CN108460218B - Power consumption budget and energy balance analysis method for optical imaging type small satellite - Google Patents
Power consumption budget and energy balance analysis method for optical imaging type small satellite Download PDFInfo
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Abstract
The invention provides an optical imaging type small satellite power consumption budget and energy balance analysis method, which comprises the steps of firstly combining the use requirements of users, and calculating the satellite power consumption value in a single working mode in a user-defined manner; then, according to the satellite working mode, reasonably considering the power consumption value according to the single-track working state, and calculating the total single-track power consumption of the satellite; according to the model selection and design allowance of different cell arrays, calculating solar cell array parameters meeting the energy balance requirement, wherein the solar cell array parameters comprise solar cell array single-rail minimum energy, solar cell array minimum power, solar cell array minimum effective area, solar cell array minimum design area, solar cell array design area after considering the allowance, solar cell array effective area after considering the allowance, solar cell array power after considering the allowance and solar cell array single-rail energy after considering the allowance; and finally, calculating the energy requirement of the lithium battery pack, and performing battery type selection. The method combines the actual use mode of the satellite and reasonably completes the analysis of the energy satisfaction degree of the whole satellite.
Description
Technical Field
The invention relates to the field of spacecraft design, in particular to a power consumption budget and energy balance analysis method for an optical imaging type small satellite.
Background
The analysis of the power consumption budget and the energy balance of the satellite is a very important ring in the overall design of the satellite, and determines whether the design of a satellite energy system can meet the use requirement. The power consumption budget and energy balance analysis relates to the power requirements of the satellite, the satellite orbit parameters (illumination conditions), the working mode of the satellite, the mission planning of the payload, and the like. In the overall design stage of the satellite, according to different satellite mission missions, functions and use requirements, a lot of uncertainties exist in power consumption budget and energy balance analysis, so that a standard power consumption budget and energy balance analysis method of the satellite is difficult to provide, and therefore, the publication of the aspect is few.
Disclosure of Invention
Aiming at the technical characteristics of the optical imaging type small satellite and combining with practical engineering experience, the invention provides an optical imaging type small satellite power consumption budget and energy balance analysis method which can be directly used in the overall design stage of the optical imaging type small satellite and provides reference for satellite engineering designers.
In order to achieve the purpose, the invention adopts the following technical scheme:
an optical imaging type small satellite power consumption budget and energy balance analysis method comprises the following steps:
firstly, budgeting the power consumption of a satellite;
giving an optical imaging type small satellite to be designed, and giving the orbit period T of the satellite according to the design task requirement0. For a given optical imaging type small satellite, a user self-defines various working modes of the satellite, and defines the working states of energy consumption equipment on the satellite and the working time of the satellite in each single working mode under the various working modes. And then, according to various working modes of the satellite input by a user and the working time of the satellite in each single working mode, calculating and outputting satellite power consumption values of the satellite in each single working mode, wherein the satellite power consumption values comprise steady-state constant power consumption, peak power consumption, user-defined satellite power consumption and single-track total power consumption of the satellite.
(1) Calculating a satellite power consumption value in a single working mode;
the optical imaging small satellite to be designed comprises N energy consumption devices and any satellite working mode defined by a userThen, the number of the various energy consumption devices participating in the work of the satellite is assumed to be xiThe power consumption of each type of energy consumption equipment is pi(unit: W), then the satellite power consumption P (unit: W) in the single operating mode is:
P＝∑xi·pi，i∈[1,N] (1)
it should be noted that, in any satellite operating mode, the operating state of each energy consumption device of the satellite is set by a user, and the power consumption of each energy consumption device of the satellite is determined by the user.
Selecting a satellite power consumption value corresponding to the satellite working mode with the longest working time from all satellite working modes defined by a user, and assuming that the satellite power consumption value is PwAs steady state constant power consumption. Selecting a satellite power consumption value corresponding to the satellite working mode with the maximum power consumption, and assuming that the satellite power consumption value is PfAs peak power consumption. In other satellite working modes defined by the user, outputting the corresponding power consumption P according to the names of the other satellite working modes defined by the userj。
(2) Calculating the total energy consumption of the single track of the satellite;
the total energy consumption of the single track of the satellite is determined according to a user-defined satellite working mode and according to an orbit period T0And carrying out statistical calculation on power consumption values corresponding to different working modes of the internal satellite. If in one track period T0And a plurality of working modes (two or more working modes) exist simultaneously during a certain time period, and the satellite working mode corresponding to the maximum accumulated energy consumption is selected in the time period to calculate the total energy consumption of the satellite monorail.
