阅读说明：本技术 高轨卫星阴影期能源紧张自主应对方法及系统 (Autonomous coping method and system for energy shortage in shadow period of high-orbit satellite ) 是由 陈占胜 陈双全 陈华 孙伟 赵吉喆 田敏 黄小虎 顾燕萍 王志国 袁双 于 2021-08-19 设计创作，主要内容包括：本发明提供一种高轨卫星阴影期能源紧张自主应对方法及系统,涉及空间飞行器技术领域,包括：步骤S1：星上自主阴影期预报；步骤S2：计算阴影期蓄电池最大放电深度；步骤S3：阴影期能源决策；步骤S4：自主生成程控延时控制指令；步骤S5：自主执行卫星进阴影前策略；步骤S6：自主执行卫星进阴影后策略；步骤S7：自主监测阴影期能源并根据状态进行应对；步骤S8：卫星出影后执行出影后整星策略,切回正常输出模式,阴影期前后全程智能化完成阴影期能源自主管理。本发明能降低阴影期能源紧张时蓄电池最大放电深度,减少卫星因能源紧张导致功能受限的影响程度,提高阴影期能源安全性,提升高轨卫星自主应对阴影期能源紧张的智能化水平。(The invention provides an autonomous energy tension responding method and system for a shadow period of a high-orbit satellite, which relate to the technical field of space vehicles and comprise the following steps: step S1: forecasting an on-satellite autonomous shadow period; step S2: calculating the maximum discharge depth of the storage battery in the shadow period; step S3: making a shadow period energy decision; step S4: autonomously generating a program control delay control instruction; step S5: autonomously executing a pre-shadow strategy of the satellite; step S6: autonomously executing a strategy after the satellite enters the shadow; step S7: autonomously monitoring the energy in the shadow period and responding according to the state; step S8: and executing a post-shadow whole-satellite strategy after the satellite is shadowed, switching back to a normal output mode, and intelligently completing the autonomous energy management in the shadow period in the whole process before and after the shadow period. The invention can reduce the maximum discharge depth of the storage battery when the energy is in tension in the shadow period, reduce the influence degree of the satellite on function limitation caused by the energy tension, improve the energy safety in the shadow period and improve the intelligent level of the high-orbit satellite for autonomously coping with the energy tension in the shadow period.)

1. An autonomous energy stress responding method for a shadow period of a high-orbit satellite is characterized by comprising the following steps:

step S1: forecasting the time and the total duration of the satellite in and out of the shadow period by the on-board computer;

step S2: calculating the maximum discharge depth of the storage battery in the shadow period according to the forecast content;

step S3: according to the maximum discharge depth result of the satellite storage battery in the shadow period, a targeted shadow period energy source corresponding strategy is made;

step S4: a satellite counting computer autonomously generates a program control delay control instruction;

step S5: a satellite counting computer autonomously executes a strategy before the satellite performs shadow entering;

step S6: a satellite counting computer autonomously executes a strategy after the satellite enters the shadow;

step S7: a satellite counting computer automatically monitors the energy in the shadow period and responds according to the state;

step S8: and executing a post-shadow whole-satellite strategy after the satellite is shadowed, switching back to a normal output mode, and intelligently completing the autonomous energy management in the shadow period in the whole process before and after the shadow period.

2. The method according to claim 1, wherein the step S1 includes: and (3) forecasting the autonomous shadow period on the satellite, wherein the on-satellite computer forecasts the time when the satellite enters and exits the shadow period and the total duration of the shadow period through real-time orbit data of the sun, the earth, the moon and the satellite, and the forecasting error is less than 2 minutes.

