CN115118330A - Multi-satellite cooperation on-orbit information interaction protocol and time sequence design method, device and medium - Google Patents
Multi-satellite cooperation on-orbit information interaction protocol and time sequence design method, device and medium Download PDFInfo
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- H04—ELECTRIC COMMUNICATION TECHNIQUE
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- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
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- H04B7/18521—Systems of inter linked satellites, i.e. inter satellite service
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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
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- Y02D—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN INFORMATION AND COMMUNICATION TECHNOLOGIES [ICT], I.E. INFORMATION AND COMMUNICATION TECHNOLOGIES AIMING AT THE REDUCTION OF THEIR OWN ENERGY USE
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Abstract
The embodiment of the invention discloses a method, a device and a medium for designing a multi-satellite collaborative on-orbit information interaction protocol and a time sequence; the method comprises the following steps: classifying and packaging multi-source guiding information received by a planning satellite in real time to design an inter-satellite data packet; designing the inter-satellite data packet interaction protocol between the planning satellite and each member satellite based on the designed inter-satellite data packet; and planning and executing the multi-satellite cooperative task based on the inter-satellite data packet interaction protocol according to a set time sequence rule.
Description
Technical Field
The embodiment of the invention relates to the technical field of spacecrafts, in particular to a method, a device and a medium for designing a multi-satellite cooperative on-orbit information interaction protocol and a time sequence.
Background
With the increasing dependence on spatial information support, satellite earth observation tasks are generally oriented to some global key areas, are wide in range, random in target and strong in task mobility, and can be generally executed by means of multi-satellite and multi-load. The load accurately analyzes and processes the collected data in an on-orbit manner in real time, further identifies and confirms the target to be observed, and transmits primary target information after the target is identified and confirmed, so that the target confidence is required to be high. Therefore, the multi-satellite collaborative autonomous task planning system has the following characteristics: the multiple loads are distributed on multiple small satellites, the satellites are small and cheap, the loads are various, and compared with a large and full single satellite, the organization form of the constellation is more flexible.
The multi-satellite collaborative design scheme enables information acquisition time to be continuous and space to be expanded, a constellation system composed of a plurality of satellites is used for collaboratively observing a ground target, the time continuity of image acquisition is stronger, the frequency and the region range of image acquisition are increased, different observation satellites can conveniently observe the same ground target or phenomenon at different angles, or continuous regions can be observed at the same time, the integration of simultaneous and multidimensional load information is facilitated, the complex multi-satellite system is composed of different types of imaging satellites, more abundant image data can be collected through multi-satellite collaboration, the integration of on-orbit information is facilitated, and the related information of the target can be accurately identified.
At present, the prior art mainly focuses on multiple aspects of multi-satellite autonomous task planning, multi-source satellite in-orbit data fusion, multi-satellite cooperation in-orbit information interaction and the like; however, most of the prior art is relatively independent in specific development, the input conditions and the constraint conditions of research are greatly different from the actual application environment, and the key links in the autonomous task collaborative full link have relatively complex association relations with each other.
Disclosure of Invention
In view of this, embodiments of the present invention are to provide a method, an apparatus, and a medium for designing a multi-satellite cooperative on-orbit information exchange protocol and a time sequence; by specifying the sending time of the data packets among the satellites, the on-orbit information interaction among the satellites can be performed orderly and accurately.
The technical scheme of the embodiment of the invention is realized as follows:
in a first aspect, an embodiment of the present invention provides a method for designing a multi-satellite cooperation on-orbit information interaction protocol and a time sequence, where the method includes:
classifying and packaging the multi-source guiding information received by the planning satellite in real time to design an inter-satellite data packet;
designing the inter-satellite data packet interaction protocol between the planning satellite and each member satellite based on the designed inter-satellite data packet;
and planning and executing the multi-satellite cooperative task based on the inter-satellite data packet interaction protocol according to a set time sequence rule.
In a second aspect, an embodiment of the present invention provides a device for designing an on-orbit information interaction protocol and a time sequence for multi-satellite collaboration, where the device includes: an inter-satellite data packet design part, an interaction protocol design part and a planning part; wherein the content of the first and second substances,
the inter-satellite data packet design part is configured to design an inter-satellite data packet by classifying and packaging multi-source guide information received by a planning satellite in real time;
the interaction protocol design part is configured to design the inter-satellite data packet interaction protocol between the planning satellite and each member satellite based on the designed inter-satellite data packet;
the planning part is configured to plan and execute the multi-satellite cooperative task according to a set time sequence rule based on the inter-satellite data packet interaction protocol.
