectively wi, then satellite gross mass W be：
W=∑s xi·wi, i ∈ [1, N] (1)
Second step, satellite Power budgets
For optical imagery class moonlet to be designed, the orbital period T of satellite is given according to design objective demand0.Needle
To optical imagery class moonlet to be designed, the various operating modes of User Defined satellite are defined under various operating modes, are defended
The working time of satellite under the working condition of each energy consumption equipment on star and each operating mode.Next according to input by user
The working time of satellite under the various operating modes of satellite and each single operating mode, calculate each single work of output satellite
Satellite power consumption number under pattern includes the single track of stable state constant value power consumption, peak power, user-defined satellite power consumption, satellite
Total energy consumption.
(1) the satellite power consumption number under single operating mode is calculated；
If optical imagery class moonlet to be designed includes M kind energy consumption equipments, in any one user-defined satellite
Under operating mode, it is assumed that the quantity that the various energy consumption equipments of satellite participate in work is yiA, the power consumption of various energy consumption equipments is respectively pi
(unit：W), then satellite power consumption P (units under the single operating mode：W) it is：
P=∑s yi·pi, i ∈ [1, M] (2)
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.Such as：Payload segment is not switched on usually usually, work(
Consumption takes 0 (being calculated according to steady state power consumption for particular/special requirement), solar battery array to take 0, and structure takes 0 with mechanism section；Reaction
When flywheel works, quantity takes 3 calculating, magnetic torquer to be only used for not calculating generally when flywheel unloading according to maximum, is taken as 0.
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 wherein maximum satellite is selected within the period
Satellite operation pattern corresponding to power consumption number 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 (unit：Wh) it is：
Ew=∑ (ti/3600)·Pi, i ∈ [1, n] (3)
Wherein n is satellite in an orbital period T0The number of interior satellite operation pattern.
Third walks：Satellite downlink number passes link budget
Estimate that satellite downlink number passes link according to communication system parameter, computational methods are as follows
In formula：
In formula：
EIRP1For satellite launch equivalent isotropically radiated power (dBm)：
EIRP1=PT1+GT1-LT1 (5)
Wherein PT1For satellite launch power (unit dBm)；GT1For satellite transmitting antenna gain (unit dB)；LT1For satellite
(unit dB) is lost in feeder network.
Ls1For star-ground free space loss：
Ls1=32.4+20log10 (d)+20log10 (f) (6)
Maximum distance when wherein d takes star-ground visible when being link budget according to space geometry relationship, unit km；F is to defend
Star tranmitting frequency, unit MHz.
LP1It is directed toward loss (unit dB) for satellite antenna, according to actual test selected value, generally less than 0.5dB.
LPO1(unit dB) is lost for satellite antenna polarization, according to actual test selected value, generally less than 0.5dB.
LCIt declines (dB) for rain, (S-band 3GHz or less generally takes 0 to the curve graph value provided according to national military standard (GJB), X-band
Value 2dB).
LP2It is directed toward loss (unit dB) for earth station antenna, according to actual test selected value, generally less than 0.5dB.
LPO2For earth station antenna polarization loss (unit dB), according to actual test selected value, generally less than 0.5dB.
LGround(unit dB) is lost for earth station's feeder network generally to can be evaluated whether as 3dB according to actual conditions value.
Satellite can be obtained to ground receiver power PR(unit dBm)
PR=EIRP1-LS1-LP1-LPO1-LC-LP2-LPO2-LGround。
G/T is earth station antenna quality factor, unit (dB/K)：
G/T=GR1-10log10(TS) (7)
Wherein, GR1For earth station antenna gain, speciallyD is parabola antenna bore；λ
For electric wave wavelength,Unit m, c are the light velocity, and f is satellite launch frequency；G is antenna efficiency, and general value is 0.5；TSFor
Earth station antenna noise temperature, unit K.General earth station antenna can provide the G/T values under different frequency range.
kbFor Boltzmann constant, specially -228.6dB/HzK.
[Rb] it is transmitted data rates (dB), [Rb]=10log10 Rb, Rb(kbps) it is determined according to system actual conditions.
MSFor modulation loss (dB), general value is no more than 0.5dB；
DMSFor demodulation losses (dB), general value is no more than 0.5dB；
GcodeFor coding gain (dB), according to different coding mode, value is different, and value is 0 when not encoding；
[Eb/n0]thFor theoretical snr of received signal Eb/N0 (dBHz), determined according to modulation system.General QPSK and
BPSK values are 10.5dB.