3. The method according to claim 1, wherein the step S3 includes:

when the maximum discharge depth of the storage battery is between a normal threshold and a safety threshold, the satellite is in an energy tension state, and an energy tension coping strategy is executed;

executing a normal mode when the maximum discharge depth of the storage battery is between a normal threshold value and a protection threshold value;

when the maximum discharge depth of the storage battery is between the protection threshold and the limit threshold, executing a whole-satellite synchronous heating method before shadow entering, a whole-satellite heater temporary strong-closing method during shadow period and a corresponding method for limiting an output mode;

when the maximum discharge depth of the storage battery is between the limited threshold and the safe threshold, executing a whole-satellite synchronous heating method before shadow entering, a whole-satellite temporary strong-closing method during shadow period and a corresponding method of a minimum output mode.

4. The method according to claim 1, wherein the step S4 is implemented by autonomously generating programmed delay control commands, which include autonomously programming satellite operation modes before, after, and after shadow periods, and before and after a single shadow, and a whole satellite heater delay control program.

5. The method according to claim 1, wherein the autonomously performing a pre-shadowing strategy for the satellite in the shadowing period of the high-earth orbit satellite in step S5 comprises: the whole-satellite synchronous heating method before shadow entering comprises the following specific operation modes: within hours in the shadow entering period, implementing a whole satellite heater temporary forced opening instruction for several times at equal time intervals, so that the satellite enters the shadow at the highest temperature of temperature control; and after the satellite enters the shadow, executing a temporary strong closing instruction to reduce the discharge of the storage battery.

6. The method according to claim 1, wherein the autonomously performing the satellite shadow-entering strategy in step S6 comprises: the temporary strong turn-off method of the whole satellite heater in the shadow period comprises the following specific operation modes: and in the shadow period, when the satellite heating current reaches the peak value, a temporary strong turn-off instruction of the satellite heater is carried out once after the set time, so that the discharge of the storage battery is reduced.

7. The method according to claim 1, wherein the energy supply tension in shadow period of the high earth orbit satellite is autonomously monitored and autonomously coped with in step S7, including deep discharge monitoring and cell voltage monitoring of the storage battery;

the storage battery discharge depth monitoring method comprises the step of calculating and solving by a real-time bus voltage, bus current and duration integration method.

8. An autonomous energy stress coping system for a shadow period of a high-orbit satellite is characterized by comprising the following components:

module M1: forecasting the time and the total duration of the satellite in and out of the shadow period by the on-board computer;

module M2: calculating the maximum discharge depth of the storage battery in the shadow period according to the forecast content;

module M3: according to the maximum discharge depth result of the satellite storage battery in the shadow period, a targeted shadow period energy source corresponding strategy is made;

module M4: a satellite counting computer autonomously generates a program control delay control instruction;

module M5: a satellite counting computer autonomously executes a strategy before the satellite performs shadow entering;

module M6: a satellite counting computer autonomously executes a strategy after the satellite enters the shadow;

module M7: a satellite counting computer automatically monitors the energy in the shadow period and responds according to the state;

module M8: and executing a post-shadow whole-satellite strategy after the satellite is shadowed, switching back to a normal output mode, and intelligently completing the autonomous energy management in the shadow period in the whole process before and after the shadow period.

9. The system according to claim 6, wherein the module M1 comprises: and (3) forecasting the autonomous shadow period on the satellite, wherein the on-satellite computer forecasts the time when the satellite enters and exits the shadow period and the total duration of the shadow period through real-time orbit data of the sun, the earth, the moon and the satellite, and the forecasting error is less than 2 minutes.

10. The system according to claim 6, wherein the module M3 comprises:

when the maximum discharge depth of the storage battery is between a normal threshold and a safety threshold, the satellite is in an energy tension state, and an energy tension coping strategy is executed;

executing a normal mode when the maximum discharge depth of the storage battery is between a normal threshold value and a protection threshold value;

when the maximum discharge depth of the storage battery is between the protection threshold and the limit threshold, executing a whole-satellite synchronous heating method before shadow entering, a whole-satellite heater temporary strong-closing method during shadow period and a corresponding method for limiting an output mode;

when the maximum discharge depth of the storage battery is between the limited threshold and the safe threshold, executing a whole-satellite synchronous heating method before shadow entering, a whole-satellite temporary strong-closing method during shadow period and a corresponding method of a minimum output mode.