In a third aspect, an embodiment of the present invention provides a computing device, where the computing device includes: a communication interface, a memory and a processor; the various components are coupled together by a bus system in which,
the communication interface is used for receiving and sending signals in the process of receiving and sending information with other external network elements;
the memory for storing a computer program operable on the processor;
the processor is configured to execute the steps of the multi-satellite cooperative on-orbit information interaction protocol and the time sequence design method according to the first aspect when the computer program is run.
In a fourth aspect, an embodiment of the present invention provides a computer storage medium, where the computer storage medium stores a multi-satellite collaborative on-orbit information interaction protocol and a time sequence design program, and when the program is executed by at least one processor, the method implements the steps of the multi-satellite collaborative on-orbit information interaction protocol and the time sequence design method in the first aspect.
The embodiment of the invention provides a method, a device and a medium for designing a multi-satellite cooperation on-orbit information interaction protocol and a time sequence; the method comprises the steps of classifying and packaging multi-source guiding information received by a planning satellite in real time to design an inter-satellite data packet; designing an inter-satellite data packet interaction protocol between the planning satellite and each member satellite based on the designed inter-satellite data packet; planning and executing a multi-satellite cooperative task based on an inter-satellite data packet interaction protocol according to a set time sequence rule; by stipulating the sending time of various inter-satellite data packets, the on-orbit information interaction among the multiple satellites is orderly and accurately executed.
Drawings
Fig. 1 is a schematic flow chart of a multi-satellite collaborative on-orbit information interaction protocol and a time sequence design method according to an embodiment of the present invention;
fig. 2 is a schematic diagram illustrating a design of an on-orbit information interaction protocol of a multi-satellite task cooperation according to an embodiment of the present invention;
fig. 3 is a schematic diagram illustrating a timing sequence design of the multi-satellite task cooperation on-orbit information interaction according to an embodiment of the present invention;
fig. 4 is a schematic diagram illustrating a multi-satellite cooperative on-orbit information interaction protocol and a time sequence design apparatus according to an embodiment of the present invention;
fig. 5 is a schematic diagram of a specific hardware structure of a computing device according to an embodiment of the present invention.
Detailed Description
The technical solution in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention.
At present, the prior art has a common research on a single-satellite load protocol, for example, a 1553B high-level bus communication protocol and a CAN bus communication protocol have strict timing sequence definitions. With the attendant diversity in satellite loading and complexity in satellite service design. In order to meet the actual satellite scheduling requirements and to deal with the changes caused by various uncertainties, it is more urgent to design a fast and effective information interaction protocol. The multi-satellite autonomous task planning technology is an effective means for better combining and utilizing satellite resources and ground resources, and is also a crucial link in the whole multi-satellite control system, so that the protocol and the time sequence of multi-satellite cooperative task planning are also important. In addition, aiming at the communication hardware research of a satellite-borne platform, the method mainly researches the transceiving and analysis of an inter-satellite ranging signal and an inter-satellite communication signal, provides an inter-satellite ranging mode and method, and determines the communication code and the communication rate of the ranging communication module for the self-adaptive control module according to an inter-satellite link budget result. However, at present, there is rarely research on the multi-satellite cooperative on-orbit information interaction protocol and timing.
Therefore, based on the above explanation, the embodiments of the present invention are expected to provide a multi-satellite collaborative on-orbit information interaction protocol and a time sequence design, which can provide technical support for each link of the multi-satellite task collaborative on-orbit. Referring to fig. 1, it shows a method for designing a multi-satellite cooperative on-orbit information interaction protocol and a time sequence provided by an embodiment of the present invention, where the method specifically includes:
s101, classifying and packaging multi-source guiding information received by a planning satellite in real time to design an inter-satellite data packet;
s102, designing an inter-satellite data packet interaction protocol between the planning satellite and each member satellite based on the designed inter-satellite data packet;
and S103, planning and executing a multi-satellite cooperative task based on the inter-satellite data packet interaction protocol according to a set time sequence rule.
For the technical scheme shown in fig. 1, multi-source guiding information received by a planning satellite in real time is classified and packaged to design an inter-satellite data packet; designing an inter-satellite data packet interaction protocol between the planning satellite and each member satellite based on the designed inter-satellite data packet; and planning and executing the multi-satellite cooperative task according to a set time sequence rule based on an inter-satellite data interaction protocol. Through the technical scheme shown in fig. 1, reasonable antenna pointing layout between the satellites and the member satellites is planned, and the member satellites are continuously visible through the inter-satellite low-speed link in the whole process and the whole posture of multi-satellite cooperative operation. Meanwhile, the multi-satellite autonomous task planning carries out inter-satellite cluster information interaction through the inter-satellite low-speed network, and the protocol format of the multi-satellite autonomous task planning follows the inter-satellite low-speed packet format, so that technical support can be provided for all links of the multi-satellite task cooperation on orbit. And the on-orbit information interaction among the multiple stars can be orderly and accurately executed by stipulating the sending time of various inter-star data packets.
