CN114444314A - Optimization method of satellite load on-orbit reconstruction implementation process - Google Patents
Optimization method of satellite load on-orbit reconstruction implementation process Download PDFInfo
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Abstract
The invention discloses an optimization method of an on-orbit reconstruction implementation process of satellite load, which solves the technical problems of long exposure time, multiple coordination, close connection of each party and complex influence factors in reconstruction task implementation and comprises the following steps: receiving a reconstruction task, preparing satellite reconstruction, preparing reconstruction program data uploading, performing reconstruction program data uploading, comparing data transmission data downloading, broadcasting reconstruction program data to a satellite load, comparing EEPROM data downloading, uploading three times of reconstruction program data in the same FPGA sector, loading a program, confirming a state, performing circular operation and finishing the reconstruction task. The method optimizes the implementation method of the in-orbit reconstruction of the satellite, improves the specification of the task flow of the satellite control, meets the requirement of the future in-orbit emergency task, improves the response timeliness of the control, and improves the applicability of the equipment in the orbit. Provides a method reference for promoting the application and development of space equipment.
Description
Technical Field
The invention relates to an optimization method for an on-orbit reconstruction implementation process of satellite load, belonging to the technical field of communication.
Background
In the in-orbit operation process of the satellite, when the working task is changed and the load capacity needs to be expanded, or certain devices on the satellite fail or the performance is reduced, the satellite load parameter configuration needs to be adjusted, and at the moment, the in-orbit reconstruction of the satellite needs to be implemented. By updating certain program versions of the satellite load, the load performance and the applicability are improved, and the satellite can meet the requirement of continuously executing the work task in orbit. The satellite load refers to a subsystem which directly executes a specific task on a satellite, comprises a load management and control machine, a load processor and software and hardware thereof, is equivalent to a satellite effective load and is equivalent to a satellite platform. It can be simply understood that a satellite is composed of two major parts, a platform and a load.
In the prior art, the in-orbit reconstruction function of the satellite is to reconstruct program data by injecting the program data on a ground station, receive, demodulate and reconstruct the program data and store the program data under the unified control of a load management and control machine by a related load processor, and then update the program version of each processor by a load bus protocol to complete the in-orbit function reconstruction. The satellite load on-orbit reconstruction test shows that the performance configuration of load related parameters can be adjusted in a targeted manner by reconstructing the program version of the load processor, the load function can be expanded, and the method plays an important role in completing specific tasks, improving the load applicability and the on-orbit efficiency. The reconstruction program data is modulated and processed by signals and is directly injected to a relevant load processor through an injection link protocol; the reconstruction control related instruction is injected to a satellite house keeping computer through a measurement and control link protocol, and then is forwarded to a load management controller through a 1553B bus protocol inside the satellite, and the on-orbit reconfigurable load implementation flow is shown in figure 1, wherein the injection refers to a process that an earth station sends uplink data, the instruction or program is sent to the satellite in a wireless link protocol mode, and the satellite can reliably receive the uplink data.
Processing and generating related control instructions and reconstruction program data by the ground operation and control system according to the reconstruction task requirement in the on-rail reconstruction task, and waiting for the reconstruction program data of the load injected by the ground station; the satellite platform sets the data transmission subsystem into a reconstruction mode by adjusting the satellite attitude, completes the parameter configuration of the load processor and prepares for reconstruction; after the satellite load completes the configuration of wave beams, radio frequency and the like, the reconstruction program data is received and demodulated through a reconstruction program data load link; after data extraction, the load is directly transmitted to a satellite platform data transmission subsystem to complete data storage; the data transmission subsystem carries out comparison twice in sequence by reconstructing a real-time downloading mode; and after the ground operation and control system is compared correctly, the upper injection instruction execution program is loaded to complete on-rail reconstruction. The information interaction process of the on-orbit reconstruction satellite-ground system is shown in figure 2.
The current reconfiguration task is implemented, and the overall flow of the reconfiguration task from the reception of the task requirement to the completion of the reconfiguration task is shown in fig. 3.