One track period T0In the method, the working time of the satellite in a plurality of different working modes is assumed to be tj(unit: s),. sigma.tj＝T0In one track period T0The power consumption of the internal satellite in various different working modes is PiThen the total energy consumption E (unit: Wh) of the single track of the satellite is:
Ew＝∑(tj/3600)·Pj，j∈[1,n] (2)
wherein n is the satellite in one orbitPeriod T0The number of internal operating modes.
Secondly, analyzing the energy balance of the satellite and analyzing a power supply system; the method comprises the steps of calculating solar cell array single-rail energy, solar cell array power, solar cell array effective area, solar cell array design area and energy requirements of storage batteries, and carrying out corresponding type selection on the solar cell array and the storage batteries.
Assuming that the average sun exposure time of the satellite is known to be Ts(unit s), total energy consumption of single track of satellite Ew(unit Wh) (total energy consumption of satellite monorail calculated in the first step).
Assuming percent electrical-to-chemical conversion efficiency as ηdhDefault to 90%;
the percent of the photoelectric conversion efficiency is etagdDefault to 90%;
designing a solar cell array model selection:
two solar cell array types are designed here for the user to choose: first, triple junction GaAs with a cell array efficiency percentage of ηpThe efficiency defaults to 27%. Second, silicon, with a cell array efficiency percentage of ηpDefault 14%.
The solar energy density Q is 1353.0W/m2；
Designing an energy margin percentage x, wherein a user can define the energy margin percentage x by default to be 50%;
percentage of efficiency eta of battery array sheet distributionbThe user can define the method by default, and the default is 80%;
percentage of battery discharge efficiency etacDefault to 90%;
percentage η of battery depth of dischargedThe user can customize the device to default to 30%.
Then there are:
solar cell array single-rail minimum energy Ep(unit Wh) is:
Ep＝Ew/ηdh/ηgd (3)
minimum power P of solar cell arrayp(unit W) is:
Pp＝Ep/(Ts/3600) (4)
minimum effective area S of solar cell arrayE(unit m)2) Comprises the following steps:
SE＝Pp/ηp/Q (5)
minimum design area S of solar cell arrayd(unit m)2) Comprises the following steps:
Sd＝SE/ηb (6)
solar cell array design area S after allowance is consideredd2(unit m)2) Comprises the following steps:
Sd2＝Sd·(1+x) (7)
the effective area S of the solar cell array after considering the allowanceE2(unit m)2) Comprises the following steps:
SE2＝Sd2·ηb (8)
solar cell array power P after allowance is consideredp2(unit W) is:
Pp2＝SE2·ηp·Q (9)
solar cell array single-rail energy E after allowance is consideredp2(unit Wh) is:
Ep2＝Pp2·(Ts/3600) (10)
energy requirement E of lithium battery packb(unit Wh) is:
Eb＝Ew/ηc/ηd (11)
the storage battery type selection can be carried out by a user according to the bus voltage V (the user can define) and the energy requirement E of the lithium battery packbOutput capacity E of the battery packbAnd the model/V (rounding) is the proper storage battery model, and the model selection is carried out according to the first gear of every 10 Ah.
Compared with the prior art, the invention has the following beneficial technical effects:
the invention provides an analysis method and a process of the energy system satisfaction degree in the overall scheme design stage of an optical imaging type small satellite. The method combines the characteristics and task modes of the optical imaging satellite, establishes a mathematical model of power consumption budget and energy balance analysis, and quantitatively describes a satellite energy balance analysis and power system analysis method. The method is clear, correct and reasonable in order, can provide design basis for global satellite designers and power subsystem designers, and has good application prospect in the field of satellite design and development.
Drawings
FIG. 1 is a flow chart of the present invention
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and further detailed description will be given, but the embodiments of the present invention are not limited thereto.
Referring to fig. 1, a flow chart of the present invention is shown. The satellite energy balance aims at performing task operation on a single station and a single rail, and consumed electric energy can realize energy balance in the single rail. Starting from the characteristics of the optical imaging type small satellite, the method firstly combines the use requirements of users to self-define and calculate the power consumption value of the satellite in a single working mode; then, according to the satellite working mode, reasonably considering the power consumption value (including a full load mode) according to the single-track working state, and calculating the total power consumption of the single track of the satellite; according to the model selection and design allowance of different cell arrays, calculating solar cell array parameters meeting the energy balance requirement, wherein the solar cell array parameters comprise solar cell array single-rail minimum energy, solar cell array minimum power, solar cell array minimum effective area, solar cell array minimum design area, solar cell array design area after considering the allowance, solar cell array effective area after considering the allowance, solar cell array power after considering the allowance and solar cell array single-rail energy after considering the allowance; and finally, calculating the energy requirement of the lithium battery pack, and performing battery type selection. The method combines the actual use mode of the satellite and reasonably completes the analysis of the energy satisfaction degree of the whole satellite. The practical engineering application proves that the method has the advantages of progressive and clear design steps, correct and reasonable result and high design speed, and can lay a solid foundation for the overall design of the satellite.
