CN102801435A - C3I system applicable to small satellite launch site - Google Patents
C3I system applicable to small satellite launch site Download PDFInfo
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- CN102801435A CN102801435A CN2012102229088A CN201210222908A CN102801435A CN 102801435 A CN102801435 A CN 102801435A CN 2012102229088 A CN2012102229088 A CN 2012102229088A CN 201210222908 A CN201210222908 A CN 201210222908A CN 102801435 A CN102801435 A CN 102801435A
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Abstract
The invention discloses a C3I system applicable to a small satellite launch site, comprising a launch site C3I system, a main testing processor, a parameter transmitting module, a parameter subscription module, a first data returning module and a second data returning module. Before a satellite is launched, the parameter subscription module receives a parameter engineering value which is remotely measured by a main testing computer according to a remotely-measured parameter number of each satellite, and sends the parameter engineering value to the parameter transmitting module; and the parameter transmitting module sends the received remotely-measured parameter value to the C3I system of the launch site. After the satellite is launched, the first data returning module receives remotely-measured original code values of the different satellites from the C3I system of the launch site, converts the remotely-measured original code values into a remotely-measured frames used by a satellite testing net and sends the remotely-measured frames to the second data returning module; and the second data returning module sends the original frames to the main testing computer and are analyzed by the main testing computer. With the adoption of the C3I system applicable to the small satellite launch site disclosed by the invention, the communication problem among a plurality of the satellites and the launch site can be solved.
Description
Technical field
The present invention relates to a kind of C that is applicable to that the moonlet launching site is used
3The I system.
Background technology
Moonlet launching site C
3I (Command, Control, Communications & Intelligence) system is mainly used in commander, control, the coordination of accomplishing launching site and satellite system, and makes decisions simultaneously.Before the satellites transmits, satellite C
3The I system is to launching site C
3The I system sends the satellite telemetry decode value of agreement in advance, the running status of each subsystem of satellite is provided, launching site C
3The I system is to satellite C
3The I system sends information such as weather, commander; After the satellites transmits, launching site C
3The I system sends to satellite C with the form of satellite telemetry true form information with satellite survey photos and sending messages frame format
3In the I system, satellite C
3The I system surveys the form that the photos and sending messages frame is processed into the remote measurement true form with satellite, and sends it to the satellite test net, and the satellite test net is resolved the remote measurement oss message, obtains satellite data in orbit, will resolve good data simultaneously and send to Test Network.
Present moonlet launching site C
3The I system mainly is applicable to single satellite mode, the C under single satellite mode
3The employing of I system is point-to-point carries out communication with group broadcast mode and launching site, and Fig. 1 provides a typical moonlet C
3I system and launching site C
3The composition sketch map of I system.Among Fig. 1, this system comprises satellite network and C
3The interface computer of I system, satellite network switch mainly are responsible for the obtaining of satellite test data, data parsing, storage, exchanges data, data and are shown.
Along with the development of moonlet, the launching site has engendered the emission mode of several satellite in a rocket, C under existing single star pattern
3The I system can only provide single satellite test network and launching site C
3The communication function of I system in addition, owing to the limitation of its logical construction, has influenced the performance of system, can not satisfy many stars whiles and launching site C
3The requirement of I system communication.
Summary of the invention
Technology of the present invention is dealt with problems and is: to the deficiency of prior art, a kind of C that is applicable to that the moonlet launching site is used is provided
3The I system.Adopt the present invention can solve the communication issue between a plurality of satellites whiles and the launching site.
Technical solution of the present invention is:
A kind of C that is applicable to that the moonlet launching site is used
3The I system comprises: launching site C
3I system, main test handler, parameter forwarding module, parameter subscribing module, the first returning data module, the second returning data module,
Before the satellites transmits, said parameter subscribing module number receives the telemetry parameter engineering value of being returned by said main test computer corresponding to the telemetry parameter of said each satellite number according to the telemetry parameter of multi-satellite, and sends to said parameter forwarding module; Said parameter forwarding module is transmitted to launching site C with the telemetry parameter engineering value that receives
3The I system;
After the satellites transmits, the said first returning data module is from said launching site C
3The I system receives the former code value of remote measurement of different satellites, and sends to the second returning data module after the former code value of remote measurement is converted into the telemetry frame that the satellite test net uses; The said second returning data module sends to main test handler with primitive frame, is resolved by main test handler.
Further, said parameter subscribing module is distinguished satellite through list, records the telemetry parameter name of subscribing to main test computer and telemetry parameter number on the list corresponding to each satellite.
Further, said parameter forwarding module sends to said launching site C after the telemetry parameter engineering value on said each satellite list is organized into information frame
3The I system.
