CN106407531A - Incremental model-based spacecraft telemetering method - Google Patents
Incremental model-based spacecraft telemetering method Download PDFInfo
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Abstract
The invention discloses an incremental model-based spacecraft telemetering method. The method comprises the steps of (1) building a spacecraft incremental telemetering design model which includes a data system model, a detail design model and a system integration model; (2) finishing related parameter design of the data system model, the detail design model and the system integration model in sequence; (3) converting the data system model, the detail design model and the system integration model after parameter design into configuration codes compilable for a computer; (4) finishing configuration code combination and providing the configuration codes for satellite-borne telemetering software components; and (5) reading the corresponding configuration codes by satellite-borne software, and finishing spacecraft telemetering data acquisition, storage, retrieval, packing, scheduling, framing, virtual channel scheduling and telemetering transmission frame generation and transmission. The method can ensure design information of a spacecraft telemetering system not to be repeated and omitted, thereby remarkably improving the design efficiency of the spacecraft telemetering system.
Description
Technical field
The invention belongs to spacecraft measurement and control area, it is related to a kind of method of telemetering of spacecraft it is adaptable to the remote measurement of spacecraft
System design.
Background technology
Spacecraft telemetry system is the critical function ingredient of spacecraft, including Telemetry Data Acquisition, storage, tissue,
Scheduling, the down function such as biography.Telemetry system has consequence and effect in spacecraft field, covers Space Vehicle System function
Test and the overall process of in-orbit application.Therefore, the wrong telemetry system method for designing of high efficiency, homodyne is to ensure that Space Vehicle System is surveyed
Examination and in orbit safe and reliable prerequisite.
" moonlet software telemetry scheme and modular design method " (Quantum Electronics journal, the 3rd phase of volume 21 in 2004)
Telemetry system method for designing based on modularized design is proposed, on the premise of need not changing remote measurement framing process, by changing
Telemetry mode, frame length, increase and decrease telemetry etc. improve the reusability of telemetering software.However, this design and specific model
Real needs and close structure bind it is impossible to realize the code reuse between different model, system design efficiency is low；Meanwhile,
The degree of coupling of telemetry function intermodule is high, and changes in demand adaptability is poor, and system robustness is poor.
" a kind of Component- Based Development reconfigurable general spaceborne telemetering software design " (spacecraft engineering, 2013 volume 22 4
Phase) telemetry function module is designed using componentization mode, devise data pool component, space bag component, period of element scheduling structure
Part, pseudo channel component and synchronous asynchronous scheduling component, it is possible to achieve code level multiplexing between different model for the software component.So
And, mainly process logical sum algorithm packaged by above-mentioned component, not with specific user data (such as telemetry parameter table, distant
Survey outline etc.) binding, in project implementing process, application program needs to be modified according to the real needs of model.
Additionally, the source of current China all kinds of spacecraft telemetry intelligence (TELINT) collection, the type and quantity of collection remote measurement, remote measurement are adopted
The method that the mode of collection, telemetry intelligence (TELINT) tissue pass down, all has nothing in common with each other according to the difference of space mission.Large complicated spacecraft
Telemetry parameter up to thousands of, during Project R＆D, during the related software code of manual compiling telemetry parameter, journey
Sequence is write, is tested and verify that workload is very big.Remote measurement due to lacking compatible with the design of spaceborne telemetering software component designs a model, no
Same domain model provides the telemetry system degree of refinement that design inputs, mode, form each variant, needs designer's ditch repeatedly
Lead to, absorb and convert, these differences make the telemetry system of each model be required for custom-made exploitation, and this mode is on the one hand
Reduce design efficiency, on the other hand, because process is loaded down with trivial details and the carelessness of developers may produce all kinds of mistakes again, including
Telemetry parameter content false, telemetry parameter order (position) mistake, telemetry parameter are changed incomplete etc..