For the technical solution shown in fig. 1, in some possible embodiments, the designing an inter-satellite data packet by classifying and grouping multi-source guidance information received by a planning satellite in real time includes:
and classifying and packaging the multi-source guiding information into a cooperative scheduling data packet, a state feedback data packet and an inter-satellite guiding data packet according to the on-satellite and ground multi-source guiding information received by the planning satellite in real time.
It should be noted that, in the embodiment of the present invention, as shown in fig. 2, multi-source guiding information on the satellite and on the ground may be first transmitted to an inter-satellite network terminal, and then transmitted to a planning satellite through an RS422 interface via the inter-satellite network transmission terminal, the planning satellite receives the multi-source guiding information in real time, and performs calculation processes such as on-satellite task planning, comprehensive guiding information processing, visible time window calculation, task distribution optimization, large area task decomposition, and the like according to various constraints, generates guiding information of each member satellite, and transmits imaging coordinates and imaging mode data information to each member satellite, and the planning satellite and the member satellites realize interaction of inter-satellite data by receiving or transmitting a cooperative scheduling data packet, a state feedback data packet, and an inter-satellite guiding data packet, so as to promote the orderly development and implementation of multi-satellite cooperative task planning.
For the above possible implementation, in some examples, the cooperative scheduling packet includes: setting information of a cooperative task, ground preset imaging target information, slice return setting information, task planning star orbit information and imaging target information required in a cooperative period; wherein the content of the first and second substances,
the cooperative task setting information comprises a star cluster cooperative task number, a cooperative mode, the star state establishing time of each member, the task cooperative duration, the load starting state and a slice return object;
the ground preset imaging target information comprises an imaging target effective mark, a target number, longitude and latitude, a working mode, imaging duration and coagulation and scanning length;
the slice return setting information comprises a slice return task state, a slice return object and a slice return process starting moment;
the task planning satellite orbit information comprises a planning satellite orbit timestamp second count, a planning satellite orbit microsecond count, a planning satellite position coordinate in a WGS84 coordinate system, a planning satellite speed coordinate in a WGS84 coordinate system, a planning satellite position coordinate in a J2000 coordinate system, and a planning satellite speed coordinate in a J2000 coordinate system;
the imaging target information comprises an imaging target number, imaging target longitude and latitude, an imaging target working mode, imaging target imaging duration and imaging target hyperspectral star coagulation scanning length.
The planning star can send the cooperative scheduling data packet to the member star, and the member star can set the working state of the member star during the cooperative task according to the data information in the cooperative scheduling data and execute the actions of cooperative related imaging, data transmission and the like.
For the above possible implementation, in some examples, the status feedback packet includes: the member satellite orbit data, the attitude data of the member satellite, the inter-satellite data transmission data of the member satellite and the data feedback of the member satellite; wherein the content of the first and second substances,
the member satellite orbit data comprise orbit timestamp second counts and microsecond in seconds counts, position coordinates of a WGS84 coordinate system, speed coordinates of a WGS84 coordinate system, position coordinates of a J2000 coordinate system and speed coordinates of the J2000 coordinate system;
the attitude data of the member star comprises a rolling attitude angle, a pitching attitude angle and a yawing attitude angle;
the inter-satellite data transmission data of the member satellite comprises a credible mark of the latest moment at which the data transmission data can be transmitted, data transmission duration requirements, the latest moment at which the data transmission can be transmitted, feedback of the inter-satellite high-speed transmission starting time of the member satellite, feedback of the inter-satellite high-speed transmission ending time of the member satellite and feedback of the inter-satellite high-speed transmission state;
the data feedback of the member star comprises the total target receiving count of the member star, the planned imageable target number of the member star, the planned imageable target numbers of the member star, the planned non-imageable target number of the member star, the planned non-imageable target numbers of the member star, the received latest task number feedback and the load image acquisition state feedback.
For the above possible implementation, in some examples, the inter-satellite bootstrap packet includes: the method comprises the steps of identifying data field types, guiding target numbers and multiple inter-satellite guiding target information; wherein the content of the first and second substances,
the inter-satellite guiding target information consists of a target number, attribute information of a target and longitude and latitude of the target; the attribute information of the target comprises the signal-to-noise-ratio of the target, the type of the target, the confidence level of the target, the external dimension of the target and the importance of the target.