The present invention compared with prior art has following advantage:
(1) the present invention adopts modularized design, is main functional modules with functional modules such as parameter forwarding module, parameter subscribing module, the first returning data module, the second returning data modules, optimizes and the workflow of clear and definite system before emission, after the emission.Be applicable to the launching site task of single satellite or multi-satellite simultaneously;
(2) the present invention adopts object-oriented analysis and method for designing, follows the modularization design principle, and is clear and definite and optimized data structure, the handling process of module, guarantees level, the call relation of intermodule, can improve running efficiency of system;
(3) existing C
3The I system compares, and the present invention can carry out system's setting of multi-satellite through the page configuration item, satisfies the configuration requirement of different task.Simultaneously, utilize list that the subscription parameters of multi-satellite is distinguished, the configuration list can be changed flexibly, and the change back only need import again and get final product.Native system has flexibility, reusability, and same version program can be accomplished the launching site work of multi-satellite;
(4) each module of the present invention is divided according to mission requirements, and definite functions and separate can be accomplished functions such as data parsing, data format processing, data demonstration, storage respectively.Simultaneously, the intermodule close ties are accomplished Data Receiving, the data of intermodule and are sent through corresponding external interface.As: parameter forwarding module, the first returning data module need be accomplished data processing, will accomplish simultaneously and launching site C
3The exchanges data of I; The subscription parameters module need subscribe to the telemetry parameter of answering to main test handler accomplishing the reading of list, verification through different port numbers; The second returning data module need be responsible for carrying out communication with main test handler after emission, and data are passed to Test Network.
Description of drawings
Fig. 1 is moonlet C
3I system and launching site C
3The composition sketch map of I system;
Fig. 2 is a sketch map of the present invention;
Fig. 3 is the parameter subscribing module;
Fig. 4 is a parameter forwarding module sketch map;
Fig. 5 is that the first returning data module receives the transmission schematic diagram data;
Fig. 6 is that the second returning data module is sent schematic diagram data;
Fig. 7 is the preceding flow chart of emission;
Fig. 8 is emission back flow chart.
Embodiment
Just combine accompanying drawing that the present invention is done further introduction below.
As shown in Figure 2, the C that is applicable to that the moonlet launching site is used according to the invention
3The I system comprises: launching site C
3I system, main test handler, parameter forwarding module, parameter subscribing module, the first returning data module, the second returning data module, display module, data memory module.
Before the emission; The subscription parameters module is responsible for to main test handler (MTP; Main Test Processor) subscription parameters, MTP number returns corresponding remote measurement engineering value to said subscription parameters module according to what the subscription parameters module was sent corresponding to the telemetry parameter of each satellite.The subscription parameters module is exported to the parameter forwarding module with the remote measurement engineering value that obtains and according to communications protocol format the remote measurement engineering value is packaged into information frame by the parameter forwarding module, and information frame is transmitted to the C at launching site
3The I system exports to launching site C
3The remote measurement engineering value of I system also can be used for exporting display module and shows.
As shown in Figure 3, in the parameter subscribing module, the telemetry parameter that sends to each satellite of MTP number is distinguished different satellites through list.For example, for three satellite A, B, C utilize respectively single table choose a little _ A, single table choose a little _ B, single table choose a little _ C writes down telemetry parameter that the needs of corresponding satellite subscribe to number.The parameter subscribing module is through reading 3 telemetry parameter tables; Telemetry parameter number is sent to MTP, number return corresponding telemetry parameter engineering value according to telemetry parameter respectively corresponding to 3 process MTP_A of satellite A, B, C, MTP_B, MTP_C among the MTP to the parameter subscribing module.In the parameter subscribing module, can support simultaneously to carry out exchanges data, can satisfy the mission requirements of several satellite in a rocket with a plurality of MTP.
Under many stars pattern, when MTP sends corresponding to the telemetry parameter in the list of different satellites, need the network address and the port numbers of configuration MTP.As: the network address of the corresponding MTP of satellite A is 192.9.200.10, and port is 4003; The network address of the corresponding MTP of satellite B is 192.9.200.10, and port is 4103; The network address of the corresponding MTP of satellite C is 192.9.200.10, and port is 4203.
As shown in Figure 4, in the parameter forwarding module, at first read the telemetry parameter engineering value that is kept in the temporary variable, according to the communication protocol that is applicable to this satellite the telemetry parameter engineering value is packaged into information frame then, send to launching site C through the multicast mode then
3The I system is up to requiring to stop transmission
The first returning data module receives by receiving launching site C
3The I system sends to moonlet C
3The weather data of I system, commander's information, and export to display module after said antenna data, commander's information resolved and show.As shown in Figure 5, receive from launching site C in the first passback data module
3After the information that includes weather data, command data of I system, the agreement according to communication protocol is resolved information, again weather data that obtains and command data are sent to the display module demonstration.
After the emission, the first returning data module receives by launching site C
3The former code value of remote measurement corresponding to different satellites of I system passback utilizes data memory module to store the former code value of said remote measurement.Simultaneously, the said first returning data module sends to the second returning data module after the former code value of said remote measurement is converted into the telemetry frame that the satellite test net uses, and by the second returning data module telemetry frame that receives is sent to MTP.
As shown in Figure 6, the second returning data module at first is connected MTP according to the address with port numbers, sends the information of registering to MTP, then with MTP to the time, send spontaneous emission field C to MTP once more
3The telemetry frame of I system.Send to the different processes of MTP corresponding to the telemetry frame correspondence of different satellites, thereby realized satisfying the mission requirements of several satellite in a rocket.