Technical Field

The invention relates to the technical field of space vehicles, in particular to an autonomous energy tension responding method and system for a shadow period of a high-orbit satellite.

Background

In the shadow period, the satellite cannot obtain energy through a solar cell array, and only can rely on an energy system (usually a storage battery) of the satellite to complete single-machine operation and energy supply of temperature control of the whole satellite. Due to the characteristics of the orbit of the high-orbit satellite, the low-orbit satellite has more complicated in-orbit shadow period, longer duration and larger demand on energy. And the high orbit satellite is restricted by the emission quality, and the design margin of the capacity of the storage battery is smaller. Therefore, the high orbit satellite is more likely to have energy shortage in the shadow period. The energy shortage in the shadow period is an abnormal state of the satellite, the function and the performance of the satellite are limited if the energy shortage is in a light state, the satellite is temporarily disabled in a safe mode if the energy shortage is in a heavy state, and even the satellite is permanently out of control and disabled.

Because the intelligent degree of the satellite is not high, the energy management in the shadow period is generally completed by adopting a ground intervention method aiming at the situation of energy shortage in the shadow period. The implementation procedure of the so-called "ground intervention method" generally includes: the method comprises the steps of satellite real-time energy monitoring, satellite storage battery discharge depth calculation, satellite output mode decision generation, ground programming control instructions, upper injection control instructions and the like. The implementation of the ground intervention method needs a plurality of condition guarantees, for example, the satellite is in a measurable and controllable arc segment, the satellite has on-orbit programming conditions, the operation control system can upload control instructions and emergency instructions in time, and the like, and has extremely high requirements on instantaneity, correctness and effectiveness.

The invention patent with publication number CN111086655A discloses a method and system for saving thermal control compensation power in a non-measurement and control arc segment shadow period, comprising: step 1: determining the states of heaters in the satellite illumination period and the shadow period through thermal simulation; step 2: in the satellite measurement and control arc section, sending a thermal control heater program control prohibition instruction and a thermal control heater state setting instruction according to the state of a heater in an illumination period; and step 3: when the satellite exits the measurement and control arc section and before the satellite enters the non-measurement and control arc section, a delay instruction with a time code is sent according to the shadow time forecast and the shadow period heater state of the non-measurement and control arc section, and the states of the thermal control heaters when the non-measurement and control arc section enters the shadow and exits the shadow are respectively set; and 4, step 4: and after the non-measurement and control arc section is finished and the satellite reenters the measurement and control arc section, sending a program control permission instruction of the thermal control heater, and performing closed-loop control on the heater according to a threshold value. The patent is a 'ground intervention method' for implementing an energy management method in a shadow period, and is different from the scheme in that a non-satellite autonomously completes the energy management method.

The invention patent with publication number CN111064249A discloses a method for autonomous management of operating modes of a medium and high orbit satellite energy system, which comprises the following steps: step 1: defining the working mode of the energy system; adjusting the output mode of the whole satellite energy source according to the working state of the satellite energy source when in shortage; the working modes of the energy system comprise a normal output mode, a limited output mode and a minimum output mode; step 2: determining conversion relation and judgment criterion among the working modes of the energy system; the conversion relationship includes conversion of the normal output mode to the limited output mode, conversion of the limited output mode to the minimum output mode, and conversion of the limited output, the minimum output mode to the normal output mode. This patent only describes the definition of the energy system operating mode and the principle of autonomous management switching, unlike the method described in the present invention.