The invention will be further described with reference to specific embodiments:
firstly, budgeting the power consumption of a satellite;
according to the method in the first step of the optical imaging type small satellite power consumption budget and energy balance analysis method provided by the invention, the satellite power consumption in the embodiment is counted as shown in the following table:
TABLE 1 Power consumption Allocation Table
As can be seen from table 1, each energy consumption device of the satellite includes devices in a power management subsystem, an integrated information management subsystem, an attitude control subsystem, a load subsystem, a data transmission subsystem, and a thermal control subsystem. The user-defined satellite working modes comprise a standby mode, a preparation mode, an autonomous video staring imaging mode, a data downloading mode and a human-in-loop video staring imaging mode.
The distribution of the satellite operating mode and the average power consumption over time is shown in table 2. Within a task operating window, calculated as autonomous video gaze imaging and data download as 5 minutes, human on-loop video gaze imaging as 3 minutes, and task preparation as 1 minute. Therefore, according to the actual working mode of the satellite, the satellite working mode corresponding to the maximum satellite power consumption value in the satellite standby mode (namely the ground station non-controllable section), the task preparation mode and the task stage is selected to calculate the single-track total energy consumption of the satellite. Referring to table 2, in the task phase, the satellite working mode corresponding to the maximum satellite power consumption value among the three modes of the autonomous video staring imaging mode, the data downloading mode and the loop video staring imaging mode of the person is the autonomous video staring imaging mode, so that the accumulated energy consumption corresponding to the autonomous video staring imaging mode during the task period is calculated, and the maximum energy consumption in the monorail is 244 Wh.
TABLE 2 satellite Power consumption distribution over time
| Item | Power consumption (W) | Time(s) | Cumulative energy consumption (Wh) |
| Ready for use | 128.8 | 5356 | 191.6 |
| Preparation of | 465.6 | 60 | 7.76 |
| Autonomous video staring imaging | 535.8 | 300 | 44.65 |
| Data download | 382.8 | 300 | 31.9 |
| Human-in-loop video staring imaging | 722.8 | 180 | 36.14 |
| Full cycle of satellite operation | —— | 5716 | Maximum 244.01 |
Taking the maximum of the three energy consumption states, the main array of solar cells should generate 244Wh of energy during the single-rail exposure period.
Second, analysis of energy balance and power system analysis of satellite
According to the method in the second step of the optical imaging type small satellite power consumption budget and energy balance analysis method provided by the invention and the single-track total energy consumption 244Wh obtained by the previous calculation, the energy balance analysis and the power system analysis are carried out, and the results are shown in the following table:
TABLE 3 satellite energy balance budget
According to the satellite power supply design result, the energy balance of the single track can be realized under the full-load working mode under the normal working state of the solar cell main array.
In summary, although the present invention has been described with reference to the preferred embodiments, it should be understood that various changes and modifications can be made by those skilled in the art without departing from the spirit and scope of the invention.