4th step, TTC channel budget；
(1)-star uplink budget
Known satellite receiver sensitivity, ground-star uplink budget method are as follows：
EIRP2Emit equivalent isotropically radiated power (dBm) for earth station：
EIRP2=PT2+GT2-LT2 (9)
Wherein PT2For earth station's transmission power (dBm)；GT2For ground station transmitting antenna gain (dB), for paraboloid day
For line,D is parabola antenna bore in formula；λ is electric wave wavelength,Unit m, c are
The light velocity, f are earth station's tranmitting frequency；
gFor antenna efficiency, general value is 0.5；LT2It is lost for earth station's feeder network；
LP1It is directed toward loss (dB) for satellite antenna, according to actual test selected value, generally less than 0.5dB.
LP2It is directed toward loss (dB) for earth station antenna, according to actual test selected value, generally less than 0.5dB.
Ls2For ground-star free space loss：(dB)：
Ls2=32.4+20log10 (d)+20log10 (f) (10)
Maximum distance when wherein d takes star-ground visible when being link budget according to space geometry relationship, unit km；f
For earth station's tranmitting frequency, unit MHz.
LPO1(dB) is lost for satellite antenna polarization, according to actual test selected value, generally less than 0.5dB.
LPO2For earth station antenna polarization loss (dB), according to actual test selected value, generally less than 0.5dB.
GR2For satellite earth antenna gain (dB), provided according to antenna parameter.
PminFor satellite receiver sensitivity (dBm).
(2) star-ground downlink link budget
Star-ground downlink link budget method, specific calculate pass link calculation method, institute with line number under " third step " Satellite
The calculation formula of use is identical, and only the parameters such as tranmitting frequency, transmission power of satellite are different, only need to be according to actual parameter
" satellite downlink number passes link budget " formula calculates in being walked using third, and which is not described herein again.
5th step, satellite cost budget
If forming in all components of satellite, electrically the quantity of part, identification part and positive exemplar is respectively xdi、xji、xziIt is a,
Each electrical part cost is mdi(unit is generally ten thousand yuan, similarly hereinafter)；Each electrical part cost is mji；Each positive exemplar cost is mzi, then group
At the hard cost M of all components of satellitebzjFor
Mbzj=∑ xdi·wdi+∑xji·wji+∑xzi·wzi (11)
If overall system design cost Mg, system software cost Ms, System Integration Test cost Mi, environmental test cost Mt,
Transportation cost Mc, target range cost Mr。
To sum up, satellite system minimum cost M is
M=Mbzj+Mg+Ms+Mi+Mt+Mc+Mr (12)
6th step, satellite Energy Balance Analysis and power-supply system are analyzed, that is, 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.It is the flow of satellite Energy Balance Analysis and power-supply system analysis with reference to Fig. 2, Fig. 2
Figure.
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 second 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 solar battery battle array,
Cell array Percent efficiency is ηpEfficiency acquiescence 27%.Second, Silicon solar array, cell array Percent efficiency is ηpIt is silent
Recognize 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 (13)
Solar battery array minimum power Pp(unit W) is：
Pp=Ep/(Ts/3600) (14)
Solar battery array minimum effective area SE(unit m2) be：
SE=Pp/ηp/Q (15)
Solar battery array minimal design area Sd(unit m2) be：
Sd=SE/ηb (16)
Solar battery array design area S after consideration allowanced2(unit m2) be：
Sd2=Sd·(1+x) (17)
Effective solar array area S after consideration allowanceE2(unit m2) be：
SE2=Sd2·ηb (18)
Solar battery array power P after consideration allowancep2(unit W) is：
Pp2=SE2·ηp·Q (19)
Solar battery array single track ENERGY E after consideration allowancep2(unit Wh) is：
Ep2=Pp2·(Ts/3600) (20)
The energy requirement E of lithium battery groupb(unit Wh) is：
Eb=Ew/ηc/ηd (21)
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.
It is the flow chart of satellite imagery capability analysis and the analysis of gesture stability index request, the i.e. present invention the 7th with reference to Fig. 3
It walks to the flow diagram of the 9th step.
7th step, the analysis of satellite load imaging capability
The optics load CCD or the total pixel of cmos sensor that known optical is imaged on class moonlet are L × B, pixel dimension
For μ (unit is μm), lens focus is that (unit m), camera lens F numbers, satellite orbital altitude are H (unit km) to f.
According to the above-mentioned known parameters of optical imagery load to its imaging of the optical imagery load of optical imagery class moonlet
Ability is calculated, including assumed (specified) load substar pixel resolution, the breadth being imaged over the ground over the ground, sensor field of view angle, mirror
Head bore diameter, image planes size and resolution of diffraction.
