CN102801435B - A kind of C being applicable to moonlet launching site and using 3i system - Google Patents
A kind of C being applicable to moonlet launching site and using 3i system Download PDFInfo
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- CN102801435B CN102801435B CN201210222908.8A CN201210222908A CN102801435B CN 102801435 B CN102801435 B CN 102801435B CN 201210222908 A CN201210222908 A CN 201210222908A CN 102801435 B CN102801435 B CN 102801435B
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Abstract
The invention discloses a kind of C being applicable to moonlet launching site and using
3i system, comprising: launching site C
3i system, main test handler, parameter forwarding module, parameter subscribing module, the first data back module, the second data back module.Before satellite launch, described parameter subscribing module receives by described main test computer telemetry parameter engineering value according to the telemetry parameter of each satellite number, and sends to described parameter forwarding module; The telemetry parameter engineering value received is transmitted to launching site C by described parameter forwarding module
3i system.After satellite launch, described first data back module is from described launching site C
3the remote measurement true form value of the different satellite of I system acceptance, and be sent to the second data back module after remote measurement true form value being converted into the telemetry frame of satellite test net use; Primitive frame is sent to main test handler by described second data back module, is resolved by main test handler.Adopt the present invention can solve the communication issue of multiple satellite simultaneously and between launching site.
Description
Technical field
The present invention relates to a kind of C being applicable to moonlet launching site and using
3i system.
Background technology
Moonlet launching site C
3i (Command, Control, Communications & Intelligence) system has been mainly used in the commander of launching site and satellite system, control, coordination, and makes decisions simultaneously.Before satellite launch, satellite C
3i system is to launching site C
3i system sends the satellite telemetry decode value of in advance arranging, and provides the running status of each subsystem of satellite, launching site C
3i system is to satellite C
3i system sends the information such as weather, commander; After satellite launch, launching site C
3satellite telemetry true form information is surveyed the form of photos and sending messages frame format by I system with satellite, be sent to satellite C
3in I system, satellite C
3satellite is surveyed the form that photos and sending messages frame is processed into remote measurement true form by I system, and sends it to satellite test net, and remote measurement oss message is resolved by satellite test net, obtains satellite data in orbit, the data of having resolved is sent to Test Network simultaneously.
Current moonlet launching site C
3i system is mainly 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 schematic diagram of I system.In Fig. 1, this system comprises satellite network and C
3the interface computer of I system, satellite network switch, the acquisition of primary responsibility satellite test data, Data Analysis, data storage, exchanges data, data display.
Along with the development of moonlet, launching site has engendered the emission mode of several satellite in a rocket, C under existing single star pattern
3i system, can only provide single satellite test network and launching site C
3the communication function of I system, in addition, due to the limitation of its logical construction, have impact on the performance of system, can not meet many stars simultaneously with launching site C
3the requirement of I system communication.
Summary of the invention
Technology of the present invention is dealt with problems and is: for the deficiencies in the prior art, provides a kind of C being applicable to moonlet launching site and using
3i system.Adopt the present invention can solve the communication issue of multiple satellite simultaneously and between launching site.
Technical solution of the present invention is:
A kind of C being applicable to moonlet launching site and using
3i system, comprising: launching site C
3i system, main test handler, parameter forwarding module, parameter subscribing module, the first data back module, the second data back module,
Before satellite launch, described parameter subscribing module receives the telemetry parameter engineering value of the telemetry parameter corresponding to described each satellite that returned by described main test computer number according to the telemetry parameter of multi-satellite number, and sends to described parameter forwarding module; The telemetry parameter engineering value received is transmitted to launching site C by described parameter forwarding module
3i system;
After satellite launch, described first data back module is from described launching site C
3the remote measurement true form value of the different satellite of I system acceptance, and be sent to the second data back module after remote measurement true form value being converted into the telemetry frame of satellite test net use; Primitive frame is sent to main test handler by described second data back module, is resolved by main test handler.
