CN112287467B - Micro-nano satellite energy balance evaluation system and application method thereof - Google Patents
Micro-nano satellite energy balance evaluation system and application method thereof Download PDFInfo
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Abstract
The invention provides a micro-nano satellite energy balance evaluation system and an application method thereof, wherein the energy balance evaluation system comprises: the system comprises a satellite flight orbit simulator, a mission planning computer, a tested micro-nano satellite, a ground power supply program control machine, a solar array simulator and an energy balance evaluation device. According to the method, the energy balance of the micro-nano satellite is evaluated based on satellite physical simulation, the setting of each parameter in the testing process is consistent with the state of the satellite in orbit flight, the energy consumption and supply state of the micro-nano satellite in orbit work can be well simulated, the influence of factors such as attitude and orbit parameters of the satellite, a platform and a load working state on the energy balance of the micro-nano satellite can be reflected by remote measurement parameters, the energy balance state can be comprehensively and accurately evaluated by analyzing the remote measurement parameters, potential risks are eliminated, the use efficiency of the satellite energy is improved, and the potential of the satellite is developed to the maximum extent.
Description
Technical Field
The invention belongs to the technical field of satellite task simulation, and particularly relates to a micro-nano satellite energy balance evaluation system and an application method thereof, which are used for evaluating the micro-nano satellite energy balance state, and are particularly suitable for the evaluation work of low-orbit micro-nano satellite energy balance with complex tasks and frequent and rapid maneuvering postures.
Background
The energy balance state of the micro-nano satellite powered by solar energy is influenced by a plurality of complex factors, and various factors are coupled with each other, so that the energy balance evaluation work is very difficult.
The micro-nano satellite for acquiring solar energy is influenced by various factors: the micro-nano satellite has low orbit and short orbit period, can frequently switch between an illumination area and a ground shadow area during the orbital working period, has large time ratio of the ground shadow area, and limits the utilization of solar energy by the micro-nano satellite due to the factors; in addition, the micro-nano satellite has small volume and light weight, and generally can not carry a large-area solar cell array, so that the solar energy acquisition is greatly limited.
The energy consumption state of the micro-nano satellite is complex and changeable: the micro-nano satellite works on a low orbit, and the requirement on quick maneuvering of the attitude is higher and more frequent. Attitude and orbit control platforms have complex working conditions, which makes satellite energy requirements more difficult to evaluate through modeling.
Accurate evaluation of the energy balance state can help to optimize satellite mission planning, utilize energy to the maximum extent, improve the satellite use efficiency and eliminate potential energy shortage risks.
At present, energy balance evaluation methods are mostly based on digital modeling of various factors influencing energy balance, and energy balance states are evaluated by calculating supply and consumption of energy through model simulation. A remote sensing satellite energy balance constraint analysis system and a method thereof (publication number: CN 106324631A) model a plurality of factors influencing energy balance to obtain a method for evaluating energy balance, but the method does not consider the influence of coupling relation among the factors on energy balance, for example, the voltage of a storage battery is influenced by the charge state of the storage battery, load current, power supply current of a solar battery array, platform, load working time sequence and other factors, and single factor adjustment influences other factors, so that the comprehensive evaluation of the energy balance state in the state is difficult.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the invention provides a micro-nano satellite energy balance evaluation system and an application method thereof, the satellite energy balance is evaluated based on satellite physical simulation, the setting of each parameter in the test process is consistent with the state of a satellite in orbit flight, the energy consumption and supply state of the micro-nano satellite in orbit work can be well simulated, the telemetering parameter reflects the influence of all factors on the energy balance, the balance state of the energy can be comprehensively and accurately evaluated by analyzing the telemetering parameter, the micro-nano satellite energy balance state can be comprehensively evaluated, the potential risk is eliminated, the satellite energy use efficiency is improved, and the potential of the satellite is developed to the maximum extent.