For the technical solution described in fig. 1, in some possible embodiments, designing the inter-satellite data packet interaction protocol between the planning satellite and each member satellite based on the designed inter-satellite data packet includes:
designing the cooperative scheduling data packet to be sent to the member star by the planning star for starting a cooperative task;
designing the state feedback data packet to be sent to the planning star by each member star through an inter-star low-speed network, wherein the state feedback data packet is used for the planning star to acquire state feedback information of each member star;
and designing the inter-satellite guiding data packet, packaging the found target information by each member satellite, and sending the target information to the planning satellite for planning the cooperative task.
The method has the advantages that the interaction of data among the planets and the member satellites is realized by receiving or sending the cooperative scheduling data packet, the state feedback data packet and the inter-satellite guiding data packet, the inter-satellite information interaction is carried out through the inter-satellite low-speed network, the protocol format of the inter-satellite information interaction follows the inter-satellite low-speed packet format, and the technical support can be provided for each link of the multi-satellite task cooperation on orbit.
For the technical solution shown in fig. 1, in some possible embodiments, the planning and executing a multi-satellite cooperative task based on the inter-satellite data packet interaction protocol according to a set timing rule includes:
the planning star sends the cooperative scheduling data packet to each member star every 1 minute from T0-30 minutes; transmitting the cooperative scheduling data packet to each member satellite every 3 seconds from T0-3 minutes; starting the cooperative task until T0 moment;
the member satellite receives the cooperative scheduling data packet sent by the planning satellite, and sets the working state of the member satellite, so that the member satellite has imaging conditions at the time of T0 and starts an electromagnetic signal detection load; wherein each member satellite sends the status feedback data packet to the planning satellite every 3 seconds from T0-3 minutes; sending an inter-satellite guidance data packet to the planning satellite every 8-40 seconds, wherein each inter-satellite guidance data packet at most contains 10 pieces of target information;
the member star stops sending the inter-satellite data packet to the planning star at the time of T0+ dT, and executes load shutdown and posture-to-day orientation state recovery operations;
after the planning satellite is at the time of the cooperative task T0+ dT, executing a stand-alone shutdown instruction chain except for the data server and executing a ground program-controlled satellite-ground data transmission task, and after the execution is finished, executing sun-to-day directional operation;
wherein T0 represents the start time of the collaborative task; dT represents the duration of the collaborative task.
Specifically, as shown in fig. 3, after the multi-satellite task cooperation starts, by defining the transmission time of the cooperative scheduling packet, the state feedback packet, and the inter-satellite guidance packet, efficient and accurate inter-satellite information interaction can be achieved. In the specific implementation process, a resident task central point is preset on the ground, a resident task triggering effective radius jointly defines a plurality of ground circular areas, when a satellite cluster sub-satellite point exists a top window for the circular area, basic conditions for starting the cooperative tasks in the area are considered to be met, meanwhile, the solar altitude in the time period needs to meet the requirement of a minimum solar altitude angle, T0 and dT of the cooperative element task are determined according to the window time and the area radius, wherein T0 is the starting time of the multi-satellite cooperative task, and dT is the cooperative duration.
In the specific implementation process, considering the situation that a low-speed network between sun-oriented satellites may be sporadically invisible, the planning satellite starts to send an adjacent cooperative task to each member satellite in T0-30 minutes, the same cooperative scheduling data packet is sent to each member satellite every 1 minute, and the frequency of sending the cooperative scheduling data packets is increased to every 3 seconds from T0-3 minutes until a stable interaction state after T0 is entered. Note that each satellite turns on its own load before time T0 to satisfy the cooperative condition.
Meanwhile, after the member satellite receives the cooperative scheduling data packet sent by the planning satellite, the member satellite sets the working state of the member satellite so as to realize that the member satellite has the imaging condition at the time of T0 and starts the electromagnetic signal detection load. It should be noted that the status feedback data packet of each member satellite starts to be sent to the planning satellite in the time T0-3 minutes, and is sent every 3 seconds, so that each member satellite has the capability of on-orbit adjustment period.
In addition, the inter-satellite guiding data packet is sent to the planning satellite once every 8-40 seconds, the sending frequency can be adjusted according to the actual situation every 8 seconds in the actual implementation process, and each inter-satellite guiding data packet contains 10 pieces of target information at most. It should be noted that the inter-satellite guidance packet preferentially sends the electromagnetic signal detection target information found in the wide area, and then the electromagnetic signal detection target information found in the single wide area.
And finally, stopping inter-satellite data transmission and executing on-satellite state recovery operations such as load shutdown and attitude-to-sun orientation when each member satellite receives T0+ dT of the cooperative task. And after the planning satellite sends the cooperative task T0+ dT, firstly executing a stand-alone shutdown instruction chain except for the data server, immediately executing a ground program control satellite-ground data transmission task, and after the execution is finished, executing a sun-oriented recovery operation.
