CN110034812B - Autonomous safety protection method for on-satellite emergency and state recovery of low-earth orbit satellite - Google Patents
Autonomous safety protection method for on-satellite emergency and state recovery of low-earth orbit satellite Download PDFInfo
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- CN110034812B CN110034812B CN201910165290.8A CN201910165290A CN110034812B CN 110034812 B CN110034812 B CN 110034812B CN 201910165290 A CN201910165290 A CN 201910165290A CN 110034812 B CN110034812 B CN 110034812B
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M10/00—Secondary cells; Manufacture thereof
- H01M10/42—Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells
- H01M10/4207—Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells for several batteries or cells simultaneously or sequentially
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
- H04B7/185—Space-based or airborne stations; Stations for satellite systems
- H04B7/1851—Systems using a satellite or space-based relay
- H04B7/18519—Operations control, administration or maintenance
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02E60/10—Energy storage using batteries
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Abstract
The invention discloses an autonomous safety protection method for on-satellite emergency and state recovery of a low-orbit satellite, which comprises the following steps: judging whether the program-controlled autonomous safety protection function is forbidden; judging whether two groups of storage batteries are in energy crises or not; the safety protection program control shutdown instruction queue sends and executes; the thermal control electric heater prohibits program control and sends out and executes a shutdown instruction queue; judging whether a full-posture sun-facing directional control mode is entered; judging whether two groups of storage batteries are in energy crises or not; the safety protection program control shutdown instruction queue sends and executes; judging whether two groups of storage batteries are recovered preliminarily; judging whether the program control of the thermal control electric heater is forbidden or not; certain portions of the thermally controlled electric heater are program controlled to allow. According to the invention, the safety protection operation is automatically carried out on the satellite according to the crisis condition, and the program control function of the specific part of the thermal control electric heater can be automatically recovered after the energy of the satellite is initially recovered to be normal, so that the satellite can be automatically and effectively protected under the crisis condition, the reliability of the satellite is ensured, and the on-orbit service life of the satellite is prolonged.
Description
Technical Field
The invention relates to an autonomous safety protection method in the technical field of satellite housekeeping software, in particular to an autonomous safety protection method for emergency and state recovery on a low-orbit satellite.
Background
The lithium ion storage battery pack adopted on the satellite has the advantages of small volume, light weight and large storage capacity, but also has the defect of failure under specific conditions, namely, the lithium ion storage battery pack does not have charging capacity any more after deep discharge, so the lithium ion storage battery on the satellite has an over-discharge protection function, and when the discharge voltage of the storage battery drops to a certain threshold value, all power consumption single-machine equipment (including an electric heater) which does not influence the life safety of the satellite on the satellite should be closed, so that the consumption of the lithium ion storage battery is reduced, and the safety and normal use of the lithium ion storage battery are ensured.
When the attitude of the satellite is abnormal, so that the solar cell array cannot face the sun normally, namely the satellite cannot acquire solar energy normally, the attitude and orbit control software enters a full-attitude sun-facing orientation mode according to the design of the satellite attitude and orbit control subsystem, and the solar cell array can face the sun to acquire solar energy after the sun is successfully captured. In the full-attitude sun-oriented mode, the satellite is mainly powered by the storage battery pack and also faces the danger of excessive consumption of the storage battery on the satellite, so all power-consumption single-machine equipment (which can not comprise an electric heater) which does not influence the life safety of the satellite should be turned off on the satellite at the moment.
Because some single machines on the satellite can not be started normally when the temperature is too low, a certain temperature condition needs to be ensured before starting, and after the satellite recovers from the condition of low voltage of the lithium ion storage battery, namely the voltage gradually rises, some electric heaters which influence the starting of the single machines on the satellite are started so that the single machines can be started normally.