In the existing process, in order to ensure that each step is accurate, data uploading of each segment of reconstruction program data is carried out twice for data downloading and comparison. In order to ensure that the influence of external factors such as space environment on the satellite receiving reconstruction program data is reduced to the minimum, the processing mechanism of the satellite load on the reconstruction program data is a triple modular redundancy mode, namely, each segment of reconstruction program data needs to be stored in 3 parts to different addresses. However, since the load processor cannot automatically store the reconstruction program data into corresponding different addresses, the ground operation control system needs to mark the designated address in the reconstruction program data, and therefore the reconstruction program data of the same FPGA sector needs to be annotated for 3 times. Program replacement needs to be carried out on N FPGA sectors by referring to the developed reconstruction task, N multiplied by 3 segments of reconstruction program data need to be added in total, and data downloading and comparison needs to be carried out for 6N times with the number of multiplied by 3 multiplied by 2 according to the existing flow.
In summary, in the overall flow chart 3 of the reconstruction task, the reconstruction instruction of the existing flow has many repeated steps in the annotating and comparing stages, many interaction links, frequent scheduling, close connection, and cumbersome operation, and in addition, many ground station tasks are switched, which is prone to error, so that the whole task consumes a long time, and one load reconstruction task performed in the early stage consumes more than 20 hours.
The problems of long time, multiple coordination, close connection of all parties, complex influence factors and the like are exposed in the implementation of the reconstruction task, and the importance of the specification and optimization of the reconstruction implementation process is highlighted.
Disclosure of Invention
The invention provides an optimization method for satellite load on-orbit reconstruction task implementation, which solves the technical problems of long exposure time, multiple coordination, close connection of all parties and complex influence factors in reconstruction task implementation.
The optimization method for implementing the in-orbit reconstruction control of the satellite load disclosed by the invention can greatly compress the control time and has a remarkable effect of improving the in-orbit reconstruction control efficiency of the satellite. The method comprises the following steps:
the method comprises the following steps that firstly, a ground operation and control system receives a satellite load on-orbit reconstruction task requirement, and processing and generating reconstruction program data related to the requirement and a control instruction combining real-time and time delay;
secondly, controlling a satellite platform and a satellite load related to the requirement to perform reconstruction preparation based on a delay control instruction;
thirdly, the ground operation and control system sends reconstruction program data to the satellite load through a reconstruction program data load link, and the satellite load directly transmits and stores the received and extracted reconstruction program data in a specific storage space of the satellite platform data transmission terminal;
the ground operation and control system downloads the reconstruction program data stored by the satellite platform data transmission terminal through a real-time control instruction and compares the reconstruction program data with the reconstruction program data of the ground operation and control system so as to check the correctness of the reconstruction program data implementation flow and the reconstruction program data load link;
fifthly, after the reconstructed program data of the ground operation and control system is compared with the reconstructed program data stored in the satellite platform correctly, starting a bus transmission command through a real-time control command, broadcasting and forwarding the reconstructed program data from a specific storage space of a data transmission terminal of the satellite platform and storing the reconstructed program data to an EEPROM storage address corresponding to an FPGA sector of the satellite load processor;
after the ground operation and control system sends a real-time control instruction to finish bus transmission, sending a load program to download the real-time control instruction, downloading the reconstruction program data stored in the satellite load EEPROM, and performing secondary comparison with the reconstruction program data of the ground operation and control system to ensure that the reconstruction program data received by the satellite load is correct;
the ground operation and control system sequentially injects the reconstruction program data twice, and sends a real-time control instruction to broadcast and forward the reconstruction program data from a specific storage space of a data transmission terminal machine of the satellite platform and store the data to an EEPROM storage address corresponding to an FPGA sector of the satellite load processor;
in summary, the same FPGA sector is annotated with three times of reconstruction program data. Except for the first time of annotating and reconstructing program data, two times of data downloading and comparison are needed, the other times of annotating and reconstructing program data only need to repeat the operations of the third step, the fifth step and the seventh step, and data downloading and comparison links of the fourth step and the sixth step are omitted.
Step eight, the ground operation and control system sends a control instruction to load the reconstruction program data stored in the FPGA sector of the load processor, and the FPGA sector program version of the load processor is replaced;
and step nine, if the program versions of a plurality of FPGA sectors are required to be replaced for one reconstruction task, the steps three, five, seven and eight are circulated from the replacement of the program version of the second FPGA sector until all the program versions of all the FPGA sectors to be reconstructed are replaced, and finally the on-orbit reconstruction task of the satellite load is completed.
After the first step, the method further comprises the following steps: and the ground operation and control system schedules the ground station to be familiar with the reconstruction implementation process and prepares for modulating and transmitting reconstruction program data.