As shown in Figure 7, before emission, set MTP address, port; Single-point table systems inspection point tableau format in loading procedure that loading is made according to communications protocol; Mistake occurs like form, then program stops to continue to carry out and return, and revises correct up to a sheet format.Load correctly like a table, then the telemetry parameter in MTP subscription point table is failed if subscribe to, and program is returned, if subscribe to successfully, then subscription data is shown, and according to the transmission that is provided with at interval, the while generates information frame according to communication protocol, to launching site C
3The I system sends information frame, up to stopping transmission.
As shown in Figure 8, after emission, set launching site C
3The address of I system, port begin to receive launching site C
3The data to the satellite test net are sent out by the I system, if accepting state is correct, then data are carried out format conversion, the primitive frame remote measurement that converts are sent out to MTP, up to stopping transmission.
The unspecified part of the present invention belongs to general knowledge as well known to those skilled in the art.
Claims (3)
1. C who is applicable to that the moonlet launching site is used
3The I system is characterized in that comprising: launching site C
3I system, main test handler, parameter forwarding module, parameter subscribing module, the first returning data module, the second returning data module,
Before the satellites transmits, said parameter subscribing module number receives the telemetry parameter engineering value of being returned by said main test computer corresponding to the telemetry parameter of said each satellite number according to the telemetry parameter of multi-satellite, and sends to said parameter forwarding module; Said parameter forwarding module is transmitted to launching site C with the telemetry parameter engineering value that receives
3The I system;
After the satellites transmits, the said first returning data module is from said launching site C
3The I system receives the former code value of remote measurement of different satellites, and sends to the second returning data module after the former code value of remote measurement is converted into the telemetry frame that the satellite test net uses; The said second returning data module sends to main test handler with primitive frame, is resolved by main test handler.
2. a kind of C that is applicable to that the moonlet launching site is used as claimed in claim 1
3The I system is characterized in that: said parameter subscribing module is distinguished satellite through list, records the telemetry parameter name of subscribing to main test computer and telemetry parameter number on the list corresponding to each satellite.
3. a kind of C that is applicable to that the moonlet launching site is used as claimed in claim 1
3The I system is characterized in that: said parameter forwarding module sends to said launching site C after the telemetry parameter engineering value on said each satellite list is organized into information frame
3The I system.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201210222908.8A CN102801435B (en) | 2012-06-28 | 2012-06-28 | A kind of C being applicable to moonlet launching site and using 3i system |
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| CN201210222908.8A CN102801435B (en) | 2012-06-28 | 2012-06-28 | A kind of C being applicable to moonlet launching site and using 3i system |
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| CN102801435A true CN102801435A (en) | 2012-11-28 |
| CN102801435B CN102801435B (en) | 2015-08-05 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107632844A (en) * | 2017-07-28 | 2018-01-26 | 上海航天电子有限公司 | Remote measurement multi-format framing method for satellite test |
| CN111161524A (en) * | 2019-12-11 | 2020-05-15 | 北京东方计量测试研究所 | Testing device |
| CN113993003A (en) * | 2021-09-18 | 2022-01-28 | 深圳航天东方红卫星有限公司 | Multi-satellite parallel data forwarding system and method |
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| US20040085976A1 (en) * | 2002-11-06 | 2004-05-06 | Mark Dale | Downstream time domian based adaptive modulation for DOCSIS based applications |
| CN101039139A (en) * | 2007-03-16 | 2007-09-19 | 北京航空航天大学 | Space-based mobile communication system and communication method |
| CN101145825A (en) * | 2007-10-30 | 2008-03-19 | 航天东方红卫星有限公司 | Small satellite satellite-ground communication integrated system |
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2012
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040085976A1 (en) * | 2002-11-06 | 2004-05-06 | Mark Dale | Downstream time domian based adaptive modulation for DOCSIS based applications |
| CN101039139A (en) * | 2007-03-16 | 2007-09-19 | 北京航空航天大学 | Space-based mobile communication system and communication method |
| CN101145825A (en) * | 2007-10-30 | 2008-03-19 | 航天东方红卫星有限公司 | Small satellite satellite-ground communication integrated system |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107632844A (en) * | 2017-07-28 | 2018-01-26 | 上海航天电子有限公司 | Remote measurement multi-format framing method for satellite test |
| CN107632844B (en) * | 2017-07-28 | 2023-07-18 | 上海航天电子有限公司 | Telemetry multi-format framing method for satellite test |
| CN111161524A (en) * | 2019-12-11 | 2020-05-15 | 北京东方计量测试研究所 | Testing device |
| CN113993003A (en) * | 2021-09-18 | 2022-01-28 | 深圳航天东方红卫星有限公司 | Multi-satellite parallel data forwarding system and method |
| CN113993003B (en) * | 2021-09-18 | 2023-12-26 | 深圳航天东方红卫星有限公司 | Multi-satellite parallel data forwarding system and method |
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| CN102801435B (en) | 2015-08-05 |
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