The invention patent with publication number CN107611504B discloses an on-orbit management method for a lithium ion storage battery pack of a medium and high orbit satellite, which comprises the following steps: step 1: when the medium and high orbit satellite enters a long illumination period, the storage battery pack monomer is stored in a first preset temperature range and a preset charge state SOC 1; step 2: when the medium and high orbit satellite enters N days before the image entering period, the temperature of a single body of the storage battery pack is increased to be within a second preset temperature range, and then the storage battery pack is charged to the final charging voltage of the storage battery pack in the image entering period; and step 3: when the medium and high orbit satellite enters the earth shadow period, maintaining the temperature of the single storage battery pack within a second preset temperature range; and (5) executing the step 1 after the shadow is generated. According to the patent, the lithium ion storage battery pack adopts low-temperature low-charge state storage in a long illumination period, the charging final voltage of the storage battery pack is gradually increased during a ground shadow period, the capacity attenuation of the storage battery pack is reduced, and the service life of the storage battery pack is prolonged. The content of the patent belongs to single-machine level autonomous management, and is different from the satellite system level autonomous management of the scheme.

The patent of the invention with the publication number of CN104821894B discloses an on-orbit autonomous management system and an autonomous management method for a satellite, and the patent improves the satellite data acquisition efficiency and intelligent fault processing and data recovery by introducing a bus data monitoring unit and using a distributed data management method, and is unrelated to satellite energy management and different from the scheme.

The invention patent with publication number CN112528488A discloses a method and a system for saving satellite shadow period thermal compensation power consumption based on heat capacity difference, comprising the following steps: modeling: establishing a thermal simulation model of the satellite to obtain a time-varying temperature curve of each electronic device; and (3) correcting: correcting the heat capacity parameters of each electronic device through a thermal balance test; a first calculation step: calculating the temperature change rate of the electronic equipment according to the temperature change curve of the electronic equipment; a determination step: determining the starting time of the thermal compensation heater before the shadow according to the temperature change curve of the electronic equipment; closing: turning off the thermal compensation heater one minute before the satellite enters the shadow period; a second calculation step: calculating the shutdown time of the heater in the shadow period; and (4) upper injection step: and designing a delay instruction according to the starting-up time and the shutdown time of the heater and uploading.

Disclosure of Invention

Aiming at the defects in the prior art, the invention provides an autonomous energy tension responding method and system for a shadow period of a high-orbit satellite.

According to the autonomous energy tension responding method and system for the shadow period of the high orbit satellite, the scheme is as follows:

in a first aspect, a method for autonomous energy stress response during a shadow period of a high-orbit satellite is provided, the method including:

step S1: forecasting the time and the total duration of the satellite in and out of the shadow period by the on-board computer;

step S2: calculating the maximum discharge depth of the storage battery in the shadow period according to the forecast content;

step S3: according to the maximum discharge depth result of the satellite storage battery in the shadow period, a targeted shadow period energy source corresponding strategy is made;

step S4: a satellite counting computer autonomously generates a program control delay control instruction;

step S5: a satellite counting computer autonomously executes a strategy before the satellite performs shadow entering;

step S6: a satellite counting computer autonomously executes a strategy after the satellite enters the shadow;

step S7: a satellite counting computer automatically monitors the energy in the shadow period and responds according to the state;

step S8: and executing a post-shadow whole-satellite strategy after the satellite is shadowed, switching back to a normal output mode, and intelligently completing the autonomous energy management in the shadow period in the whole process before and after the shadow period.

Preferably, the step S1 includes: and (3) forecasting the autonomous shadow period on the satellite, wherein the on-satellite computer forecasts the time when the satellite enters and exits the shadow period and the total duration of the shadow period through real-time orbit data of the sun, the earth, the moon and the satellite, and the forecasting error is less than 2 minutes.

Preferably, the step S3 includes:

when the maximum discharge depth of the storage battery is between a normal threshold and a safety threshold, the satellite is in an energy tension state, and an energy tension coping strategy is executed;

executing a normal mode when the maximum discharge depth of the storage battery is between a normal threshold value and a protection threshold value;

when the maximum discharge depth of the storage battery is between the protection threshold and the limit threshold, executing a whole-satellite synchronous heating method before shadow entering, a whole-satellite heater temporary strong-closing method during shadow period and a corresponding method for limiting an output mode;

when the maximum discharge depth of the storage battery is between the limited threshold and the safe threshold, executing a whole-satellite synchronous heating method before shadow entering, a whole-satellite temporary strong-closing method during shadow period and a corresponding method of a minimum output mode.