The ground station adjusts the signal-to-noise ratio of the modulation signal of the adaptive signal transmitting equipment in advance according to the receiving requirement of the satellite load processor.
In the second step, based on the delay control instruction, the satellite platform and the satellite load related to the demand are controlled to perform reconstruction preparation, including:
the ground operation and control system sends a delay control instruction to the satellite platform, adjusts the attitude of the satellite platform, sequentially performs power-on, sector erasure, reset initialization of the satellite load processor, switch array, frequency converter, intermediate frequency network control parameter configuration, beam, radio frequency and other setting work of the related satellite load and data transmission subsystems, sets the data transmission subsystems of the satellite platform into a reconstruction mode, and ensures that the satellite platform related to the requirement and the satellite load reconstruction preparation state are in place.
Before the third step, a step of preparation for reconstruction program data injection is further included, and the step includes: the ground operation and control system injects a real-time instruction of frequency point beam control and a delay instruction of link injection starting in advance, and dispatches a ground station in advance to ensure that the ground station sends a modulation signal for reconstructing program data before the link injection starting time.
In the third step, the ground operation and control system sends reconstruction program data to the satellite load through the reconstruction program data load link, and the method comprises the following steps: satellite load executes a link upper injection starting delay instruction at a starting time T1, receives a modulation signal sent by a ground station, and at the moment, a reconstruction program data load link is established; the ground station continuously sends out a modulation signal to ensure that the satellite load receives complete reconstruction program data;
after the ground station stops sending the modulation signal, the establishment of a remote control uplink is completed through a satellite-ground response handshake mechanism so as to have the condition that the ground station sends a control instruction to a satellite, and a ground operation and control system injects a real-time instruction of the stop of a single machine on the ground station;
and finishing the reconstruction program data uploading and the remote control instruction uploading in a time-sharing manner.
In the fourth step, the ground operation and control system downloads the reconstruction program data stored in the satellite platform data transmission terminal through a real-time control instruction and compares the reconstruction program data with the reconstruction program data of the ground operation and control system so as to check the correctness of the reconstruction program data implementation process and the reconstruction program data load link; the method comprises the following steps:
the ground operation control system informs the ground station of the data receiving time interval in the data transmission receiving plan preset in the control instruction, schedules the ground station in advance to establish a remote control uplink, and completes instruction injection and reconstruction program data modulation and sending operations in a time-sharing manner through the control instruction combining real time and time delay;
and the ground operation control system compares the reconstruction program data downloaded by the satellite platform and received by the ground station with the original reconstruction program data stored by the ground operation control system, and checks whether the reconstruction program data stored by the satellite platform is consistent with the original reconstruction program data stored by the ground operation control system.
The step of completing the instruction injection and reconstruction program data modulation sending operation in a time-sharing manner through the control instruction combining real time and time delay comprises the following steps: the ground operation control system processes in advance to generate a delay instruction for the injection starting on the link, injects the satellite load on the link and carries the starting time T1; informing the ground station to send a reconstruction program data modulation signal within a preset time before the starting time T1, and immediately establishing a remote control uplink after the ground station stops sending the modulation signal; filling a real-time instruction of the stop of the single machine, and controlling the load processor to be reconstructed to stop working and running; the ground station completes instruction injection and reconstruction program data modulation and transmission in a time-sharing manner, and reconstruction program data can be received when the satellite starts an injection channel of a reconstruction link.
And in the step eight, the ground operation and control system sends a real-time control instruction to load the reconstruction program data stored in the FPGA sector of the load processor, and the telemetry parameters of the load processor corresponding to the reconstruction program data are monitored to display that the loading is normal, so that the normal replacement of the FPGA sector program version of the load processor can be confirmed, and the success of the reconstruction program loading of the FPGA sector is verified.
In the ninth step, if the reconfiguration program data loading of a certain FPGA sector is unsuccessful, the corresponding reconfiguration program data can be downloaded and compared with the reconfiguration program data stored in the ground operation control system according to the annotating time, the annotating duration and the technical requirements carried by the reconfiguration program data, and if the reconfiguration program data are found to be inconsistent, the corresponding reconfiguration program data are only needed to be annotated again.
The invention has stronger pertinence and can effectively reduce repeated and reworking operations. The performance improvement effect of the load processor can be verified by developing the on-orbit task subsequently.