(1) assumed (specified) load substar pixel resolution over the ground；
(unit m) is substar pixel resolution r load over the ground：
μ × 10 r=-6·(H×103/F) (22)
(2) breadth being imaged over the ground is calculated, respectively：
Length direction (unit km)：r·L/1000 (23)
Width direction (unit km)：r·B/1000 (24)
(3) sensor field of view angle is calculated
Optics load CCD or the field angle of cmos sensor requirement are respectively：
Length direction (unit °)：
Width direction (unit °)：
(4) lens opening, image planes size
Lens opening d (unit mm)：
D=f/F1000 (27)
Image planes size (unit mm) is：
(L·μ/1000)×(B·μ/1000) (28)
(5) (unit m) is resolution of diffraction r '：
R '=H × 103·θ (29)
1.22 λ of θ ≈/(d/1000) in formula, wherein λ are optical wavelength, and d is lens opening.
8th step judges whether satellite load design is reasonable
If by formula (22) calculated load, substar pixel resolution r is numerically greater than by formula (29) meter over the ground
Obtained resolution of diffraction r ', then illustrate reasonable design (such as：Assuming that by formula (22) calculated load substar over the ground
Pixel resolution r is 2 meters, and the resolution of diffraction r ' being calculated by formula (29) is 1 meter, then it represents that reasonable design), after
The step of continuing subsequent nine step.
If by formula (22) calculated load, substar pixel resolution r is numerically less than by formula (29) calculating over the ground
Obtained resolution of diffraction r ' then illustrates that substar pixel resolution r has surmounted spreading out for camera lens to designed load over the ground
Limiting resolution is penetrated, the index being actually not achieved, design is unreasonable (such as：Assuming that by formula (22) calculated load
Substar pixel resolution r is 0.5 meter over the ground, and the resolution of diffraction r ' being calculated by formula (29) is 1 meter, then it represents that
Design requirement is not achieved in system, and design is unreasonable), the 7th step is returned, type selecting is carried out to camera lens again, changes lens focus
Or aperture, making the load of design, substar pixel resolution r is more than resolution of diffraction r ' over the ground.
9th step, the attitude of satellite determine precision, satellite pointing accuracy and the analysis of stability precision index；
(1) satellite pointing accuracy rp(unit is °) is：
rpThe π of=W/m/H × 180/ (30)
W indicates the length direction for the breadth being imaged over the ground in formula.M indicates that satellite is directed toward the 1/m that offset is no more than W, root
According to engineering experience, the default setting is m=20, and user can also be self-defined according to actual demand modification, but suggests m ∈ [10,30].
(2) attitude of satellite determines precision rd(unit is °) is：
rd=rp/2 (31)
Above formula indicates that the attitude of satellite determines that precision is rule of thumb taken as the 1/2 of satellite pointing accuracy, and designer can also
It changes self-defined.
(3) satellite is directed toward instantaneous imaging to target and requires stability Si(unit：°/s) be：
Si=arcsin (r/n/H/1000)/te×180/π (32)
Above formula indicates that satellite is directed toward instantaneous imaging to target and requires to be no more than 1/n pixel, is rule of thumb set as n=3,
Designer can also be self-defined according to actual demand modification, but suggests n ∈ [2,5].teIndicate instantaneous imaging time for exposure, root
It is determined according to optics load CCD or cmos sensor parameter setting.
(4) it if satellite is to stare the imaging of class video successive frame to target, is transferred to (5)；Otherwise, design satellite is to target
It is directed toward imaging stability SpInstantaneous imaging is directed toward to target for satellite and requires stability Si, i.e. Sp=Si。
(5) it calculates satellite and successive frame imaging requirements stability is directed toward to target
Assuming that cameras frame rate is fr (unit f/s), satellite is directed toward successive frame imaging requirements stability S to targetcIt is (single
Position：°/s) be：
Sc=arcsin (r × p/H/1000)/(1/fr) × 180/ π (33)
When above formula indicates that satellite is directed toward successive frame imaging to target, rule of thumb front and back two frames require to scheme between two continuous frames
Image jump is not more than 3~5 pixels, i.e. p ∈ [3,5], general acquiescence p is 4, and designer can change self-defined.
(6) design satellite is directed toward imaging stability S to targetp(unit：°/s) take target direction instantaneous imaging to aspire for stability
Degree and that value smaller to target direction successive frame imaging requirements stability, as：
Sp=min (Si,Sc) (34)
Further, the invention also includes satellite electric interfaces statistics, satellite data interface statistics and satellite hot interfaces
Statistics.
Satellite electric interfaces count：
Assuming that there is R kinds to need the building block powered in satellite, it is n that the quantity for the building block powered is needed in satellitei
It is a, and it is v respectively to need the supply voltage for the building block poweredi, then the total power supply way of satellite be：
U=∑s ni, i ∈ [1, R] (35)
Further, according to the supply voltage v of each building block for needing to poweriClassify, counts different voltages respectively
Power supply way.