Content of the invention
Present invention solves the technical problem that being：Overcome the deficiencies in the prior art, there is provided a kind of based on quantitation model
The spacecraft method of telemetering is it is achieved that telemetry system topology design, remote measurement bag design, telemetry frame designs, telemetry parameter designs, remote measurement
Collection design, remote measurement transmit the decouplings such as design it is ensured that spacecraft telemetry system design information does not repeat, do not omit, Neng Gouxian
Write the efficiency improving the design of spacecraft telemetry system and reliability.
The technical solution of the present invention is：A kind of spacecraft method of telemetering based on quantitation model, including：
(1) set up the quantitation remote measurement of spacecraft to design a model, the quantitation remote measurement of described spacecraft designs a model further
Including data system system model, detailed design model, System Integration Model；
Described data system system model includes：
Spacecraft topological arrangement submodel：Including terminal name, terminal code name, terminal address；
Remote measurement transmission frame-form submodel：Including synchronous head, leading head, insertion domain, data field, Error Control domain row
Row mode and length；
Remote measurement head-coating structure submodel：Including bag version number, Packet type, secondary top guide mark, application process mark, packet
Mark, packet sequence counting, the arrangement mode of packet length and length；
Pseudo channel plans submodel：Including pseudo channel title, code name, data field type；
Packet plans submodel：Including telemetry data packet code name, title, application process mark；
Described detailed design model includes：
Hard passage telemetry parameter submodel：Reflection spacecraft standalone hardware remote measurement design point, including spacecraft unit
The code name of hardware telemetry parameter, title, channel number, parameter type；
Bus telemetry parameter submodel：Reflection spacecraft software telemetry design point, including each point of spacecraft
The telemetry parameter list that system terminal is comprised by the telemetry data packet of bus transfer, each telemetry parameter includes code name, name
Title, position, length；
System-level telemetry parameter submodel：Reflection spacecraft housekeeping software remote measurement design point, including spacecraft Star Service
Software telemetry parameter list, each telemetry parameter includes code name, title, length；
Described System Integration Model includes：
Data acquisition protocol submodel：Telemetry data packet host-host protocol in each terminal, including in each terminal
Each telemetry data packet title, data flow, mailing address, communication cycle, data length；
Downlink telemetry data packets model：The telemetry parameter list being comprised including each downlink telemetry packet, including
Code name, title, data length；
Telemetry data packet dispatches submodel：The remote measurement number being comprised including all kinds of telemetry mode under all kinds of pseudo channels
According to bag code name and transmission cycle；
Pseudo channel transmits submodel：Including the transmission frame of each pseudo channel, transmission priority；
(2) it is sequentially completed the relevant parameter design of data system system model, detailed design model and System Integration Model；
(3) the spacecraft topological arrangement generation that the data system system model conversation after parameter designing can be compiled for computer
Code, remote measurement transmission frame-form configuration code, remote measurement head-coating structure configuration code, pseudo channel planning and configuration code, packet rule
Draw configuration code；Hard telemetry parameter configuration code that detailed design model conversation after parameter designing can be compiled for computer,
Bus telemetry parameter configuration code, system-level telemetry parameter configuration code；System Integration Model after parameter designing is converted into
Data acquisition protocol configuration code that computer can compile, downlink telemetry packet configuration code, the configuration of telemetry packet scheduling
Code, pseudo channel transmission configuration code；
(4) complete configuration code combination, provide configuration code for spaceborne telemetering software component；Wherein, spacecraft topology is joined
Put code, data acquisition protocol configuration code is collectively forming data acquisition configuration code, provide operation to connect for data acquisition component
Mouth data；Hard telemetry parameter configuration code, bus telemetry parameter configuration code, system-level telemetry parameter configuration code are collectively forming
Data pool configuration code, provides runnable interface data for data pool component；Packet planning and configuration code, remote measurement head-coating structure are joined
Put code, downlink telemetry packet configuration code is collectively forming remote measurement bag configuration code, provide operation to connect for remote measurement group bag component
Mouth data；Telemetry packet scheduling configuration code provides runnable interface data for source packet scheduling component；Remote measurement transmission frame-form is joined
Put code, pseudo channel planning and configuration code is collectively forming pseudo channel configuration code, provide fortune for pseudo channel framing component
Line interface data；Pseudo channel planning and configuration code, pseudo channel transmission configuration code are collectively forming virtual channel schedule configuration
Code, provides runnable interface data for virtual channel schedule component；The downlink telemetry of remote measurement transmission frame-form configuration code definition
Transmission frame synchronous head constant, and downlink telemetry frame error control encryption algorithm enumerated variable forms down-going synchronous and verification configures
Code, generating for full frames of data provides runnable interface data with conveying member；
(5) the data acquisition component of On-board software, data pool component, remote measurement group bag component, source packet scheduling component, virtual letter
Road framing component, virtual channel schedule component, full frames of data generate and read corresponding configuration code with conveying member, complete space flight
Device Telemetry Data Acquisition, storage, retrieval, group bag, scheduling, framing, virtual channel schedule, remote measurement transmission frame generate and transmission.