Further, described parameter subscribing module is distinguished satellite by list, the list corresponding to each satellite records the telemetry parameter name and telemetry parameter number of subscribing to main test computer.
Further, described parameter forwarding module is sent to described launching site C after the telemetry parameter engineering value on described each satellite list is organized into information frame
3i system.
The present invention compared with prior art tool has the following advantages:
(1) the present invention adopts modularized design, with functional modules such as parameter forwarding module, parameter subscribing module, the first data back module, the second data back modules for main functional modules, optimize and specify that system before transmission, launch after workflow.Be applicable to the launching site task of single satellite or multi-satellite simultaneously;
(2) the present invention adopts object-oriented system analysis and design method, follows modular design principle, clear and definite and optimize data structure, the handling process of module, guarantees the level of intermodule, call relation, can improve running efficiency of system;
(3) existing C
3i system is compared, and the present invention can carry out the Operation system setting of multi-satellite by page configuration item, meet the configuration requirement of different task.Meanwhile, utilize the subscription parameters of list to multi-satellite to distinguish, configuration list can be changed flexibly, only needs again to import after change.Native system has flexibility, reusability, and same version program can complete the launching site work of multi-satellite;
(4) each module of the present invention divides according to mission requirements, definite functions and separate, can complete the functions such as Data Analysis, data format process, data display, data storage respectively.Meanwhile, intermodule is maintained close ties with, and is completed data receiver, the data transmission of intermodule by corresponding external interface.As: parameter forwarding module, the first data back module have needed data processing, will complete and launching site C simultaneously
3the exchanges data of I; Subscription parameters module completes the reading of list, verification, needs to subscribe to the telemetry parameter of answering to main test handler by different port numbers; Second data back module needs to be responsible for afterwards carrying out communication with main test handler in transmitting, and data are passed to Test Network.
Accompanying drawing explanation
Fig. 1 is moonlet C
3i system and launching site C
3the composition schematic diagram of I system;
Fig. 2 is schematic diagram of the present invention;
Fig. 3 is parameter subscribing module;
Fig. 4 is parameter forwarding module schematic diagram;
Fig. 5 is that the first data back module receives transmission schematic diagram data;
Fig. 6 is that the second data back module sends schematic diagram data;
Fig. 7 is for launching front flow chart;
Fig. 8 is for launching rear flow chart.
Embodiment
Just by reference to the accompanying drawings the present invention is described further below.
As shown in Figure 2, the C being applicable to moonlet launching site and using of the present invention
3i system, comprising: launching site C
3i system, main test handler, parameter forwarding module, parameter subscribing module, the first data back module, the second data back module, display module, data memory module.
Before transmitting, subscription parameters module in charge is to main test handler (MTP, Main Test Processor) subscription parameters, the telemetry parameter corresponding to each satellite number that MTP sends according to subscription parameters module returns corresponding remote measurement engineering value to described subscription parameters module.The remote measurement engineering value of acquisition is exported to parameter forwarding module and according to communications protocol format, remote measurement engineering value is packaged into information frame by parameter forwarding module by subscription parameters module, and information frame is transmitted to the C at launching site
3i system, exports to launching site C
3the remote measurement engineering value of I system also can be used for output display module and shows.
As shown in Figure 3, in parameter subscribing module, the telemetry parameter number being sent to each satellite of MTP is distinguished different satellites by list.Such as, three satellites A, B, C are utilized respectively to _ A chosen a little by single table, _ B chosen a little by single table, single table is chosen a little _ telemetry parameter number subscribed to of needs that C records corresponding satellite.Parameter subscribing module is by reading 3 telemetry parameter tables, telemetry parameter number is sent to MTP, corresponds to 3 process MTP_A of satellite A, B, C, MTP_B, MTP_C in MTP and return corresponding telemetry parameter engineering value according to telemetry parameter number to parameter subscribing module respectively.Can support to carry out exchanges data with multiple MTP in parameter subscribing module simultaneously, the mission requirements of several satellite in a rocket can be met.