Preferably, the step S4 is to autonomously generate the programmed delay control command, including the satellite autonomously programming the satellite operating mode before and after the shadow entering, and the shadow period, and before and after the single shadow after the shadow exiting, and the whole satellite heater delay control program.

Preferably, the autonomously executing the satellite pre-shadow strategy in step S5 includes: the whole-satellite synchronous heating method before shadow entering comprises the following specific operation modes: within hours in the shadow entering period, implementing a whole satellite heater temporary forced opening instruction for several times at equal time intervals, so that the satellite enters the shadow at the highest temperature of temperature control; and after the satellite enters the shadow, executing a temporary strong closing instruction to reduce the discharge of the storage battery.

Preferably, the autonomously executing the satellite shadow-entering strategy in step S6 includes: the temporary strong turn-off method of the whole satellite heater in the shadow period comprises the following specific operation modes: and in the shadow period, when the satellite heating current reaches the peak value, a temporary strong turn-off instruction of the satellite heater is carried out once after the set time, so that the discharge of the storage battery is reduced.

Preferably, in step S7, the energy state in the shadow period is autonomously monitored and autonomously responded, including monitoring the depth of discharge of the storage battery and monitoring the cell voltage;

the storage battery discharge depth monitoring method comprises the step of calculating and solving by a real-time bus voltage, bus current and duration integration method.

In a second aspect, an autonomous energy stress coping system for shadow periods of high-orbit satellites is provided, the system comprising:

module M1: forecasting the time and the total duration of the satellite in and out of the shadow period by the on-board computer;

module M2: calculating the maximum discharge depth of the storage battery in the shadow period according to the forecast content;

module M3: according to the maximum discharge depth result of the satellite storage battery in the shadow period, a targeted shadow period energy source corresponding strategy is made;

module M4: a satellite counting computer autonomously generates a program control delay control instruction;

module M5: a satellite counting computer autonomously executes a strategy before the satellite performs shadow entering;

module M6: a satellite counting computer autonomously executes a strategy after the satellite enters the shadow;

module M7: a satellite counting computer automatically monitors the energy in the shadow period and responds according to the state;

module M8: and executing a post-shadow whole-satellite strategy after the satellite is shadowed, switching back to a normal output mode, and intelligently completing the autonomous energy management in the shadow period in the whole process before and after the shadow period.

Preferably, the module M1 includes: and (3) forecasting the autonomous shadow period on the satellite, wherein the on-satellite computer forecasts the time when the satellite enters and exits the shadow period and the total duration of the shadow period through real-time orbit data of the sun, the earth, the moon and the satellite, and the forecasting error is less than 2 minutes.

Preferably, the module M3 includes:

when the maximum discharge depth of the storage battery is between a normal threshold and a safety threshold, the satellite is in an energy tension state, and an energy tension coping strategy is executed;

executing a normal mode when the maximum discharge depth of the storage battery is between a normal threshold value and a protection threshold value;

when the maximum discharge depth of the storage battery is between the protection threshold and the limit threshold, executing a whole-satellite synchronous heating method before shadow entering, a whole-satellite heater temporary strong-closing method during shadow period and a corresponding method for limiting an output mode;

when the maximum discharge depth of the storage battery is between the limited threshold and the safe threshold, executing a whole-satellite synchronous heating method before shadow entering, a whole-satellite temporary strong-closing method during shadow period and a corresponding method of a minimum output mode.

Compared with the prior art, the invention has the following beneficial effects:

1. the method can autonomously forecast the time when the satellite enters and exits the shadow and the total shadow duration, calculate the maximum discharge depth of the satellite in the shadow period and pertinently specify a coping strategy;

2. the method for synchronously heating the whole satellite before the shadow is carried out and the temporary strong closing method of the whole satellite heater in the shadow period are innovatively provided, so that the requirement of the satellite in the shadow period on energy can be effectively reduced, and the negative influence of energy shortage on the function of the satellite can be reduced to the maximum extent;

3. by autonomously generating and executing a delay control instruction, the energy monitoring and autonomous coping in the shadow period are implemented, and the autonomous coping of energy tension in the shadow period can be realized.