Claims (5)
1. An optical imaging type small satellite power consumption budget and energy balance analysis method is characterized by comprising the following steps:
firstly, budgeting the power consumption of a satellite;
giving an optical imaging type small satellite to be designed, and giving the orbit period T of the satellite according to the design task requirement0(ii) a Aiming at a given optical imaging type small satellite, a user self-defines various working modes of the satellite, and defines the working states of energy consumption equipment on the satellite and the working time of the satellite in each single working mode under the various working modes; followed by satellite according to user inputCalculating and outputting satellite power consumption values of the satellite in various working modes of the satellite, including steady-state constant power consumption, peak power consumption, user-defined satellite power consumption and single-track total power consumption of the satellite; selecting a satellite power consumption value corresponding to the satellite working mode with the longest working time from all satellite working modes defined by a user, and assuming that the satellite power consumption value is PwAs steady state constant power consumption;
secondly, analyzing the energy balance of the satellite and analyzing a power system; calculating the solar cell array single-rail energy, the solar cell array power, the solar cell array effective area, the solar cell array design area and the energy requirement of a storage battery, and performing corresponding type selection of the solar cell array and the storage battery;
let the average exposure time of the known satellite be TsPercentage of electric-to-chemical conversion efficiency is ηdhThe percent of the photoelectric conversion efficiency is etagdThe percentage of efficiency of the solar cell array is etapSolar energy density Q, energy margin percentage x, cell array sheet distribution efficiency percentage etabPercentage of battery discharge efficiency ηcPercentage of depth of discharge η of the storage batteryd；
Then there are:
solar cell array single-rail minimum energy EpComprises the following steps:
Ep＝Ew/ηdh/ηgd (3)
minimum power P of solar cell arraypComprises the following steps:
Pp＝Ep/(Ts/3600) (4)
minimum effective area S of solar cell arrayEComprises the following steps:
SE＝Pp/ηp/Q (5)
minimum design area S of solar cell arraydComprises the following steps:
Sd＝SE/ηb (6)
solar cell array design area S after allowance is consideredd2Comprises the following steps:
Sd2＝Sd·(1+x) (7)
the effective area S of the solar cell array after considering the allowanceE2Comprises the following steps:
SE2＝Sd2·ηb (8)
solar cell array power P after allowance is consideredp2Comprises the following steps:
Pp2＝SE2·ηp·Q (9)
solar cell array single-rail energy E after allowance is consideredp2Comprises the following steps:
Ep2＝Pp2·(Ts/3600) (10)
energy requirement E of lithium battery packbComprises the following steps:
Eb＝Ew/ηc/ηd (11)
wherein EwThe single-track total energy consumption of the satellite is achieved;
the storage battery is selected by a user according to the bus voltage V and the energy requirement E of the lithium battery packbTo capacity E of the output battery packbAnd the model selection is carried out according to one gear of every 10 Ah.
2. The method for analyzing power budget and energy balance of an optical imaging microsatellite according to claim 1, wherein: in the first step of the process,
(1) calculating a satellite power consumption value in a single working mode;
under any satellite working mode defined by a user, the number of various energy consumption devices of the satellite participating in the work is assumed to be xiThe power consumption of each type of energy consumption equipment is piThen, the satellite power consumption P in the single operating mode is:
P＝∑xi·pi，i∈[1,N] (1)
wherein N is the number of types of energy consuming equipment;
selecting a satellite power consumption value corresponding to the satellite working mode with the maximum power consumption, and assuming that the satellite power consumption value is PfAs peak power consumption;
in other user-defined satellite working modes, according to user self-definitionThe names of other satellite working modes output the power consumption P of various energy consumption equipment of the corresponding satellitej；
(2) Calculating the total energy consumption of the single track of the satellite;
the total energy consumption of the single track of the satellite is determined according to a user-defined satellite working mode and according to an orbit period T0Carrying out statistical calculation on power consumption values corresponding to different working modes of the internal satellite; if in one track period T0If a plurality of working modes exist in a certain time period, selecting the satellite working mode corresponding to the maximum accumulated energy consumption in the time period to calculate the total energy consumption of the single track of the satellite;
in one track period T0In the method, the working time of the satellite in a plurality of different working modes is assumed to be tj，∑tj＝T0Then the total energy consumption of the single track of the satellite is:
Ew＝∑(tj/3600)·Pj，j∈[1,n] (2)
where n is the satellite in one orbital period T0The number of internal operating modes.
3. The method for analyzing power budget and energy balance of an optical imaging microsatellite according to claim 1, wherein: in the second step, the percentage of electric-to-chemical conversion efficiency etadhIs 90%; percent photoelectric conversion efficiency ηgdIs 90%; the solar energy density Q is 1353.0W/m2The energy margin percentage x is 50%; percentage of efficiency eta of battery array sheet distributionb80 percent; percentage of battery discharge efficiency etacIs 90%; percentage η of battery depth of dischargedThe content was 30%.
4. The optical imaging microsatellite power consumption budget and energy balance analysis method as set forth in claim 2 or 3 wherein: in the second step, the solar cell array is a three-junction gallium arsenide solar cell array, and the efficiency percentage eta of the solar cell array ispThe content was 27%.
5. According to claim 2 or 3The method for analyzing the power consumption budget and the energy balance of the optical imaging type small satellite is characterized by comprising the following steps of: in the second step, the solar cell array is a silicon solar cell array, and the efficiency percentage eta of the solar cell array ispThe content was 14%.
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