Under many stars pattern, when corresponding to the telemetry parameter in the list of different satellite to MTP transmission, need the network address and the port numbers that configure 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 parameter forwarding module, first read the telemetry parameter engineering value be kept in temporary variable, then according to the communication protocol being applicable to this satellite, telemetry parameter engineering value is packaged into information frame, is then sent to launching site C by multicast mode
3i system, until require to stop sending
First data back module receives by reception launching site C
3i system sends to moonlet C
3the weather data of I system, command information, and after described antenna data, command information being resolved, export to display module display.As shown in Figure 5, receive from launching site C in the first return data module
3i system include the information of weather data, command data after, the agreement according to communication protocol is resolved information, then sends to display module to show the weather data of acquisition and command data.
After transmitting, the first data back module receives by launching site C
3the remote measurement true form value corresponding to different satellite of I system passback, utilizes data memory module to store described remote measurement true form value.Meanwhile, described first data back module is sent to the second data back module after described remote measurement true form value being converted into the telemetry frame of satellite test net use, by the second data back module, the telemetry frame received is sent to MTP.
As shown in Figure 6, first the second data back module is connected MTP according to address with port numbers, sends information of registering, time then with MTP couple, again send spontaneous emission field C to MTP to MTP
3the telemetry frame of I system.Telemetry frame correspondence corresponding to different satellite is sent to the different processes of MTP, thus achieves the mission requirements meeting several satellite in a rocket.
As shown in Figure 7, before transmission, MTP address, port is set, load the single-point table systems inspection point tableau format in loading procedure made according to communications protocol, as mistake appears in form, then program stopped continues perform and return, until the amendment of some sheet format is correct.As a table loads correct, then to the telemetry parameter in MTP subscription point table, if subscribe to unsuccessfully, program returns, if subscribe to successfully, is then shown by subscription data, and according to the transmission interval arranged, simultaneously according to communication protocol information generated frame, to launching site C
3i system sends information frame, until stop sending.
As shown in Figure 8, after transmitting, setting launching site C
3the address of I system, port, start to receive launching site C
3i system is sent to the data of satellite test net, if accepting state is correct, then carries out format conversion to data, the primitive frame remote measurement converted is sent to MTP, until stop sending.
The unspecified part of the present invention belongs to general knowledge as well known to those skilled in the art.
Claims (2)
1. the C being applicable to moonlet launching site and using
3i system, is characterized in that comprising: launching site C
3i system, main test handler, parameter forwarding module, parameter subscribing module, the first data back module, the second data back module,
Before satellite launch, described parameter subscribing module receives the telemetry parameter engineering value of the telemetry parameter corresponding to described each satellite that returned by described main test handler number according to the telemetry parameter of multi-satellite number, and sends to described parameter forwarding module; The telemetry parameter engineering value received is transmitted to launching site C by described parameter forwarding module
3i system;
After satellite launch, described first data back module is from described launching site C
3the remote measurement true form value of the different satellite of I system acceptance, and be sent to the second data back module after remote measurement true form value being converted into the telemetry frame of satellite test net use; Primitive frame is sent to main test handler by described second data back module, is resolved by main test handler;
Described parameter subscribing module is distinguished satellite by list, the list corresponding to each satellite records the telemetry parameter name and telemetry parameter number of subscribing to main test handler.
2. as claimed in claim 1 a kind of be applicable to moonlet launching site use C
3i system, is characterized in that: described parameter forwarding module is sent to described launching site C after the telemetry parameter engineering value on each satellite list is organized into information frame
3i system.
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| 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 |
| CN111161524B (en) * | 2019-12-11 | 2022-03-04 | 北京东方计量测试研究所 | Testing device |
| 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 |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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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| US7508785B2 (en) * | 2002-11-06 | 2009-03-24 | Broadcom Corporation | Downstream time domain based adaptive modulation for DOCSIS based applications |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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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