Satellite data interface statistics：
Some has data-interface in the building block of satellite, and all data-interfaces of satellite are classified, are united respectively
Count total interface type.(to include also house keeping computer, intelligent interface unit with Integrated Electronic System after interface statistics
Deng) included all connection equipment interfaces carry out matching comparison, judge whether spaceborne computer disclosure satisfy that the interface of whole star
Demand, provide design whether rational conclusion.
Satellite hot interface counts：
A part has hot interface in the building block of satellite, and all hot interface information of satellite are extracted, including
Start-up temperature, operating temperature, storage temperature etc. carry out hot interface statistics.
Above each step calculates and statistical result can automatically generate list according to the format customized in advance.
Compared with the existing technology, present invention produces following advantageous effects：
The present invention gives the master-plans in optical imagery class moonlet collectivity Scheme Design stage and task analysis method
With process.The quantitative description mass budget of satellite, Power budgets, TTC channel budget, number pass link budget, cost in method
The design contents such as budget, and combine optical imagery class satellite the characteristics of and mission mode, quantitatively give satellite energy balance
Analysis is analyzed with power-supply system, and satellite imagery capability analysis and the attitude of satellite determine precision, pointing accuracy and stability precision
Analysis method.Satellite electric interfaces statistics, satellite data interface statistics, satellite hot interface statistical method are additionally provided simultaneously.It should
Method content is comprehensive, orderliness is clear, simplifies, and mentality of designing can be provided for satellite master-plan personnel, in design of satellites
There is good application prospect with the field of development.
Description of the drawings
Fig. 1 is the frame diagram of the present invention；
Fig. 2 is the flow chart of satellite Energy Balance Analysis and power-supply system analysis；
Fig. 3 is the flow chart of satellite imagery capability analysis and the analysis of gesture stability index request；
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, the present invention is from optical imagery class moonlet feature, from optical imagery class moonlet feature,
Mass budget, Power budgets, TTC channel budget, number biography link budget and cost budgeting have been carried out first；Then in conjunction with task
It has carried out satellite Energy Balance Analysis to analyze with power-supply system, satellite imagery capability analysis, the attitude of satellite determines precision, is directed toward essence
Degree and stability precision analysis are finally to carry out satellite electric interfaces statistics, satellite data interface statistics, satellite hot interface system
Meter.
With reference to specific implementation example, the present invention is further illustrated：
Step 1: satellite mass budget；
Optical imagery class moonlet to be designed is by structure and train of mechanism, power-supply management system, satellited system, posture control
System processed, TT＆C system, loading device sum number pass equipment composition, wherein building block and each component that each system includes
Quantity, substance situation are as shown in table 1：
1 mass distribution table of table
Step 2：Satellite Power budgets
It is as shown in the table to count satellite power consumption.
2 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 2
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 3.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 3, 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.
3 satellite power consumption of table is distributed at any time
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.
Step 3：Satellite data transmission link budget
Assuming that known star ground downlink data rate 150Mbps, satellite launch power 10W, terrestrial receiving antenna 10m bores,
Reception antenna noise temperature is 100K, then link budget is as follows：
4 satellite data transmission link budget of table
| Project | Parameter | Remarks |
| Satellite launch frequency f (MHz) | 8600.00 | |
| Satellite launch power P t (dBm) | 40.00 | 10W |
| Satellite transmitting antenna gain G t (dB) | 5.00 | |
| Satellite feeder loss (dB) | 2.00 | |
| Satellite launch EIRP (dBm) | 43.00 | |
| Antenna minimum angle of elevation (°) | 5.00 | |
| Star-ground free space loss (dB) | 177.29 | Orbit altitude 500km |
| Satellite antenna is directed toward loss (dB) | 0.00 | |
| (dB) is lost in satellite antenna polarization | 0.00 | |
| Rain declines (dB) | 2.30 | |
| Earth station antenna is directed toward loss Lp0 (dB) | 0.50 | |
| Earth station antenna polarization loss Lp1 (dB) | 0.50 | |
| Earth station feeder loss Lr (dB) | 1.00 | |
| Satellite is to ground receiver power P rmin (dBm) | -138.59 | |
| Earth station antenna gain G r (dB) | 48.14 | 10m antennas |
| Earth station antenna quality factor (dB/K) | 35.00 | |
| Boltzmann constant (dB/Hz.K) | -228.60 | |
| Transmitted data rates Rb (kbps) | 150000.00 | |
| Transmitted data rates [Rb] (dB) | 81.76 | |
| Modulation loss Lm (dB) | 0.50 | |
| Demodulation losses Ldem (dB) | 2.50 | |
| Coding gain Cg (dB) | 6.00 | |
| Theoretical Eb/N0 (dBHz) | 10.50 | QPSK is modulated |
| System margin (dB) | 5.75 |
Step 4：Satellite TT link budget
It is as follows to calculate TTC channel budget：
Observing and controlling distant control chain circuit (- star uplink) budget of 5 star of table ground
6 star of table ground observing and controlling telemetering (star-ground downlink) link budget
Step 5：Satellite cost budget
It is as shown in table 7 to calculate satellite cost：
7 satellite cost budget of table
Step 6: satellite Energy Balance Analysis is analyzed with power-supply system
Using the single track total energy consumption 244Wh being calculated in step 2, carries out Energy Balance Analysis and is analyzed with power-supply system,
The results are shown in table below：
8 satellite energy balance budget of table
Step 7：Satellite technology realizes imaging capability analysis
If being equipped with two optics load, respectively 1 high-resolution camera and 1 low resolution video camera on satellite,
The cmos sensor that the two uses is identical, and pixel is 4K × 3K, and pixel dimension size is 6um.High-resolution camera
Lens parameters are 10 using focal length 2000mm, F number, and the lens parameters of low resolution video camera use focal length for 150mm, and F numbers are
5.6.Assuming that satellite orbital altitude 500km, as follows to satellite load imaging analysis result：
9 satellite imagery capability analysis of table
According to table 9 it is found that load over the ground substar pixel resolution r be more than resolution of diffraction r ', then illustrate load
Reasonable design, the step of continuation below.