According to the optimization method, four times of data downloading and comparison can be reduced by reconstructing program data of one FPGA sector. Assuming that the operator is skilled in operation, the time taken for reconstructing the program data of one FPGA sector can be reduced by (14+5) × 4 ═ 76 minutes compared with the time taken for reconstructing the program data of one time by 5 minutes, referring to the time indicated in fig. 4. According to a recently implemented load reconstruction task, five FPGA sector reconstruction program data are required to be reconstructed, and after the first FPGA sector reconstruction program data is loaded successfully, subsequent four FPGA sectors are not required to be downloaded and compared. Without the need for rework operations, a total savings of 76+19 × 2 × 3 × 4 to 532 minutes is achieved. If the load reconstruction task is completed in about 22 hours according to the original operation flow; by adopting the optimization scheme, about 9 hours are saved, the time is greatly compressed by about 40 percent, and the operation efficiency is obviously improved.
Drawings
FIG. 1 is a schematic diagram of a flow of an on-orbit reconfigurable load implementation in the prior art;
FIG. 2 is a schematic diagram of interaction flow of system information in a reconstruction satellite-ground system on a rail in the prior art;
FIG. 3 is a schematic diagram of the overall flow of a reconfiguration task in the prior art;
FIG. 4 is a specific control flow of an optimization method for implementing an on-orbit reconstruction task of a satellite load;
fig. 5 is a schematic diagram of a satellite load reconstruction optimization process.
Detailed Description
In order to make the technical solutions of the present invention better understood, 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.
Example one
The process of the satellite load on-orbit reconstruction task can be combed into three links of load power-on parameter configuration preparation, reconstruction program data uploading and downloading comparison and reconstruction program loading; on the premise of ensuring that the uploading of the data of the reconstruction program is normal and reducing rework, the inventor determines a link of comparing the uploading and the downloading of the data of the reconstruction program as an optimization key and provides an optimization method.
The ground operation control system is a ground operation control system which can complete the work of satellite task planning, planning and scheduling of satellite and ground systems, generating and sending satellite control instructions, monitoring telemetering parameters, monitoring ground subsystems and other equipment, and comprises related hardware equipment and service software, and is a 'central hub' for the operation and control of the whole satellite system.
The satellite platform consists of a satellite service guarantee system and can support one or a combination of a plurality of payloads. It can be simply understood that the satellite platform is the rest of the satellite except for the payload. The system comprises various subsystems such as energy, attitude and orbit control, propulsion, measurement and control, data transmission, heat control and structure.
The satellite load is a subsystem for directly executing specific tasks on a satellite, and comprises a load management and control machine, a processor and software and hardware thereof, which is equivalent to a satellite effective load and is equivalent to a satellite platform. It can be simply understood that a satellite is composed of two major parts, a platform and a load.
The data transmission subsystem is a satellite important subsystem responsible for recording and storing various data and downloading the data. The digital transmission system comprises a solid-state memory, a digital transmission terminal, a transmitter, a power amplifier, a baseband pre-stage, a digital transmission antenna and the like.
The data transmission terminal machine is a control module in a satellite data transmission subsystem and is responsible for completing the work of time sequence control, data framing, sequencing and the like of different services such as data storage, real-time downloading, delayed playback and the like:
the ground station, namely the ground receiving measurement and control station, is responsible for completing the work of receiving and forwarding satellite telemetry data, receiving and forwarding data transmission data, injecting measurement and control instructions and the like, and is responsible for providing uplink and downlink channels between satellite and ground systems.
The FPGA sector refers to a designated address or a storage space for storing a control program in the load processor.
As shown in fig. 1 to 5, an embodiment of the present invention discloses an optimization method for implementing an in-orbit reconstruction control of a satellite load, which can significantly improve the in-orbit reconstruction control performance of the satellite when the in-orbit reconstruction control is greatly compressed. The method comprises the following steps:
and S101, receiving a reconstruction task. The ground operation and control system receives the on-orbit reconstruction task requirement of the satellite load, processes and generates a control instruction and reconstruction program data related to the requirement; and (4) the dispatching ground station is familiar with the reconstruction task flow, and the work preparation of modulating and sending the data of the load reconstruction program is made.
And S102, preparing satellite reconstruction. And parameter configuration work such as satellite attitude adjustment, load/data transmission subsystem power-on, sector erasing, load initialization and the like is completed in sequence, and the satellite is ensured to be ready for reconstruction.