Present invention advantage compared with prior art is：
(1) the inventive method is designed a model based on quantitation spacecraft telemetry system, and spacecraft remote measurement is designed a model
It is decomposed into data system system model, detailed design model and System Integration Model it is achieved that telemetry system topology design, remote measurement
Bag design, telemetry frame design, telemetry parameter design, telemetry-acquisition design, the decoupling of remote measurement transmission design are it is ensured that spacecraft is distant
Examining system design information does not repeat, does not omit；
(2) data system system model, detailed design model and System Integration Model are changed into by the inventive method automatically
The configuration code of spaceborne telemetering software component, high efficiency, homodyne meet the use demand of different model wrongly, overcome artificial volume
Write the deficiency that thousands of telemetry parameters gather, store, group bag, framing, scheduling code are time-consuming, laborious, and eliminate artificial
Write the quality accident that code leads to, significantly reduce the development cost of spacecraft.
Brief description
Fig. 1 is the schematic diagram of the inventive method；
The composition structure chart that Fig. 2 designs a model for the present invention quantitation spacecraft remote measurement；
Fig. 3 is spacecraft telemetry system work process flow chart of the present invention.
Specific embodiment
As shown in figure 1, being the schematic diagram of the inventive method, key step is as follows：
Step one, sets up the quantitation remote measurement of spacecraft and designs a model, and in the present invention, spacecraft remote measurement designs a model decomposition
For data system system model, detailed design model, System Integration Model three part composition it is ensured that spacecraft telemetry system
Design considerations do not repeat, do not omit.Specifically as shown in Figure 2.
(1) data system system model includes：
Spacecraft topological arrangement submodel：Including terminal (Remote Terminal-RT) title, terminal code name, end
End address；
Remote measurement transmission frame-form submodel：Including synchronous head, leading head (containing version number, spacecraft identifier (SCID),
Virtual channel identifier (VCID), virtual channel data unit unit (VCDU) enumerator, mark domain), insertion domain, data field, mistake
The isoparametric arrangement mode of control domain and length；
Remote measurement head-coating structure submodel：Including bag version number, Packet type, secondary top guide mark, application process mark
(APID), group character, packet sequence counting, the isoparametric arrangement mode of packet length and length；
Pseudo channel plans submodel：Including pseudo channel title, code name, data field type；
Packet plans submodel：Including telemetry data packet code name, title, application process mark；
(2) detailed design model includes：
Hard passage telemetry parameter submodel：Reflection spacecraft standalone hardware remote measurement design point, including spacecraft unit
The code name of hardware telemetry parameter, title, channel number, parameter type；
Bus telemetry parameter submodel：Reflection spacecraft software telemetry design point, including each point of spacecraft
The telemetry parameter list that system terminal is comprised by the telemetry data packet of bus transfer, each telemetry parameter includes code name, name
Title, position, length；
System-level telemetry parameter design：Reflection spacecraft housekeeping software remote measurement design point, soft including spacecraft Star Service
Part telemetry parameter list, each telemetry parameter includes code name, title, length；
(3) System Integration Model includes：
Data acquisition protocol submodel：Telemetry data packet host-host protocol in each terminal, including in each terminal
Each telemetry data packet title, data flow, mailing address, communication cycle, data length；
Downlink telemetry data packets model：The telemetry parameter list being comprised including each downlink telemetry packet, including
Code name, title, data length；
Telemetry data packet dispatches submodel：The remote measurement number being comprised including all kinds of telemetry mode under all kinds of pseudo channels
According to bag code name and transmission cycle；
Pseudo channel transmits submodel：Including the transmission frame of each pseudo channel, transmission priority.