Step 8：The attitude of satellite determines that precision, pointing accuracy and stability precision profiling are obtained according in step 7
Optics load imaging capability analysis result, carry out the attitude of satellite determine precision, pointing accuracy and stability precision index requirement
Analysis, the present embodiment Satellite are that video staring imaging class satellite, that is, satellite is to stare the imaging of class video successive frame, needle to target
To high-resolution camera imaging design, frame frequency 25fbps：
10 attitude of satellite index analysis of table
Step 9：Satellite electric interfaces count
Classify to each building block supply voltage, and counts the power supply way of different voltages respectively.
11 satellite electric interfaces of table count
Step 10：Satellite data interface statistics
Each composition parts data interface is counted：
3 satellite data interface statistics of table
Step 11：Satellite hot interface counts
Each building block hot interface is counted：
4 satellite hot interface of table counts
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 (10)
1. a kind of optical imagery class moonlet master-plan and task analysis method, which is characterized in that include the following steps：
The first step, satellite mass budget；
Second step, satellite Power budgets；
For optical imagery class moonlet to be designed, the orbital period T of satellite is given according to design objective demand0, user makes by oneself
The various operating modes of adopted satellite, define under various operating modes, the working condition and each work of each energy consumption equipment on satellite
The working time of satellite under operation mode；Next according to the various operating modes of satellite input by user and each single Working mould
The working time of satellite under formula calculates the satellite power consumption number under each single operating mode of output satellite, including stable state constant value work(
The single track total energy consumption of consumption, peak power, user-defined satellite power consumption, satellite；
Third walks：Satellite downlink number passes link budget；
4th step, TTC channel budget, including ground-star uplink budget and star-ground downlink link budget；
5th step, satellite cost budget；
6th step, satellite Energy Balance Analysis and power-supply system are analyzed, that is, 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；
7th step, the analysis of satellite load imaging capability
Known optical be imaged class moonlet on optics load CCD or the total pixel of cmos sensor be L × B, pixel dimension μ,
Lens focus is f, camera lens F numbers, satellite orbital altitude H；
According to the above-mentioned known parameters of optical imagery load to its imaging capability of the optical imagery load of optical imagery class moonlet
It is calculated, including assumed (specified) load substar pixel resolution, the breadth being imaged over the ground over the ground, sensor field of view angle, camera aperture
Diameter, image planes size and resolution of diffraction；
8th step, according to the satellite load imaging capability analysis result in the 7th step, judge whether satellite load design reasonable；
9th step, the attitude of satellite determine precision, satellite pointing accuracy and the analysis of stability precision index.
2. optical imagery class moonlet master-plan according to claim 1 and task analysis method, it is characterised in that：The
In one step, if optical imagery class moonlet to be designed is made of N kind components, the quantity of various parts is respectively xiIt is a, it is various
The substance of component is respectively wi, then satellite gross mass W be：
W=∑s xi·wi, i ∈ [1, N] (1).
3. optical imagery class moonlet master-plan according to claim 1 and task analysis method, it is characterised in that：The
In two steps, implementation method is as follows：
(1) the satellite power consumption number under single operating mode is calculated；
If optical imagery class moonlet to be designed includes M kind energy consumption equipments, in any one user-defined satellite operation
Under pattern, it is assumed that the quantity that the various energy consumption equipments of satellite participate in work is yiA, the power consumption of various energy consumption equipments is respectively pi, then
Satellite power consumption P is under the single operating mode：
P=∑s yi·pi, i ∈ [1, M] (2)
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 wherein maximum satellite power consumption number is selected to be defended within the period
The calculating of star 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, ∑ ti=T0,
One orbital period T0Power consumption of the interior satellite under various different working modes is respectively Pi, then satellite single track total energy consumption be：
Ew=∑ (ti/3600)·Pi, i ∈ [1, n] (3)
Wherein n is satellite in an orbital period T0The number of interior satellite operation pattern.