Specifically, the satellite reconstruction preparation includes: the ground operation and control system sends a control instruction to the satellite platform, adjusts the attitude of the satellite platform, sequentially performs power-on, sector erasing, processor reset initialization, switch array, frequency converter, intermediate frequency network control parameter configuration, beam, radio frequency and other setting work of a related satellite load and data transmission subsystem, and sets the data transmission subsystem of the satellite platform into a reconstruction mode.
Step S103, preparation for reconstruction program data annotation. Before the reconstruction program data is injected, the ground operation and control system injects real-time instructions such as frequency point beam control and the like and delay instructions of link injection starting in advance, and dispatches a ground station in advance to ensure that the ground station sends a Ka frequency band modulation signal of the reconstruction program data before the link injection starting moment.
The frequency point beam control is to configure the working frequency of satellite load and the antenna beam direction; and the link upper note starting is to start a reconstruction program data receiving link channel of the satellite load.
And step S104, the reconstruction program data is annotated. The ground station continuously sends out Ka frequency band modulation signals to ensure that the satellite receives the completed reconstruction program data; after stopping sending the modulation signal, the ground station establishes a remote control uplink and injects a single machine stop real-time instruction. And finishing the reconstruction program data uploading and the remote control instruction uploading in a time-sharing manner.
The stand-alone stop means that the load processor to be reconstructed stops working and running.
And S105, downloading and comparing the data transmission data. The ground operation and control system manually generates a data transmission receiving plan and dispatches a ground station to establish a corresponding working plan; and (3) annotating a real-time command of real-time transmission of the data transmission terminal at the scheduled starting moment, and manually comparing the satellite data transmission data by the ground operation and control system organization to confirm that the satellite-ground link is correctly matched and ensure that the reconstruction program data received by the satellite is normal.
And step S106, reconstructing data broadcast to the load. The ground operation and control system is injected with a real-time command of 'reconstruction data broadcasting', the satellite broadcasts reconstruction program data to the load subsystem from the data transmission subsystem through the internal bus, the operation needs the satellite to complete the cycle for many times, and the reconstruction program data is ensured to be broadcast and forwarded completely.
And S107, downloading and comparing the EEPROM data. The ground operation and control system manually generates a data transmission receiving plan again, and dispatches the ground station to establish a corresponding working plan; and injecting an EEPROM download real-time instruction at the scheduled starting moment, and manually comparing the EEPROM data downloaded by the satellite by the ground operation and control system organization to confirm that the communication link from the data transmission subsystem to the load subsystem in the satellite is correctly matched, so as to ensure that the reconstruction program data received by the load is normal.
And step S108, injecting the reconstruction program data for three times on the same sector. Because the corresponding write addresses of the sectors of the FPGA to be reconstructed are different, even if the reconstruction program data is the same, it is necessary to note three times to complete the reconstruction of one sector, that is, the operations of steps S104 to S107 are repeated. However, as the matching of the satellite-ground link and the data transmission from the satellite to the load communication link is verified, the second and third times of uploading of the reconstructed program data can omit the links of data downloading and comparison twice, and only an uplink instruction needs to be sent to transmit the reconstructed program data to the load processor from the specific storage space of the data transmission terminal in a broadcast manner. As shown in fig. 5.
Step S109, the ground operation and control system sends a real-time uplink control instruction to load reconstruction program data stored in the FPGA sector of the load processor, and the FPGA sector program version of the load processor is replaced to complete reconstruction operation;
the ground operation and control system sends an uplink control instruction to load reconstruction program data stored in a load processor FPGA sector, confirms whether the version of the FPGA sector program of the load processor is normally replaced or not by monitoring the telemetering parameter change of the load processor corresponding to the reconstruction program data, and verifies whether the reconstruction program loading of the FPGA sector is successful or not.
And monitoring a telemetering parameter 'detection component FPGA loading state' of the load processor corresponding to the reconstruction program data, and displaying 'loading is normal'.
And S110, if the reconstruction task needs to replace a plurality of FPGA sector program versions, the step S104 is circulated to the step 109, and two data downloading comparison links are omitted until all the FPGA sector program versions corresponding to each section of reconstruction program data are replaced, and normal loading of the reconstruction program data is completed.
If the data loading of the reconstruction program of a certain FPGA sector is unsuccessful, the corresponding reconstruction program data can be downloaded and compared with the reconstruction program data stored in the ground operation control system according to the uploading time, the uploading duration and the technical requirements carried by the reconstruction program data, and if the reconstruction program data are found to be inconsistent, the corresponding reconstruction program data only need to be uploaded and uploaded.