In summary, the invention relates to an autonomous safety protection method for satellite emergency and state recovery of a low-earth orbit satellite, which can autonomously perform safety protection operation on the satellite according to the crisis conditions of energy and attitude on the satellite, and autonomously recover the program control function of a specific part of thermal control electric heaters after the satellite energy is initially recovered to be normal, so that the satellite can autonomously and effectively perform self protection under the crisis condition, thereby ensuring the reliability of the satellite and prolonging the on-orbit service life of the satellite.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide an autonomous safety protection method for satellite emergency and state recovery of a low-earth orbit satellite, which can autonomously perform safety protection operation on the satellite according to the crisis conditions of satellite onboard energy and attitude, and can autonomously recover the program control function of a specific part of thermal control electric heaters after the satellite energy is initially recovered to be normal, so that the satellite can autonomously and effectively perform self protection under the crisis condition, further the satellite reliability is ensured, and the in-orbit service life of the satellite is prolonged.
The invention is realized according to the following technical scheme:
an autonomous safety protection method for emergency and state recovery on a low earth orbit satellite is characterized by comprising the following steps:
step S1: judging whether the program control autonomous safety protection function is forbidden according to the mark which can be injected and modified on the ground;
step S2: setting two groups of storage batteries, and judging whether the two groups of storage batteries have energy crisis or not, wherein the two groups of storage batteries comprise a first group of storage batteries and a second group of storage batteries;
step S3: the safety protection program control shutdown instruction queue sends and executes, wherein the instruction queue comprises the shutdown of each single machine of each load and data transmission subsystem on the satellite; two groups of storage batteries of the instruction queue only send and execute once;
step S4: the thermal control electric heater prohibits program control and sends out and executes a shutdown instruction queue;
step S5: judging whether to enter a full-posture sun-oriented control mode or not by a mark given by posture and orbit control subsystem software;
step S6: continuously judging whether the energy crisis occurs in the two groups of storage batteries;
step S7: when the two groups of storage batteries are not in the energy crisis, the safety protection program control shutdown instruction queue is sent and executed, wherein the instruction queue comprises the steps of closing each single machine of each load and each single machine of the data transmission subsystem on the satellite; two groups of storage batteries of the instruction queue only send and execute once;
step S8: judging whether the two groups of storage batteries are recovered;
step S9: the program control of the thermal control electric heater is forbidden by the program control quasi-forbidden marks of all the electric heaters in a forbidden state;
step S10: the recovery program control relates to the load and the automatic switch control of the electric heater started on the track of the data transmission single machine.
In the above technical solution, the step S2 or the step S6 is determined by the following method: when the voltage of any one of the two groups of storage batteries is less than the safe threshold voltage for 10 continuous beats, the group of storage batteries is in energy crisis, and when the group of storage batteries is in energy crisis, if the voltage of any one of the two groups of storage batteries is greater than the safe recovery voltage for 5 continuous beats, the group A storage batteries are not in energy crisis any more.
In the above technical solution, step S4 specifically includes: the method comprises the steps of firstly forbidding automatic on-off control of the thermal control electric heaters by on-board program control software, then sending off instructions of the thermal control electric heaters, and queuing two groups of storage batteries by the instructions and only sending and executing the instructions once.
In the above technical solution, step S8 is determined by the following method: if the battery voltages of the two groups of storage batteries are greater than the safety recovery voltage for 80 continuous beats, the group of storage batteries are no longer in energy crisis.
Compared with the prior art, the invention has the following beneficial effects:
firstly, the autonomous safety protection method provided by the invention can autonomously perform safety protection operation on the satellite according to the existing conditions and conditions of the satellite storage battery voltage and the three-axis attitude angle.
Secondly, the autonomous safety protection method provided by the invention can autonomously recover the program control function of the specific part of the thermal control electric heater related to the single-machine starting temperature of the load, the data transmission and the like after the voltage of the satellite storage battery is initially recovered to be normal.
Thirdly, the autonomous safety protection method provided by the invention can autonomously and effectively perform self-protection on the satellite under the crisis condition, thereby ensuring the reliability of the satellite and prolonging the on-orbit service life of the satellite.