4. optical imagery class moonlet master-plan according to claim 1 and task analysis method, it is characterised in that：The
In three steps, estimate that satellite downlink number passes link, computational methods such as following formula according to communication system parameter：
In formula：
EIRP1For satellite launch equivalent isotropically radiated power：
EIRP1=PT1+GT1LT1 (5)
Wherein PT1For satellite launch power；GT1For satellite transmitting antenna gain；LT1It is lost for satellite feeder network；
Ls1For star-ground free space loss：
Ls1=32.4+20log10 (d)+20log10 (f) (6)
Maximum distance when wherein d takes star-ground visible when being link budget according to space geometry relationship, unit km；F is to defend
Star tranmitting frequency, unit MHz；
LP1It is directed toward and is lost for satellite antenna, according to actual test selected value, value is less than 0.5dB；
LPO1It is lost for satellite antenna polarization, according to actual test selected value, value is less than 0.5dB；
LCIt declines for rain, the curve graph value provided according to national military standard GJB, wherein S-band 3GHz or less takes 0, X-band value 2dB；
LP2It is directed toward and is lost for earth station antenna, according to actual test selected value, value is less than 0.5dB；
LPO2For earth station antenna polarization loss, according to actual test selected value, value is less than 0.5dB；
LGroundIt is lost for earth station's feeder network, value 3dB；
Satellite can be obtained to ground receiver power PR：
PR=EIRP1-LS1-LP1-LPO1LC-LP2-LPO2-LGround；
G/T is earth station antenna quality factor：
G/T=GR1-10log10(TS) (7)
Wherein, GR1For earth station antenna gain,D is parabola antenna bore；λ is electric wave wave
It is long,Unit m, c are the light velocity, and f is satellite launch frequency；G is antenna efficiency, value 0.5；TSIt makes an uproar for earth station antenna
Sound temperature, unit K；
kbFor Boltzmann constant, value is -228.6dB/HzK；
RbFor transmitted data rates, [Rb]=10log10 Rb；
MSFor modulation loss, value is no more than 0.5dB；
DMSFor demodulation losses, value is no more than 0.5dB；
GcodeFor coding gain；
[Eb/n0]thFor theoretical snr of received signal Eb/N0.
5. optical imagery class moonlet master-plan according to claim 1 and task analysis method, it is characterised in that：The
In four steps, it is known that satellite receiver sensitivity, ground-star uplink budget method are as follows：
EIRP2Emit equivalent isotropically radiated power (dBm) for earth station：
EIRP2=PT2+GT2-LT2 (9)
Wherein PT2For earth station's transmission power；GT2For ground station transmitting antenna gain, for parabola antenna,D is parabola antenna bore in formula；λ is electric wave wavelength,Unit m, c are the light velocity, and f is
Earth station's tranmitting frequency；G is antenna efficiency, value 0.5；LT2It is lost for earth station's feeder network；
LP1It is directed toward and is lost for satellite antenna, value is less than 0.5dB；
LP2It is directed toward and is lost for earth station antenna, value is less than 0.5dB；
Ls2For ground-star free space loss：
Ls2=32.4+20log10 (d)+20log10 (f) (10)
Maximum distance when wherein d takes star-ground visible when being link budget according to space geometry relationship, unit km；F is ground
Face station tranmitting frequency, unit MHz；
LPO1It is lost for satellite antenna polarization, value is less than 0.5dB；
LPO2For earth station antenna polarization loss, value is less than 0.5dB；
GR2For satellite earth antenna gain；
PminFor satellite receiver sensitivity.
6. optical imagery class moonlet master-plan according to claim 4 and task analysis method, it is characterised in that：The
In four steps, the satellite downlink number biography link calculation method during star-ground downlink link budget method is walked with third is identical.