Based on the same inventive concept of the foregoing technical solution, referring to fig. 4, it shows a device 40 for multi-satellite cooperative on-orbit information interaction protocol and time sequence design provided in the embodiment of the present invention, where the device 40 includes: an inter-satellite data packet design part 401, an interaction protocol design part 402 and a planning part 403; wherein the content of the first and second substances,
the inter-satellite data packet designing section 401 is configured to design an inter-satellite data packet by performing classification and packaging on multi-source guidance information received by a planning satellite in real time;
the interaction protocol design section 402 configured to design the inter-satellite packet interaction protocol between the planning satellite and each member satellite based on the designed inter-satellite packet;
the planning part 403 is configured to plan and execute the multi-satellite cooperative task according to a set time sequence rule based on the inter-satellite data packet interaction protocol.
In some examples, the inter-satellite packet design section 401 is configured to:
and classifying and packaging the multi-source guiding information into a cooperative scheduling data packet, a state feedback data packet and an inter-satellite guiding data packet according to the on-satellite and ground multi-source guiding information received by the planning satellite in real time.
In some examples, the inter-satellite packet design section 401 is configured to:
the cooperative task setting information comprises a star cluster cooperative task number, a cooperative mode, the star state establishing time of each member, the task cooperative duration, the load starting state and a slice return object;
the ground preset imaging target information comprises an imaging target effective mark, a target number, longitude and latitude, a working mode, imaging duration and coagulation and scanning length;
the slice return setting information comprises a slice return task state, a slice return object and a slice return process starting moment;
the task planning satellite orbit information comprises a planning satellite orbit timestamp second count, a planning satellite orbit microsecond count, a planning satellite position coordinate in a WGS84 coordinate system, a planning satellite speed coordinate in a WGS84 coordinate system, a planning satellite position coordinate in a J2000 coordinate system, and a planning satellite speed coordinate in a J2000 coordinate system;
the imaging target information comprises an imaging target number, imaging target longitude and latitude, an imaging target working mode, imaging target imaging duration and imaging target hyperspectral star coagulation scanning length.
In some examples, the inter-satellite packet design section 401 is configured to:
the member satellite orbit data comprises orbit timestamp second counting and microsecond-in-second counting, position coordinates of a WGS84 coordinate system, speed coordinates of a WGS84 coordinate system, position coordinates of a J2000 coordinate system and speed coordinates of the J2000 coordinate system;
the attitude data of the member star comprises a rolling attitude angle, a pitching attitude angle and a yawing attitude angle;
the inter-satellite data transmission data of the member satellite comprises a credible mark of the latest moment at which the data transmission data can be transmitted, data transmission duration requirements, the latest moment at which the data transmission can be transmitted, feedback of the inter-satellite high-speed transmission starting time of the member satellite, feedback of the inter-satellite high-speed transmission ending time of the member satellite and feedback of the inter-satellite high-speed transmission state;
the data feedback of the member star comprises the total target receiving count of the member star, the planned imageable target number of the member star, the planned imageable target numbers of the member star, the planned non-imageable target number of the member star, the planned non-imageable target numbers of the member star, the received latest task number feedback and the load image acquisition state feedback.
In some examples, the inter-satellite packet design section 401 is configured to:
the inter-satellite guiding target information consists of a target number, attribute information of a target and longitude and latitude of the target; the attribute information of the target comprises the signal-to-noise-ratio of the target, the type of the target, the confidence level of the target, the external dimension of the target and the importance of the target.
In some examples, the interaction protocol design portion 402 is configured to:
designing the cooperative scheduling data packet to be sent to the member star by the planning star for starting a cooperative task;
designing the state feedback data packet to be sent to the planning star by each member star through an inter-star low-speed network, wherein the state feedback data packet is used for the planning star to acquire state feedback information of each member star;
and designing the inter-satellite guiding data packet, packaging the found target information by each member satellite, and sending the target information to the planning satellite for planning the cooperative task.