In order to solve the technical problems, the technical scheme adopted by the invention is as follows:
the satellite flight orbit simulator is used for generating satellite flight orbit parameters for testing according to the real orbit parameters of the satellite and the testing time;
the task planning computer is used for setting a platform and a load working time sequence according to the in-orbit working process of the micro-nano satellite according to the satellite orbit parameters and the planning task, generating planning task information and sending the planning task information to the tested micro-nano satellite;
the tested micro-nano satellite is used for executing all test tasks according to the satellite orbit parameters and the planning tasks, outputting the solar cell array orbit and attitude parameters to the ground power supply program control machine in real time and outputting power supply system state remote measurement parameters to the energy balance evaluation device;
the ground power supply program control machine is used for receiving solar cell array orbits and attitude parameters output by the micro-nano satellite in real time in the testing process and controlling the power supply current of the micro-nano satellite in real time according to the solar cell array orbits and the attitude parameters;
the solar array simulator is used for providing energy for the tested micro-nano satellite and is controlled by a ground power supply program controller;
the energy balance evaluation device is used for evaluating the energy balance condition of the micro-nano satellite according to the state remote measurement parameters of the power supply system;
the satellite flight orbit simulator, the mission planning computer, the ground power supply program control machine, the solar array simulator and the energy balance evaluation device are respectively connected with the micro-nano satellite to be tested.
The invention also provides an application method of the micro/nano satellite energy balance evaluation system, which comprises the following steps of carrying out single-orbit periodic energy balance test:
A1) the satellite flight orbit simulator generates satellite orbit parameters for testing according to the input satellite real orbit requirements and the test time;
A2) the task planning computer sets a platform and a load working time sequence according to the on-orbit working process of the tested micro-nano satellite according to the satellite orbit parameters and the planning task, generates planning task information and sends the planning task information to the tested micro-nano satellite;
A3) connecting a storage battery of the tested micro-nano satellite into a test system; the solar array simulator is communicated with a ground power supply program control machine; the ground power supply program control machine establishes communication with an on-board computer of the tested micro-nano satellite; recording the state of charge C of the battery at the start of the test0And the test start time T0；
A4) The system comprises a micro-nano satellite simulation satellite to be tested, a ground power supply program controller, an energy balance evaluation device and a single-orbit period test finishing time T, wherein the micro-nano satellite simulation satellite to be tested works in orbit, the ground power supply program controller receives solar cell array orbit and attitude parameters output by the micro-nano satellite to be tested in real time in the test process, controls the power supply current of the micro-nano satellite in real time according to the solar cell array orbit and attitude parameters, and the energy balance evaluation device records the power supply system state remote measurement parameters returned0+ T State of Charge C of the storage Battery1And a test period [ T0～T0+T]Maximum depth of discharge DOD1 of the internal battery;
A5) determining the state of charge C of the storage battery by the energy balance evaluation device1State of charge C of the battery above the start of the test0And test period [ T0～T0+T]DOD (depth of discharge) of internal storage battery1If the discharge depth is smaller than a preset storage battery DOD, judging that the satellite meets the requirement of single-rail energy balance, ending and exiting; otherwise, skipping to execute the step A1), reducing the task execution time of the satellite or performing the energy balance evaluation test again after adjusting the working time sequence of the satellite.
Optionally, the satellite orbit parameters in the step a 1) include a satellite orbit semi-major axis, eccentricity, inclination, satellite on-orbit position and corresponding time, and sun vector angle.
Optionally, the method further comprises the step of performing a multi-orbital cycle energy balance test:
B1) the flight orbit simulator generates satellite orbit parameters of n orbits for testing according to the input satellite real orbit requirements and the testing time, wherein n is more than or equal to 2 and is a natural number;
B2) the task planning computer sets a platform and a load working time sequence according to the on-orbit working flow of the tested micro-nano satellite according to the satellite orbit parameters and the planning task of the n orbits, generates planning task information of the n orbits and sends the planning task information to the tested micro-nano satellite;
B3) connecting a storage battery of the tested micro-nano satellite into a test system; the solar array simulator is communicated with a ground power supply program control machine; the ground power supply program control machine establishes communication with an on-board computer of the tested micro-nano satellite; recording the state of charge C of the battery at the start of the test0And the test start time T0；
B4) The method comprises the steps that a tested micro-nano satellite simulates the in-orbit work of a satellite, a ground power supply program controller receives the tested micro-nano satellite in the testing process and outputs solar cell array orbit and attitude parameters of an n orbit in real time, the power supply current of the micro-nano satellite is controlled in real time according to the solar cell array orbit and the attitude parameters of the n orbit, and an energy balance evaluation device records the multi-orbit period test ending time T according to the telemetering parameters of the power supply system state returned by the tested micro-nano satellite0+ nT state of charge C of the battery2And a test period [ T0～T0+nT]DOD (depth of discharge) of internal storage battery2；
B5) Determining the state of charge C of the storage battery by the energy balance evaluation device2State of charge C of the battery above the start of the test0And test period [ T0～T0+nT]DOD (depth of discharge) of internal storage battery2If the satellite meets the multi-orbit energy balance requirement, ending and exiting; otherwise, skipping to execute the step B1), reducing the task execution time of the satellite or performing the energy balance evaluation test again after adjusting the working time sequence of the satellite.