7. optical imagery class moonlet master-plan according to claim 1 and task analysis method, it is characterised in that：The
In five steps, if electrically the quantity of part, identification part and positive exemplar is respectively x in all components of composition satellitedi、xji、xziIt is a,
Each electrical part cost is mdi；Each electrical part cost is mji；Each positive exemplar cost is mzi, then the hard of all components of satellite is formed
Cost MbzjFor
Mbzj=∑ xdi·wdi+∑xji·wji+∑xzi·wzi (11)
If overall system design cost Mg, system software cost Ms, System Integration Test cost Mi, environmental test cost Mt, transport
Cost Mc, target range cost Mr；
To sum up, satellite system minimum cost M is
M=Mbzj+Mg+Ms+Mi+Mt+Mc+Mr (12)。
8. optical imagery class moonlet master-plan according to claim 3 and task analysis method, it is characterised in that：The
In six steps, it is assumed that known satellite is averagely T by the time is shones, satellite single track total energy consumption Ew；
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%；
If solar battery array is three-junction gallium arsenide solar battery battle array or Silicon solar array, wherein three-junction gallium arsenide solar battery
Battle array, cell array Percent efficiency are ηp, value 27%；Silicon solar array, cell array Percent efficiency are ηp, value
It is 14%；
Solar energy density Q, is taken as 1353.0W/m2；
Design energy nargin percentage x, is taken as 50%；
Cell array pieces of cloth Percent efficiency ηb, it is taken as 80%；
Battery discharging Percent efficiency ηc, it is taken as 90%；
Battery discharging percent depth ηd, it is taken as 30%；
Then have：
Solar battery array single track least energy EpFor：
Ep=Ew/ηdh/ηgd (13)
Solar battery array minimum power PpFor：
Pp=Ep/(Ts/3600) (14)
Solar battery array minimum effective area SEFor：
SE=Pp/ηp/Q (15)
Solar battery array minimal design area SdFor：
Sd=SE/ηb (16)
Solar battery array design area S after consideration allowanced2For：
Sd2=Sd·(1+x) (17)
Effective solar array area S after consideration allowanceE2For：
SE2=Sd2·ηb (18)
Solar battery array power P after consideration allowancep2For：
Pp2=SE2·ηp·Q (19)
Solar battery array single track ENERGY E after consideration allowancep2For：
Ep2=Pp2·(Ts/3600) (20)
The energy requirement E of lithium battery groupbFor：
Eb=Ew/ηc/ηd (21)
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.
9. optical imagery class moonlet master-plan according to claim 1 and task analysis method, it is characterised in that：The
In seven steps,
(1) substar pixel resolution r is assumed (specified) load over the ground：
μ × 10 r=-6·(H×103/F) (22)
(2) breadth being imaged over the ground is calculated, respectively：
Length direction：r·L/1000 (23)
Width direction：r·B/1000 (24)
(3) sensor field of view angle is calculated
Optics load CCD or the field angle of cmos sensor requirement are respectively：
Length direction：
Width direction：
(4) lens opening, image planes size
Lens opening d：
D=f/F1000 (27)
Image planes size is：
(L·μ/1000)×(B·μ/1000) (28)
(5) resolution of diffraction r ' is：
R '=H × 103·θ (29)
1.22 λ of θ ≈/(d/1000) in formula, wherein λ are optical wavelength, and d is lens opening.
10. optical imagery class moonlet master-plan according to claim 8 and task analysis method, it is characterised in that：
In 8th step, if substar pixel resolution r is numerically greater than by formula (29) over the ground by formula (22) calculated load
The step of resolution of diffraction r ' being calculated then illustrates reasonable design, continues subsequent nine step；
If by formula (22) calculated load, substar pixel resolution r is numerically less than and is calculated by formula (29) over the ground
Resolution of diffraction r ', then illustrate that substar pixel resolution r has surmounted the diffraction pole of camera lens to designed load over the ground
Resolution ratio is limited, the index being actually not achieved, design is unreasonable, returns to the 7th step, carries out type selecting to camera lens again, changes
Become lens focus or aperture, making the load of design, substar pixel resolution r is more than resolution of diffraction r ' over the ground
In 9th step,
(1) satellite pointing accuracy rpFor：
rpThe π of=W/m/H × 180/ (30)
W indicates the length direction for the breadth being imaged over the ground in formula；M expression satellite direction the offsets 1/m no more than W, m ∈ [10,
30]；
(2) attitude of satellite determines precision rdFor：
rd=rp/2 (31)
(3) satellite is directed toward instantaneous imaging to target and requires stability SiFor：
Si=arcsin (r/n/H/1000)/te×180/π (32)
Above formula indicates that satellite is directed toward instantaneous imaging to target and requires to be no more than 1/n pixel, n ∈ [2,5]；teIndicate instantaneous imaging