Drawings

Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:

FIG. 1 is a block diagram of the overall structure of the present invention;

fig. 2 is a schematic diagram of a high-orbit satellite energy management method including a "whole-satellite synchronous heating method before shadow entering" and a "whole-satellite heater temporary strong-closing method during shadow period".

Fig. 3 is a schematic diagram illustrating the effect of a method for autonomously dealing with energy supply tension in a shadow period implemented by a certain high-orbit satellite.

Detailed Description

The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.

The embodiment of the invention provides an autonomous energy tension responding method for a shadow period of a high-orbit satellite, which specifically comprises the following steps of:

step S1: and (3) forecasting the autonomous shadow period on the satellite, wherein the on-satellite computer forecasts the time when the satellite enters and exits the shadow period and the total duration of the shadow period through real-time orbit data of the sun, the earth, the moon and the satellite, and the forecasting error is less than 2 minutes.

Step S2: both this step and step S3 include an iterative calculation process. And performing shadow period energy calculation by using the current working mode or the established working mode, and calculating the maximum discharge depth of the storage battery pack in the shadow period again by using the working mode with lower power requirement when the maximum discharge depth in the shadow period exceeds a safety threshold.

Step S3: according to the maximum discharge depth result of the satellite storage battery in the shadow period, a targeted shadow period energy source corresponding strategy is made; and when the maximum discharge depth of the storage battery is between the normal threshold and the safety threshold, the satellite is in an energy tension state, and an energy tension coping strategy is executed.

When the maximum discharge depth of the storage battery is between the protection threshold and the limit threshold, executing a corresponding method of a whole star synchronous heating method before shadow entering ' + ' a whole star heater temporary strong turn-off method in the shadow period ' + ' a limit output mode '; when the maximum discharge depth of the storage battery is between a limited threshold and a safe threshold, executing a coping method of a whole star synchronous heating method before shadow entering ' + ' a whole star heater temporary strong turn-off method during shadow period ' + ' a minimum output mode '. The normal mode is executed when the maximum depth of discharge of the battery is between the normal threshold and the protection threshold. Wherein, the normal threshold, i.e. the low discharge threshold, is generally defined as a depth of discharge lower than 40%, the safety threshold is generally defined as a depth of discharge 80%, the protection threshold is generally defined as a depth of discharge 60%, and the limit threshold is generally defined as a depth of discharge 70%.

Step S4: and autonomously generating a program control delay control instruction, wherein the program control delay control instruction comprises a satellite working mode before and after shadow entering, a shadow entering period and a shadow period, and a satellite working mode before and after single shadow after shadow exiting, and a whole satellite heater delay control program.

Step S5: the strategy for autonomously executing the satellite before shadow entering comprises a whole satellite synchronous heating method before shadow entering, and the specific operation mode is as follows: within hours in the shadow entering period, implementing a whole satellite heater temporary forced opening instruction for several times at equal time intervals, so that the satellite enters the shadow at the highest temperature of temperature control; after the satellite enters the shadow, the temporary strong closing instruction is executed, and the discharge of the storage battery is reduced as much as possible.

Step S6: the strategy for automatically executing the shadow of the satellite comprises a temporary strong closing method of a heater of the whole satellite in the shadow period, and the specific operation mode is as follows: in the shadow period, when the satellite heating current reaches the peak value, a satellite heater temporary strong-closing instruction is carried out for a plurality of minutes (more than the temperature acquisition time interval) so as to reduce the discharge of the storage battery.