In some examples, the staging section 403 is configured to:
the planning star sends the cooperative scheduling data packet to each member star every 1 minute from T0-30 minutes; transmitting the cooperative scheduling data packet to each member satellite every 3 seconds from T0-3 minutes; starting the cooperative task until T0 moment;
the member satellite receives the cooperative scheduling data packet sent by the planning satellite, and sets the working state of the member satellite, so that the member satellite has imaging conditions at the time of T0 and starts an electromagnetic signal detection load; wherein each member satellite sends the status feedback data packet to the planning satellite every 3 seconds from T0-3 minutes; sending an inter-satellite guidance data packet to the planning satellite every 8-40 seconds, wherein each inter-satellite guidance data packet at most contains 10 pieces of target information;
after the cooperative task T0+ dT moment, the member satellite stops sending the inter-satellite data packet to the planning satellite and executes load shutdown and posture-to-day directional state recovery operations;
after the planning satellite is at the time of the cooperative task T0+ dT, executing a stand-alone shutdown instruction chain except for the data server and executing a ground program-controlled satellite-ground data transmission task, and after the execution is finished, executing sun-to-day directional operation;
wherein T0 represents the start time of the collaborative task; dT represents the duration of the collaborative task.
It is understood that in this embodiment, "part" may be part of a circuit, part of a processor, part of a program or software, etc., and may also be a unit, and may also be a module or a non-modular.
In addition, each component in the embodiment may be integrated in one processing unit, or each unit may exist alone physically, or two or more units are integrated in one unit. The integrated unit can be realized in a form of hardware or a form of a software functional module.
Based on the understanding that the technical solution of the present embodiment essentially or a part contributing to the prior art, or all or part of the technical solution may be embodied in the form of a software product stored in a storage medium, and include several instructions for causing a computer device (which may be a personal computer, a server, or a network device, etc.) or a processor (processor) to execute all or part of the steps of the method of the present embodiment. And the aforementioned storage medium includes: a U-disk, a removable hard disk, a Read Only Memory (ROM), a Random Access Memory (RAM), a magnetic disk or an optical disk, and other various media capable of storing program codes.
Therefore, this embodiment provides a computer storage medium, where a multi-satellite collaborative on-orbit information interaction protocol and a time sequence design program are stored, and when the multi-satellite collaborative on-orbit information interaction protocol and the time sequence design program are executed by at least one processor, the steps of the multi-satellite collaborative on-orbit information interaction protocol and the time sequence design method in the foregoing technical solution are implemented.
Referring to fig. 5, a specific hardware structure of a computing device 50 capable of implementing the multi-satellite cooperative on-orbit information interaction protocol and the timing design apparatus 40 according to the above-mentioned multi-satellite cooperative on-orbit information interaction protocol and the timing design apparatus 40 according to the embodiment of the present invention is shown, where the computing device 50 may be a wireless device, a mobile or cellular phone (including a so-called smart phone), a Personal Digital Assistant (PDA), a video game console (including a video display, a mobile video game device, and a mobile video conference unit), a laptop computer, a desktop computer, a television set-top box, a tablet computing device, an e-book reader, a fixed or mobile media player, and so on. The computing device 50 includes: a communication interface 501, a memory 502, and a processor 503; the various components are coupled together by a bus system 504. It is understood that the bus system 504 is used to enable communications among the components. The bus system 504 includes a power bus, a control bus, and a status signal bus in addition to a data bus. For clarity of illustration, however, the various buses are labeled as bus system 504 in figure X. Wherein, the first and the second end of the pipe are connected with each other,
the communication interface 501 is used for receiving and sending signals in the process of receiving and sending information with other external network elements;
the memory 502 for storing a computer program capable of running on the processor 503;
the processor 503 is configured to, when running the computer program, perform the following steps:
classifying and packaging multi-source guiding information received by a planning satellite in real time to design an inter-satellite data packet;
designing the inter-satellite data packet interaction protocol between the planning satellite and each member satellite based on the designed inter-satellite data packet;
and planning and executing the multi-satellite cooperative task based on the inter-satellite data packet interaction protocol according to a set time sequence rule.
It is to be understood that the memory 502 in embodiments of the present invention may be either volatile memory or nonvolatile memory, or may include both volatile and nonvolatile memory. The non-volatile Memory may be a Read-Only Memory (ROM), a Programmable ROM (PROM), an Erasable PROM (EPROM), an Electrically Erasable PROM (EEPROM), or a flash Memory. Volatile Memory can be Random Access Memory (RAM), which acts as external cache Memory. By way of illustration and not limitation, many forms of RAM are available, such as Static random access memory (Static RAM, SRAM), Dynamic Random Access Memory (DRAM), Synchronous Dynamic random access memory (Synchronous DRAM, SDRAM), Double Data Rate Synchronous Dynamic random access memory (ddr Data Rate SDRAM, ddr SDRAM), Enhanced Synchronous SDRAM (ESDRAM), Synchlink DRAM (SLDRAM), and Direct Rambus RAM (DRRAM). The memory 502 of the systems and methods described herein is intended to comprise, without being limited to, these and any other suitable types of memory.