Optionally, the satellite orbit parameters in step B1) include the satellite orbit semi-major axis, eccentricity, inclination, satellite on-orbit position and corresponding time, sun vector angle.
Compared with the prior art, the technical scheme of the invention has the following beneficial effects: according to the method, based on the fact that the setting of each parameter in the satellite physical simulation energy balance testing process is consistent with the state of the satellite in orbit flight, the energy consumption and supply state of the micro-nano satellite in orbit can be well simulated, the telemetering parameters reflect the influence of all factors on the energy balance, the balance state of the energy can be comprehensively and accurately evaluated by analyzing the telemetering parameters, the energy balance state of the micro-nano satellite can be comprehensively evaluated, potential risks are eliminated, the use efficiency of the satellite energy is improved, and the potential of the satellite is developed to the maximum extent.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
Fig. 1 is a schematic structural diagram of a micro/nano satellite energy balance evaluation system.
FIG. 2 is a flowchart illustrating a single-track cycle energy balance test performed according to an embodiment of the present invention.
FIG. 3 is a flowchart illustrating a multi-track cycle energy balance test performed according to an embodiment 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 it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention. The method is mainly used for micro-nano satellite energy balance evaluation work of low orbit, frequent change of illumination environment, complex task and frequent maneuvering of posture.
In this embodiment, the tested micro-nano satellite is powered by 4 solar cell arrays in the in-orbit flight process, and the maximum currents output by the solar cell arrays are respectively: the 1 st output current is 3.3A, the 2 nd output current is 3.8A, the 3 rd output current is 5.0A, and the 4 th output current is 5.8A. In the test process of the embodiment of the invention, the solar cell array is replaced by 4 solar cell array simulators to supply power to the satellite, and the maximum output current values of the 4 paths of solar cell array simulators are respectively set to be 3.3A, 3.8A, 5.0A and 5.8A.
In the embodiment of the invention, the normal directions of the solar cell arrays in the 1 st, 2 nd and 3 rd paths are the same as the normal direction of the sun sensor A, and the power supply of the solar array simulators in the 1 st, 2 nd and 3 rd paths is controlled by the sun vector angle of the sun sensor A; the direction of the normal line of the solar cell array in the 4 th path is the same as the normal line of the sun sensor B, and the power supply of the solar array simulator in the 4 th path is controlled by the sun vector angle of the sun sensor B. (the invention does not limit the installation mode of the solar cell array, does not limit the solar vector angle measuring instrument, and can calculate the attitude of the solar cell array through the measurement value of the satellite attitude).
In the embodiment of the invention, the energy balance test period is a single-orbit period, but the energy balance test period is not limited to the single-orbit period and can be a multi-orbit period, and the test period is evaluated according to the energy balance requirement of the satellite.
Step A1), inputting satellite orbit requirements and test time, generating a satellite orbit by an orbit simulator, wherein the orbit period is 5658s, and the duration of the terrestrial shadow area is 2149 s.
In the step A2), according to the generated orbit parameters and the requirement of a camera on the sun altitude of the satellite point, XX minutes and XX seconds are carried out on the satellite task at XX time, the XX place of the satellite point is optically imaged, the imaging time lasts for 6 minutes and 30 seconds, the satellite is in a sun-facing directional working mode at the non-task execution time, and the working time sequence of each platform and load is set according to the task requirement, so that the satellite in the whole testing process is controlled by a computer program.
And step A3), the storage battery is connected into the test system, and the ground power supply program control machine is communicated with the satellite borne computer and the solar array simulator respectively. The satellite flight orbit simulator starts to operate at the initial time T0=16:44:32 (hour: minute: second), state of charge of battery C0And =30Ah, and the DOD requirement of the safety threshold of the discharge depth of the storage battery does not exceed 30%.