By the operation, the optimization of the implementation process of the on-orbit reconstruction of the satellite load is completed.
After one section of reconstruction program data is uploaded and injected, two times of downloading comparison are carried out due to different storage positions. The reconstruction program data is stored in a specific storage space of the satellite data transmission terminal for the first time, and the reconstruction program data is stored in a storage address of a corresponding FPGA sector of the load processor for the second time through a load bus protocol. One FPGA sector corresponds to a section of reconstruction program data, one reconstruction task may involve program replacement of a plurality of FPGA sectors, so that the reconstruction program data is required to be repeatedly injected and compared for many times, and the reconstruction program data is ensured to be completely stored in the storage address of a related device. As shown in fig. 5, the reconstruction program data of the first upper note is set to V1, the second is set to V2, …, and the nth is set to Vn. According to the operation of fig. 5, when the reconstructed program data is injected for the second time and the third time, the data is not required to be downloaded and compared, and only an uplink instruction is required to be sent to transmit the reconstructed program data to the load processor from the specific storage space of the data transmission terminal machine in a broadcasting manner.
The reconstruction program data downloaded by the satellite platform comprises: data transmission data are downloaded and EEPROM data are downloaded;
the data transmission data is downloaded, namely the satellite firstly stores the received reconstruction program data modulated and sent by the ground station into a specific storage space of the data transmission terminal. This data is downloaded for purposes of comparison with the original data to ensure that the reconstructed program data received by the satellite is correct.
The method comprises the following steps that EEPROM data are downloaded, namely after the data are compared and correct for the first time, a satellite controls according to a ground real-time instruction and broadcasts and forwards reconstructed program data to a load subsystem; the payload will store the reconstructed program data into the EEPROM. The data is downloaded for comparison with the original data to ensure that the reconstructed program data forwarded by the data transmission subsystem to the load subsystem is correct.
The EEPROM is a charged erasable programmable read-only memory, is a storage medium with no data loss after power failure, and has the characteristics of repeatedly erasing existing information and reprogramming.
The invention has stronger pertinence and can effectively reduce repeated and reworking operations. The performance of the load processor can be verified through developing on-orbit tasks subsequently, and the effect is improved after the on-orbit task is reconstructed.
The invention provides an optimization scheme capable of greatly compressing the operation time based on the actual operation process of a certain satellite load reconstruction task based on the combing analysis, which defines the operation steps and quantifies the evaluation effect. The method has the advantages that key links such as a single ground station guarantee mode, real-time and delay instruction combined application, signal to noise ratio of transmitted signals and the like are explained, a satellite on-orbit reconstruction implementation method is optimized, satellite control task flow specifications are improved, future on-orbit emergency task requirements are met, control response timeliness is improved, and equipment on-orbit applicability is improved. Provides a method reference for promoting the application and development of space equipment.
The key points of the technology mainly comprise the following points:
1. data modulation and transmission of ground station single-station time-sharing implementation instruction upper injection and reconstruction program
In the reconstruction task, the ground station needs to play roles of instruction uploading, data receiving and data modulation and transmission of the reconstruction program. In the past, a reconstruction task adopts a 'double-station' mode, namely, extra coordination of ground station resources is needed to ensure that instruction uploading and data modulation and transmission of a reconstruction program are implemented simultaneously. Compared with a double-station mode, the reconstructed single-station mode has the advantages that the ground operation control system only needs to carry out special line scheduling on a single ground station, the coordination relation is simple, the coordination difficulty with additional ground stations is reduced, the scheduling frequency is reduced, and the interaction links are compressed.
It should be noted that the "single station" mode requires the ground station to execute different operations in a time-sharing manner, the instruction injection and the reconstruction program data modulation and transmission are performed alternately, the switching time is tightly connected, the requirement on the ground station is high, and the operation of the staff is required to be skilled. This requires that the operation control system scheduling personnel fully communicate with the ground station in advance, and are familiar with the operation flow together, and the two parties are closely matched in the implementation process.