And the processor 503 may be an integrated circuit chip having signal processing capabilities. In implementation, the steps of the above method may be performed by integrated logic circuits of hardware or instructions in the form of software in the processor 503. The Processor 503 may be a general purpose Processor, a Digital Signal Processor (DSP), an Application Specific Integrated Circuit (ASIC), a Field Programmable Gate Array (FPGA) or other Programmable logic device, discrete Gate or transistor logic device, or discrete hardware components. The various methods, steps and logic blocks disclosed in the embodiments of the present invention may be implemented or performed. A general purpose processor may be a microprocessor or the processor may be any conventional processor or the like. The steps of the method disclosed in connection with the embodiments of the present invention may be directly implemented by a hardware decoding processor, or implemented by a combination of hardware and software modules in the decoding processor. The software module may be located in ram, flash memory, rom, prom, or eprom, registers, etc. storage media as is well known in the art. The storage medium is located in the memory 502, and the processor 503 reads the information in the memory 502 and completes the steps of the above method in combination with the hardware thereof.
It is to be understood that the embodiments described herein may be implemented in hardware, software, firmware, middleware, microcode, or any combination thereof. For a hardware implementation, the Processing units may be implemented within one or more Application Specific Integrated Circuits (ASICs), Digital Signal Processors (DSPs), Digital Signal Processing Devices (DSPDs), Programmable Logic Devices (PLDs), Field Programmable Gate Arrays (FPGAs), general purpose processors, controllers, micro-controllers, microprocessors, other electronic units configured to perform the functions described herein, or a combination thereof.
For a software implementation, the techniques described herein may be implemented with modules (e.g., procedures, functions, and so on) that perform the functions described herein. The software codes may be stored in a memory and executed by a processor. The memory may be implemented within the processor or external to the processor.
Specifically, when the processor 503 is further configured to run the computer program, the steps of the multi-satellite cooperative on-orbit information interaction protocol and the time sequence design method in the foregoing technical solution are executed, which are not described herein again.
It should be noted that: the technical schemes described in the embodiments of the present invention can be combined arbitrarily without conflict.
The above description is only for the specific embodiments of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive of the changes or substitutions within the technical scope of the present invention, and all the changes or substitutions should be covered within the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Claims (10)
1. A multi-satellite cooperative on-orbit information interaction protocol and a time sequence design method are characterized by comprising the following steps:
classifying and packaging multi-source guiding information received by a planning satellite in real time to design an inter-satellite data packet;
designing the inter-satellite data packet interaction protocol between the planning satellite and each member satellite based on the designed inter-satellite data packet;
and planning and executing the multi-satellite cooperative task based on the inter-satellite data packet interaction protocol according to a set time sequence rule.
2. The method of claim 1, wherein designing the inter-satellite data packet by sorting the multi-source guiding information received by the planning satellite in real time comprises:
and according to the multi-source guiding information on the satellite and on the ground received by the planning satellite in real time, classifying and packaging the multi-source guiding information into a cooperative scheduling data packet, a state feedback data packet and an inter-satellite guiding data packet.
3. The method of claim 2, wherein the co-scheduling packet comprises: setting information of a cooperative task, ground preset imaging target information, slice return setting information, task planning star orbit information and imaging target information required in a cooperative period; wherein, the first and the second end of the pipe are connected with each other,
the cooperative task setting information comprises a star cluster cooperative task number, a cooperative mode, the star state establishing time of each member, the task cooperative duration, the load starting state and a slice return object;
the ground preset imaging target information comprises an imaging target effective mark, a target number, longitude and latitude, a working mode, imaging duration and coagulation and scanning length;
the slice returning setting information comprises a slice returning task state, a slice returning object and a slice returning process starting moment;
the task planning satellite orbit information comprises a planning satellite orbit timestamp second count, a planning satellite orbit microsecond count within a second timestamp, a position coordinate of the planning satellite in a WGS84 coordinate system, a speed coordinate of the planning satellite in a WGS84 coordinate system, a position coordinate of the planning satellite in a J2000 coordinate system and a speed coordinate of the planning satellite in the J2000 coordinate system;
the imaging target information comprises an imaging target number, imaging target longitude and latitude, an imaging target working mode, imaging target imaging duration and imaging target hyperspectral star coagulation scanning length.