Time for exposure；
(4) it if satellite is to stare the imaging of class video successive frame to target, is transferred to (5)；Otherwise, design satellite is directed toward target
Image stabilization degree SpInstantaneous imaging is directed toward to target for satellite and requires stability Si, i.e. Sp=Si；
(5) it calculates satellite and successive frame imaging requirements stability is directed toward to target
Assuming that cameras frame rate is fr, satellite is directed toward successive frame imaging requirements stability S to targetcFor：
Sc=arcsin (r × p/H/1000)/(1/fr) × 180/ π (33)
[3,5] p ∈ in above formula；
(6) design satellite is directed toward imaging stability S to targetpTarget is taken to be directed toward instantaneous imaging requirement stability and be directed toward to target
That smaller value of successive frame imaging requirements stability, as：
Sp=min (Si,Sc) (34)。
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Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140145877A1 (en) * | 2012-11-27 | 2014-05-29 | Eutelsat S A | Method of geo localization of a terminal sending a single signal to a satellite system |
| US20140160970A1 (en) * | 2013-11-21 | 2014-06-12 | Comtech Ef Data Corp. | System and method for satellite link budget analysis (lba) optimization |
| CN103929232A (en) * | 2014-04-23 | 2014-07-16 | 西安电子科技大学 | Broadband mobile communication method and system based on multi-beam GEO satellite |
| CN104133932A (en) * | 2014-05-27 | 2014-11-05 | 中国空间技术研究院 | Satellite overall plan confirmation system based on multidisciplinary optimization and realization method |
| US20160043800A1 (en) * | 2014-08-05 | 2016-02-11 | Ryan Wallace KINGSBURY | Design of a free-space optical communication module for small satellites |
| CN106599334A (en) * | 2016-09-19 | 2017-04-26 | 航天东方红卫星有限公司 | Planning method for short-term and effective load work with capability of increasing energy utilization efficiency of satellites |
| US20170118729A1 (en) * | 2015-10-27 | 2017-04-27 | The Boeing Company | Satellite Link Budget Command Interface Tool |
| CN106934217A (en) * | 2017-02-16 | 2017-07-07 | 北京空间飞行器总体设计部 | A kind of spacecraft power fast synthesis method and system based on mission program |
| CN106950975A (en) * | 2017-01-24 | 2017-07-14 | 上海卫星工程研究所 | Large angle maneuver high-resolution microwave remote sensing satellite overall control method |
| CN107733515A (en) * | 2017-08-31 | 2018-02-23 | 北京空间飞行器总体设计部 | Satellite communication link analysis method under a kind of in-orbit complex environment |
-
2018
- 2018-03-15 CN CN201810213205.6A patent/CN108491610B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140145877A1 (en) * | 2012-11-27 | 2014-05-29 | Eutelsat S A | Method of geo localization of a terminal sending a single signal to a satellite system |
| US20140160970A1 (en) * | 2013-11-21 | 2014-06-12 | Comtech Ef Data Corp. | System and method for satellite link budget analysis (lba) optimization |
| CN103929232A (en) * | 2014-04-23 | 2014-07-16 | 西安电子科技大学 | Broadband mobile communication method and system based on multi-beam GEO satellite |
| CN104133932A (en) * | 2014-05-27 | 2014-11-05 | 中国空间技术研究院 | Satellite overall plan confirmation system based on multidisciplinary optimization and realization method |
| US20160043800A1 (en) * | 2014-08-05 | 2016-02-11 | Ryan Wallace KINGSBURY | Design of a free-space optical communication module for small satellites |
| US20170118729A1 (en) * | 2015-10-27 | 2017-04-27 | The Boeing Company | Satellite Link Budget Command Interface Tool |
| CN106599334A (en) * | 2016-09-19 | 2017-04-26 | 航天东方红卫星有限公司 | Planning method for short-term and effective load work with capability of increasing energy utilization efficiency of satellites |
| CN106950975A (en) * | 2017-01-24 | 2017-07-14 | 上海卫星工程研究所 | Large angle maneuver high-resolution microwave remote sensing satellite overall control method |
| CN106934217A (en) * | 2017-02-16 | 2017-07-07 | 北京空间飞行器总体设计部 | A kind of spacecraft power fast synthesis method and system based on mission program |
| CN107733515A (en) * | 2017-08-31 | 2018-02-23 | 北京空间飞行器总体设计部 | Satellite communication link analysis method under a kind of in-orbit complex environment |
Non-Patent Citations (8)
| Title |
|---|
| KHAN M O等: "Model-based verification and validation of the SMAP uplink processes", 《IEEE》 * |
| 刘波: "新一代极轨气象卫星多星在轨运行通信链路的研究与分析", 《万方数据库》 * |
| 姚保利 等: "高分辨和超分辨光学成像技术在空间和生物中的应用", 《光子学报》 * |
| 张升康等: "卫星双向时间频率传递链路中的功率预算分析", 《宇航计测技术》 * |
| 边志强 等: "遥感卫星高精度高稳定度控制技术", 《上海航天》 * |
| 邵健: "基于MBSE的航天任务分析与设计方法", 《万方数据库》 * |
| 鲁帆等: "Ka频段点波束天线指向精度对星地数传链路的影响分析", 《航天器工程》 * |
| 黄缙等: "一种具备星间链路的中轨对地观测星座设计", 《宇航学报》 * |
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