2. Real-time instruction and delay instruction of operation control system are combined for application
The satellite can receive the uplink modulation signal sent by the ground station at the starting moment of executing the reconstruction program data link uplink injection, and the ground station can only finish the instruction uplink injection and the reconstruction program data modulation sending in a time-sharing manner. In order to solve the contradiction, a 'link up injection starting' instruction of reconstruction program data is made into a delay instruction to inject a satellite in advance, then a ground station is switched to execute the modulation and transmission of the reconstruction program data, the 'link up injection starting' time interval is continuously compressed after the verification is ground, and finally the modulation signal is determined to be transmitted for the ground station and then executed for 2min, so that higher requirements are provided for operation control system scheduling personnel and ground station operating personnel.
3. The signal-to-noise ratio of the modulation signal of the ground station signal transmitting equipment needs to be adjusted and adapted in advance
Because the on-orbit load reconstruction task of the satellite is less executed, the signal-to-noise ratio of a modulation signal of the ground station signal transmitting equipment is only (X-3) dB, the equipment needs to be debugged in advance, and the signal-to-noise ratio of the transmission signal is increased by 3dB, so that the receiving requirement of the on-satellite load processor of XdB is met.
According to the optimization method, four times of data downloading and comparison can be reduced by reconstructing program data of one FPGA sector. Assuming that the operator is skilled in operation, the time for reconstructing program data for reconstructing one FPGA sector can be reduced by (14+5) × 4 ═ 76 minutes, as can be seen from looking at the times in fig. 3 and 4, compared with the time for once using 5 minutes. Five FPGA sectors need to be reconstructed according to a recently implemented load reconstruction task, and after the reconstruction program data of the first FPGA sector are loaded successfully, the subsequent program data of the four FPGA sectors do not need to be downloaded and compared. Without the need for rework operations, a total savings of 76+19 × 2 × 3 × 4 to 532 minutes can be achieved. If the load reconstruction task is completed in about 22 hours according to the original operation flow; by adopting the optimization scheme, about 9 hours are saved, the time is greatly compressed by about 40 percent, and the operation efficiency is obviously improved.
Claims (10)
1. A method for optimizing an implementation process of on-orbit reconstruction of satellite loads is characterized by comprising the following steps:
the method comprises the following steps that firstly, a ground operation and control system receives a satellite load on-orbit reconstruction task requirement, and processing and generating reconstruction program data related to the requirement and a control instruction combining real-time and time delay;
secondly, controlling a satellite platform and a satellite load related to the requirement to perform reconstruction preparation based on a delay control instruction;
thirdly, the ground operation and control system sends reconstruction program data to the satellite load through a reconstruction program data load link, and the satellite load directly transmits and stores the received and extracted reconstruction program data in a specific storage space of the satellite platform data transmission terminal;
the ground operation and control system downloads the reconstruction program data stored by the satellite platform data transmission terminal through a real-time control instruction and compares the reconstruction program data with the reconstruction program data of the ground operation and control system so as to check the correctness of the reconstruction program data implementation flow and the reconstruction program data load link;
fifthly, after the reconstructed program data of the ground operation and control system is compared with the reconstructed program data stored in the satellite platform correctly, starting a bus transmission command through a real-time control command, broadcasting and forwarding the reconstructed program data from a specific storage space of a data transmission terminal of the satellite platform and storing the reconstructed program data to an EEPROM storage address corresponding to an FPGA sector of the satellite load processor;
after the ground operation and control system sends a real-time control instruction to finish bus transmission, sending a load program to download the real-time control instruction, downloading the reconstruction program data stored in the satellite load EEPROM, and performing secondary comparison with the reconstruction program data of the ground operation and control system to ensure that the reconstruction program data received by the satellite load is correct;
the ground operation and control system sequentially injects the reconstruction program data twice, and sends a real-time control instruction to broadcast and forward the reconstruction program data from a specific storage space of a data transmission terminal machine of the satellite platform and store the data to an EEPROM storage address corresponding to an FPGA sector of the satellite load processor;
step eight, the ground operation and control system sends a control instruction to load the reconstruction program data stored in the FPGA sector of the load processor, and the FPGA sector program version of the load processor is replaced;
and step nine, if the program versions of a plurality of FPGA sectors are required to be replaced for one reconstruction task, the steps three, five, seven and eight are circulated from the replacement of the program version of the second FPGA sector until all the program versions of all the FPGA sectors to be reconstructed are replaced, and finally the on-orbit reconstruction task of the satellite load is completed.
2. The method of claim 1, wherein after step one, further comprising: and the ground operation and control system schedules the ground station to be familiar with the reconstruction implementation process and prepares for modulating and transmitting reconstruction program data.