Step S7: automatically monitoring the energy in the shadow period and responding according to the state, wherein the monitoring comprises the monitoring of the voltage of a single storage battery and the calculation of the discharge depth of the storage battery; the storage battery monomer voltage monitoring is obtained through storage battery monomer voltage telemetering data, the storage battery discharge depth calculation is obtained through inquiring a storage battery monomer voltage and discharge depth characteristic curve table, the storage battery charge-discharge depth calculation method has the characteristics of real-time performance and accuracy, and enough reaction time can be reserved for satellite energy decision.

Step S8: and executing a post-shadow whole-satellite strategy after the satellite is shadowed, switching back to a normal output mode, and intelligently completing the autonomous energy management in the shadow period in the whole process before and after the shadow period.

Next, the present invention will be described in more detail.

The on-orbit energy autonomous management strategy of a certain high-orbit satellite is shown in figure 2, wherein the shadow duration of the satellite from 2 months 26 to 3 months 24 days is 2-72 min, and the satellite covers the shortest shadow period and the longest shadow period. During which shadow period tests are conducted, during which the satellite intentionally adopts a maximum power output mode. With the increase of the shadow period, the energy shortage condition of the shadow period occurs in the satellite. The satellite applies the autonomous coping method for energy shortage in the shadow period, the longest shadow period is safely passed, and the correctness and the effectiveness of the method are checked in an on-orbit mode.

The main implementation is as follows.

(1) Satellite energy management principles and goals:

the shadow period energy strategy takes the principle that the function and the performance of the satellite are not influenced or are influenced as little as possible, and mainly has the following two aims: in the shadow period, the discharge depth of the storage battery pack is less than 80 percent; in the shadow period, the single machine (mainly a storage battery) is in the optimal working temperature range by adjusting the temperature control threshold value of the single machine, so that the single machine is in the optimal working state.

(2) Shadow forecast result requirement and processing method:

in order to reduce the discharge depth fluctuation of the storage battery caused by the forecast errors of the ground shadow and the moon shadow, the forecast error is required to be less than 2 minutes. In order to simplify the time calculation of the delay instruction, the shadow entering and exiting time is rounded. The treatment method is shown in table 1 below.

TABLE 1 shadow forecast result processing method

XXXXXX-XX-XX _ A: B C, XXXX-XX-XX _ D: E: F represents the annual, monthly, hourly, and hourly seconds of the epoch.

(3) Shadow energy strategy:

the energy strategy for the shadow period of the satellite was designed as shown in table 3 below.

TABLE 2 satellite shadow period energy strategy

(4) Shadow period energy strategy implementation flow:

the shadow period energy strategy implementation flow is shown in the following table.

TABLE 3 shadow period energy policy implementation flow List

(5) Shadow period energy strategy implementation result

The energy strategy implementation result shows that the temperature of each single machine in the shadow period is within the temperature index range; the maximum discharge depth of the storage battery in the longest shadow period is not more than 76.4 percent, and is shown by referring to fig. 3; the shadow period energy strategy may implement the principles and goals of strategic formulation.

The embodiment of the invention provides an autonomous coping method and system for energy shortage in a shadow period of a high-orbit satellite, which can be used for reducing the maximum discharge depth of a storage battery when the energy shortage in the shadow period exists, reducing the influence degree of the satellite on function limitation caused by the energy shortage, improving the energy safety in the shadow period and improving the intelligent level of autonomous coping of the high-orbit satellite on the energy shortage in the shadow period.

Those skilled in the art will appreciate that, in addition to implementing the system and its various devices, modules, units provided by the present invention as pure computer readable program code, the system and its various devices, modules, units provided by the present invention can be fully implemented by logically programming method steps in the form of logic gates, switches, application specific integrated circuits, programmable logic controllers, embedded microcontrollers and the like. Therefore, the system and various devices, modules and units thereof provided by the invention can be regarded as a hardware component, and the devices, modules and units included in the system for realizing various functions can also be regarded as structures in the hardware component; means, modules, units for performing the various functions may also be regarded as structures within both software modules and hardware components for performing the method.

The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.