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 flow chart of an autonomous safety protection method for emergency and state recovery on a low earth orbit satellite according to the invention.
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.
Fig. 1 is a flow chart of an autonomous safety protection method for emergency and state recovery on a low earth orbit satellite according to the invention. As shown in fig. 1, the autonomous safety protection method for emergency and state recovery on a low earth orbit satellite of the present invention includes the following steps:
step S1: judging whether the program control autonomous safety protection function is forbidden according to the mark which can be injected and modified on the ground;
step S2: setting two groups of storage batteries, and judging whether the two groups of storage batteries have energy crisis or not, wherein the two groups of storage batteries comprise a first group of storage batteries and a second group of storage batteries;
specifically, when the voltage of any one of the two groups of storage batteries is less than the safety threshold voltage for 10 continuous beats, the group of storage batteries is in energy crisis, and after the group of storage batteries is in energy crisis, if the voltage of any one of the two groups of storage batteries is greater than the safety recovery voltage for 5 continuous beats, the group A storage batteries are no longer in energy crisis.
In a specific embodiment of the present invention, a first group of storage batteries is set as a group a storage batteries, a second group of storage batteries is set as a group B storage batteries, when the voltage of the group a (or group B) storage batteries is less than the safety threshold voltage (ground reference set value) for 10 continuous beats, the group a (or group B) storage batteries are in energy crisis, i.e., the group a flag DANA is 11 (or the group B flag DANB is 11), and when the storage batteries are in energy crisis, if the voltage of the group a (or group B) storage batteries is greater than the safety recovery voltage (ground reference set value) for 5 continuous beats, the group a (or group B) storage batteries are no longer in energy crisis, i.e., the group a flag DANA is 00 (or the group B flag DANB is 00).
Step S3: the safety protection program control shutdown instruction queue sends and executes, wherein the instruction queue comprises the shutdown of each single machine of each load and data transmission subsystem on the satellite; two groups of storage batteries of the instruction queue only send and execute once; in addition, the two groups of storage batteries in the instruction queue are not repeatedly sent and executed.
Step S4: the thermal control electric heater prohibits program control and sends out and executes a shutdown instruction queue;
in the invention, the automatic on-off control of the thermal control electric heaters by the satellite program control software is firstly forbidden, and then the off-state instruction of each thermal control electric heater is sent. In addition, the two groups of storage batteries in the instruction queue of the step are not repeatedly sent and executed, and are only sent and executed once.
Step S5: judging whether to enter a full-posture sun-facing directional control mode by a mark given by posture and orbit control subsystem software, namely judging that the mark QZT is 11;
step S6: continuously judging whether the energy crisis occurs in the two groups of storage batteries;
likewise, in the present invention, when the group a (or group B) battery voltage is less than the safety threshold voltage (ground bet set value) for 10 consecutive beats, the group a (or group B) battery energy crisis, i.e., the group a flag DANA is 11 (or the group B flag DANB is 11), and when the battery is in the energy crisis, if the group a (or group B) battery voltage is greater than the safety recovery voltage (ground bet set value) for 5 consecutive beats, the group a (or group B) battery is no longer in the energy crisis, i.e., the group a flag DANA is 00 (or the group B flag DANB is 00).
Step S7: when the two groups of storage batteries are not in energy crisis, the safety protection program control shutdown instruction queue is made to send and execute, wherein the instruction queue comprises the steps of closing each load on the satellite and each single machine of the data transmission subsystem; two groups of storage batteries of the instruction queue only send and execute once; the energy crisis of the storage battery in the instruction queue and the full-attitude solar-oriented mode are not repeatedly sent and executed.
Step S8: judging whether the two groups of storage batteries are recovered;
if the battery voltages of the two groups of storage batteries are greater than the safety recovery voltage for 80 continuous beats, the group of storage batteries are no longer in energy crisis.