4. The method of claim 2, wherein the status feedback packet comprises: the member satellite orbit data, the attitude data of the member satellite, the inter-satellite data transmission data of the member satellite and the data feedback of the member satellite; wherein the content of the first and second substances,
the member satellite orbit data comprises orbit timestamp second counting and microsecond-in-second counting, position coordinates of a WGS84 coordinate system, speed coordinates of a WGS84 coordinate system, position coordinates of a J2000 coordinate system and speed coordinates of the J2000 coordinate system;
the attitude data of the member star comprises a rolling attitude angle, a pitching attitude angle and a yawing attitude angle;
the inter-satellite data transmission data of the member satellite comprises a credible mark of the latest moment at which the data transmission data can be transmitted, data transmission duration requirements, the latest moment at which the data transmission can be transmitted, feedback of the inter-satellite high-speed transmission starting time of the member satellite, feedback of the inter-satellite high-speed transmission ending time of the member satellite and feedback of the inter-satellite high-speed transmission state;
the data feedback of the member star comprises the total target receiving count of the member star, the planned imageable target number of the member star, the planned imageable target numbers of the member star, the planned non-imageable target number of the member star, the planned non-imageable target numbers of the member star, the received latest task number feedback and the load image acquisition state feedback.
5. The method of claim 2, wherein the inter-satellite bootstrap packet comprises: the method comprises the steps of identifying data field types, guiding target numbers and multiple inter-satellite guiding target information; wherein, the first and the second end of the pipe are connected with each other,
the inter-satellite guiding target information consists of a target number, attribute information of a target and longitude and latitude of the target; the attribute information of the target comprises a signal-to-noise ratio of the target, a target type, a target confidence coefficient, an external dimension of the target and an importance degree of the target.
6. The method of claim 2, wherein designing the inter-satellite packet interaction protocol between the planning satellite and each member satellite based on the designed inter-satellite packet comprises:
designing the cooperative scheduling data packet to be sent to the member star by the planning star for starting a cooperative task;
designing the state feedback data packet to be sent to the planning star by each member star through an inter-star low-speed network, wherein the state feedback data packet is used for the planning star to acquire state feedback information of each member star;
and designing the inter-satellite guiding data packet, packaging the found target information by each member satellite, and sending the target information to the planning satellite for planning the cooperative task.
7. The method of claim 2, wherein the planning and executing the multi-satellite cooperative task based on the inter-satellite data packet interaction protocol according to the set timing rule comprises:
the planning star sends the cooperative scheduling data packet to each member star every 1 minute from T0-30 minutes; transmitting the cooperative scheduling data packet to each member satellite every 3 seconds from T0-3 minutes; starting the cooperative task until T0 moment;
the member satellite receives the cooperative scheduling data packet sent by the planning satellite, and sets the working state of the member satellite, so that the member satellite has imaging conditions at the time of T0 and starts an electromagnetic signal detection load; wherein each member satellite sends the status feedback data packet to the planning satellite every 3 seconds from T0-3 minutes; sending an inter-satellite guidance data packet to the planning satellite every 8-40 seconds, wherein each inter-satellite guidance data packet at most contains 10 pieces of target information;
after the cooperative task T0+ dT moment, the member satellite stops sending the inter-satellite data packet to the planning satellite and executes load shutdown and posture-to-day directional state recovery operations;
after the planning satellite is at the time of the cooperative task T0+ dT, executing a stand-alone shutdown instruction chain except for the data server and executing a ground program-controlled satellite-ground data transmission task, and after the execution is finished, executing sun-to-day directional operation;
wherein T0 represents the start time of the collaborative task; dT represents the duration of the collaborative task.
8. A multi-satellite cooperative on-orbit information interaction protocol and timing design device is characterized by comprising: an inter-satellite data packet design part, an interaction protocol design part and a planning part; wherein the content of the first and second substances,
the inter-satellite data packet design part is configured to design an inter-satellite data packet by classifying and packaging multi-source guide information received by a planning satellite in real time;
the interaction protocol design part is configured to design the inter-satellite data packet interaction protocol between the planning satellite and each member satellite based on the designed inter-satellite data packet;
the planning part is configured to plan and execute the multi-satellite cooperative task according to a set time sequence rule based on the inter-satellite data packet interaction protocol.
9. A computing device, wherein the computing device comprises: a communication interface, a memory and a processor; the various components are coupled together by a bus system in which,
the communication interface is used for receiving and sending signals in the process of receiving and sending information with other external network elements;
the memory for storing a computer program operable on the processor;
the processor is configured to execute the steps of the multi-satellite cooperative on-orbit information exchange protocol and the time sequence design method according to any one of claims 1 to 7 when the computer program is run.
10. A computer storage medium having stored thereon a multi-satellite cooperative in-orbit information exchange protocol and a timing design program, the multi-satellite cooperative in-orbit information exchange protocol and the timing design program when executed by at least one processor implementing the steps of the multi-satellite cooperative in-orbit information exchange protocol and the timing design method of any of claims 1 to 7.
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