3. The method of claim 2, wherein the ground station pre-adjusts the modulation signal-to-noise ratio of the adapted signal transmitting device based on the reception requirements of the satellite load handler.
4. The method of claim 1, wherein in the second step, the controlling the satellite platform and the satellite load related to the demand to prepare for reconstruction based on the delay control command comprises:
the ground operation and control system sends a delay control instruction to the satellite platform, adjusts the attitude of the satellite platform, sequentially performs power-on, sector erasure, reset initialization of the satellite load processor, switch array, frequency converter, intermediate frequency network control parameter configuration, beam, radio frequency and other setting work of the related satellite load and data transmission subsystems, sets the data transmission subsystems of the satellite platform into a reconstruction mode, and ensures that the satellite platform related to the requirement and the satellite load reconstruction preparation state are in place.
5. The method of claim 1, wherein before step three, further comprising the step of reconstruction program data annotation preparation, the step comprising: the ground operation and control system injects a real-time instruction of frequency point beam control and a delay instruction of link injection starting in advance, and dispatches a ground station in advance to ensure that the ground station sends a modulation signal for reconstructing program data before the link injection starting time.
6. The method of claim 1 or 5, wherein in step three, the ground operation control system sends the reconstruction program data to the satellite load through the reconstruction program data load link, and the method comprises: satellite load executes a link upper injection starting delay instruction at a starting time T1, receives a modulation signal sent by a ground station, and at the moment, a reconstruction program data load link is established; the ground station continuously sends out a modulation signal to ensure that the satellite load receives complete reconstruction program data;
after the ground station stops sending the modulation signal, the establishment of a remote control uplink is completed through a satellite-ground response handshake mechanism so as to have the condition that the ground station sends a control instruction to a satellite, and the ground operation control system stops running through a real-time instruction of a stand-alone injection machine on the ground station;
and finishing the reconstruction program data uploading and the remote control instruction uploading in a time-sharing manner.
7. The method as claimed in claim 1, wherein in the fourth step, the ground operation and control system downloads the reconstruction program data stored in the satellite platform data transmission terminal through the real-time control command and compares the reconstruction program data with the reconstruction program data of the ground operation and control system to check the correctness of the reconstruction program data implementation process and the reconstruction program data load link; the method comprises the following steps:
the ground operation control system informs the ground station of the data receiving time interval in the data transmission receiving plan preset in the control instruction, schedules the ground station in advance to establish a remote control uplink, and completes instruction injection and reconstruction program data modulation and sending operations in a time-sharing manner through the control instruction combining real time and time delay;
the ground operation control system compares the reconstruction program data received by the ground station and transmitted by the satellite platform with the original reconstruction program data stored by the ground operation control system, and checks whether the reconstruction program data stored by the satellite platform is consistent with the original reconstruction program data stored by the ground operation control system.
8. The method of claim 7, wherein the step of time-sharing the control commands combined with real-time delay to perform command-up and reconfiguration program data modulation transmission operations comprises: the ground operation control system processes in advance to generate a delay instruction for the injection starting on the link, injects the satellite load on the link and carries the starting time T1; informing the ground station to send a reconstruction program data modulation signal within a preset time before the starting time T1, and immediately establishing a remote control uplink after the ground station stops sending the modulation signal; filling a real-time instruction of the stop of the single machine, and controlling the load processor to be reconstructed to stop working and running; the ground station completes instruction injection and reconstruction program data modulation and transmission in a time-sharing manner, and reconstruction program data can be received when the satellite starts an injection channel of a reconstruction link.
9. The method according to claim 1, wherein in the eighth step, the ground operation and control system sends a real-time control instruction to load the reconstruction program data stored in the FPGA sector of the load handler, and the telemetry parameters of the load handler corresponding to the reconstruction program data are monitored to show that the loading is normal, so that the fact that the FPGA sector program version of the load handler is normally replaced can be confirmed, and the fact that the reconstruction program loading of the FPGA sector is successful is verified.
10. The method according to claim 1, wherein in the ninth step, if it is found that the reconfiguration program data of a certain FPGA sector is not loaded successfully, the corresponding reconfiguration program data downloaded can be compared with the reconfiguration program data stored in the ground operation control system according to the annotating time, the annotating duration and the technical requirements carried by the reconfiguration program data, and if the reconfiguration program data is found to be inconsistent, the corresponding reconfiguration program data only needs to be annotated again.
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