In the invention, when the voltages of the batteries of the A group and the B group are both greater than the initial recovery voltage (the value of the ground mark) for 80 continuous beats, the batteries of the A group and the B group are initially recovered, namely the A group mark RKA is 11 and the B group mark RKB is 11.
Step S9: the program control of the thermal control electric heater is forbidden by the program control quasi-forbidden marks of all the electric heaters in a forbidden state;
step S10: the recovery program control relates to the load and the automatic switch control of the electric heater started on the track of the data transmission single machine.
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.
Claims (2)
1. An autonomous safety protection method for emergency and state recovery on a low earth orbit satellite is characterized by comprising the following steps:
step S1: judging whether the program control autonomous safety protection function is forbidden according to the mark which can be annotated and modified on the ground, and executing the step S2 when the program control autonomous safety protection function is not forbidden;
step S2: setting two groups of storage batteries, and judging whether the two groups of storage batteries have energy crisis or not, wherein the two groups of storage batteries comprise a first group of storage batteries and a second group of storage batteries; when the energy crisis occurs to any one of the two groups of storage batteries, executing the step S3, and if the energy crisis does not occur to the two groups of storage batteries, executing the step S5;
step S3: the safety protection program control shutdown instruction queue sends and executes, wherein the instruction queue comprises the shutdown of each single machine of each load and data transmission subsystem on the satellite; when the two groups of storage batteries simultaneously have energy crises, the storage batteries are not repeatedly sent and executed, and the instruction queue only sends and executes the storage batteries once;
step S4: the thermal control electric heater prohibits program control and sends out and executes a shutdown instruction queue; when the two groups of storage batteries simultaneously have energy crises, the storage batteries are not repeatedly sent and executed, and the instruction queue only sends and executes the storage batteries once;
step S5: judging whether to enter a full-posture sun-oriented control mode or not by a mark given by posture and orbit control subsystem software; when entering the full-attitude sun-facing directional control mode, executing step S6; when the full-posture sun-facing directional control mode is not entered, executing step S8;
step S6: continuously judging whether the energy crisis occurs in the two groups of storage batteries; when the energy crisis occurs to any one of the two groups of storage batteries, executing the step S8, and when the energy crisis does not occur to any one of the two groups of storage batteries, executing the step S7;
step S7: when the two groups of storage batteries are not in the energy crisis, the safety protection program control shutdown instruction queue is sent and executed, wherein the instruction queue comprises the steps of closing each single machine of each load and each single machine of the data transmission subsystem on the satellite; the energy crisis of the storage battery and the full-attitude sun-oriented mode are not repeatedly sent and executed, and the instruction queue only sends and executes once;
step S8: judging whether the two groups of storage batteries are recovered preliminarily, and executing the step S9 when the two groups of storage batteries are recovered;
step S9: judging whether the program control of the thermal control electric heater is forbidden according to the program control prohibition sign of the thermal control electric heater, and executing the step S10 when the program control of the thermal control electric heater is forbidden;
step S10: restoring the program control to the autonomous switch control of the electric heater related to the on-track starting of the load and the data transmission single machine;
when the voltage of any one of the two groups of storage batteries is less than the safe threshold voltage for 10 continuous beats, the storage battery in the group is in energy crisis, and when the storage battery in the group is in energy crisis, if the voltage of any one of the two groups of storage batteries is more than the safe recovery voltage for 5 continuous beats, the current storage battery is not in energy crisis any more;
the step S8 is determined by the following method: if the battery voltages of the two groups of storage batteries are greater than the safety recovery voltage for 80 continuous beats, the group of storage batteries are no longer in energy crisis.
2. The autonomous safety protection method for emergency and state recovery on low earth orbit satellite according to claim 1, wherein step S4 specifically includes: the method comprises the steps of firstly forbidding automatic startup and shutdown control of the thermal control electric heaters by on-board program control software, then sending shutdown instructions of the thermal control electric heaters, not repeatedly sending and executing when energy crisis occurs to two groups of storage batteries simultaneously, and only sending and executing once in an instruction queue.
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