In the step A4), the sunlight incident angle theta of the solar cell array is calculated in real time according to the orbit and the attitude parameters of the solar cell array, the sunlight incident angle theta is transmitted to the ground power supply program control machine, and the ground power supply program control machine adjusts the current supply I = I of the solar array simulator to the micro-nano satellite under test in real time according to the sunlight incident angle theta0And (theta) for simulating the energy supply condition of the micro/nano satellite in the real flight process. Wherein, I0The current generated by the solar cell array when the sunlight vertically enters.
In step a 5), in this embodiment, 5 single-track cycle energy balance tests are performed in total, and the test results are as follows:
1 st track cycle end time T1=18:18:49, state of charge of accumulator T1=29.25Ah, minimum charge C of accumulator in orbit cycle1min=25.5 Ah. The charge of the storage battery is reduced by 0.75Ah in the test period, the maximum discharge depth of the storage battery is 15%, the energy production amount in the test period is less than the consumption amount, the energy is unbalanced, and the satellite state can not be continued for a long time.
End time T of 2 nd track cycle1=19:53:08, state of charge of accumulator T1=29.875Ah, minimum charge of accumulator C in orbit cycle2min=25.25 Ah. The charge of the storage battery is increased by 0.625Ah in the test period, the maximum discharge depth of the storage battery is 15.8%, the energy production amount is larger than the consumption amount in the test period, and the energy is balanced.
End time T of 3 rd track cycle1=21:27:27, state of charge of accumulator T1=29.875Ah, minimum charge of accumulator C in orbit cycle3min=25.625 Ah. The charge of the storage battery is not changed in the test period, the maximum discharge depth of the storage battery is 14.6%, the energy generation amount in the test period is equal to the consumption amount, and the energy is balanced.
End time T of 4 th track cycle1=23:01:44, state of charge of accumulator T1=29.75Ah, minimum charge C of accumulator in orbit cycle4min=25.5 Ah. The charge of the storage battery is reduced by 0.125Ah in the test period, the maximum discharge depth of the storage battery is 15 percent, the energy production amount in the test period is less than the consumption amount, the energy is unbalanced,this state of the satellite cannot last for a long time.
The energy balance evaluation method provided by the invention is based on satellite physical simulation, the setting of each parameter in the energy balance test process is consistent with the state of the satellite in orbit flight, the energy consumption and supply state of the micro-nano satellite in orbit can be well simulated, and the telemetering parameter reflects the influence of all factors on the energy balance. By analyzing related telemetering parameters in the test process, the energy balance condition of the micro-nano satellite can be comprehensively evaluated, and potential risks are eliminated.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention, and all modifications and equivalents of the present invention, which are made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (5)
1. A micro-nano satellite energy balance evaluation system is characterized by comprising:
the satellite flight orbit simulator is used for generating satellite flight orbit parameters for testing according to the real orbit parameters of the satellite and the testing time;
the task planning computer is used for setting a platform and a load working time sequence according to the in-orbit working process of the micro-nano satellite according to the satellite orbit parameters and the planning task, generating planning task information and sending the planning task information to the tested micro-nano satellite;
the tested micro-nano satellite is used for executing all test tasks according to the satellite orbit parameters and the planning tasks, outputting the solar cell array orbit and attitude parameters to the ground power supply program control machine in real time and outputting power supply system state remote measurement parameters to the energy balance evaluation device;
the ground power supply program control machine is used for receiving solar cell array orbits and attitude parameters output by the micro-nano satellite in real time in the testing process and controlling the power supply current of the micro-nano satellite in real time according to the solar cell array orbits and the attitude parameters;
the solar array simulator is used for providing energy for the tested micro-nano satellite and is controlled by a ground power supply program controller;
the energy balance evaluation device is used for evaluating the energy balance condition of the micro-nano satellite according to the state remote measurement parameters of the power supply system;
the satellite flight orbit simulator, the mission planning computer, the ground power supply program control machine, the solar array simulator and the energy balance evaluation device are respectively connected with the micro-nano satellite to be tested.
2. An application method of the micro-nano satellite energy balance evaluation system according to claim 1, characterized by comprising the following steps of carrying out single-orbit period energy balance test:
A1) the satellite flight orbit simulator generates satellite orbit parameters for testing according to the input satellite real orbit requirements and the test time;
A2) the task planning computer sets a platform and a load working time sequence according to the on-orbit working process of the tested micro-nano satellite according to the satellite orbit parameters and the planning task, generates planning task information and sends the planning task information to the tested micro-nano satellite;
A3) connecting a storage battery of the tested micro-nano satellite into a test system; the solar array simulator is communicated with a ground power supply program control machine; the ground power supply program control machine establishes communication with an on-board computer of the tested micro-nano satellite; recording the state of charge C of the battery at the start of the test0And the test start time T0；
A4) The system comprises a micro-nano satellite simulation satellite to be tested, a ground power supply program controller, an energy balance evaluation device and a single-orbit period test finishing time T, wherein the micro-nano satellite simulation satellite to be tested works in orbit, the ground power supply program controller receives solar cell array orbit and attitude parameters output by the micro-nano satellite to be tested in real time in the test process, controls the power supply current of the micro-nano satellite in real time according to the solar cell array orbit and attitude parameters, and the energy balance evaluation device records the power supply system state remote measurement parameters returned0+ T State of Charge C of the storage Battery1And a test period [ T0～T0+T]DOD (depth of discharge) of internal storage battery1；
A5) Determining the state of charge C of the storage battery by the energy balance evaluation device1State of charge C of the battery above the start of the test0And test period [ T0～T0+T]DOD (depth of discharge) of internal storage battery1If the discharge depth is smaller than a preset storage battery DOD, judging that the satellite meets the requirement of single-rail energy balance, ending and exiting; otherwise, skipping to execute the step A1), reducing the task execution time of the satellite or performing the energy balance evaluation test again after adjusting the working time sequence of the satellite.
3. The application method of the micro-nano satellite energy balance evaluation system according to claim 2, wherein the satellite orbit parameters in the step A1) comprise a satellite orbit semi-major axis, eccentricity, inclination, satellite on-orbit position and corresponding time, and sun vector angle.
4. The application method of the micro-nano satellite energy balance evaluation system according to claim 2, further comprising the step of performing multi-orbital cycle energy balance test:
B1) the flight orbit simulator generates satellite orbit parameters of n orbits for testing according to the input satellite real orbit requirements and the testing time, wherein n is more than or equal to 2 and is a natural number;
B2) the task planning computer sets a platform and a load working time sequence according to the on-orbit working flow of the tested micro-nano satellite according to the satellite orbit parameters and the planning task of the n orbits, generates planning task information of the n orbits and sends the planning task information to the tested micro-nano satellite;
B3) connecting a storage battery of the tested micro-nano satellite into a test system; the solar array simulator is communicated with a ground power supply program control machine; the ground power supply program control machine establishes communication with an on-board computer of the tested micro-nano satellite; recording the state of charge C of the battery at the start of the test0And the test start time T0；
B4) The tested micro-nano satellite simulates the on-orbit work of a satellite, the ground power supply program control machine receives the solar cell array orbit and the attitude parameter of the tested micro-nano satellite real-time output n orbits in the testing process and outputs the solar cell array orbit and the attitude parameter according to the solar cell array orbit of the n orbitsThe track and attitude parameters control the power supply current of the micro-nano satellite in real time, and the energy balance evaluation device records the multi-orbit period test ending time T according to the telemetering parameters of the power supply system state returned by the tested micro-nano satellite0+ nT state of charge C of the battery2And a test period [ T0～T0+nT]DOD (depth of discharge) of internal storage battery2；
B5) Determining the state of charge C of the storage battery by the energy balance evaluation device2State of charge C of the battery above the start of the test0And test period [ T0～T0+nT]DOD (depth of discharge) of internal storage battery2If the satellite meets the multi-orbit energy balance requirement, ending and exiting; otherwise, skipping to execute the step B1), reducing the task execution time of the satellite or performing the energy balance evaluation test again after adjusting the working time sequence of the satellite.
5. The application method of the micro-nano satellite energy balance evaluation system according to claim 4, wherein the satellite orbit parameters in the step B1) comprise a satellite orbit semi-major axis, eccentricity, inclination, satellite on-orbit position and corresponding time, and sun vector angle.
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| CN202011542792.7A CN112287467B (en) | 2020-12-24 | 2020-12-24 | Micro-nano satellite energy balance evaluation system and application method thereof |
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