Step 2, completes the instantiation that quantitation remote measurement designs a model, and is sequentially completed data system system model, sets in detail
The relevant parameter design of meter model and System Integration Model.
First, complete the instantiation of the design variable that data system system model comprises, realize spacecraft remote measurement top layer
Design, including spacecraft topological arrangement submodel, remote measurement transmission frame-form submodel, remote measurement pack arrangement submodel, pseudo channel
The instantiation of submodel design parameter planned by planning submodel data bag；
Then, complete the instantiation of the design variable that detailed design model comprises, realize spacecraft remote measurement detailed design,
Including hard passage telemetry parameter submodel, bus telemetry parameter submodel, system-level telemetry parameter submodel design parameter reality
Exampleization, the design considerations of each telemetry parameter include remote measurement code name, remote measurement title, remote measurement type, remote measurement length；
Finally, according to the data system system model of instantiation and the constraint of detailed design model, the integrated mould of completion system
The instantiation of the design variable that type is comprised, realizes the collection of spacecraft telemetry parameter, storage, group bag, framing, scheduling etc., wraps
Include data acquisition protocol submodel, downlink telemetry data packets model, telemetry data packet scheduling submodel, pseudo channel transmission
The instantiation of modelling parameter.
To sum up step, using increment type instantiation flow process, complete from top to down spacecraft remote measurement design a model design ginseng
The instantiation of number.
Step 3：Complete the quantitation remote measurement corresponding configuration code that designs a model to be autonomously generated.
By the data system system model of instantiation be automatically converted to spacecraft topological arrangement code that computer can compile,
Remote measurement transmission frame-form configuration code, remote measurement head-coating structure configuration code, pseudo channel planning and configuration code, packet planning are joined
Put code；
The detailed design model of instantiation is automatically converted to hard telemetry parameter configuration code, the bus that computer can compile
Telemetry parameter configuration code, system-level telemetry parameter configuration code；
By the System Integration Model of instantiation be automatically converted to data acquisition protocol configuration code that computer can compile, under
Row telemetry data packet configuration code, telemetry packet scheduling configuration code, pseudo channel transmission configuration code.
Remote measurement design a model be converted into spaceborne telemetering software component configuration code detailed process as follows：
1. data system system model
(1) spacecraft topological arrangement submodel
The design parameter that spacecraft topological arrangement submodel comprises is as shown in table 1, its corresponding spacecraft topological arrangement generation
Code is as follows：
Enum { GPS=0, KWY }；/ * terminal enumerated variable */
Int DEVICE_NUMBER=KWY-GPS+1；/ * terminal number variable */
Int RT_ADD []={ 13,17 }；/ * terminal (RT) address array */
Table 1 spacecraft topological arrangement submodel design parameter
| Sequence number | Terminal name | Terminal code name | Terminal (RT) address |
| 1 | Navigation neceiver | GPS | 13 |
| 2 | Intelligent temperature control instrument | KWY | 17 |
(2) remote measurement transmission frame-form submodel
The design parameter that remote measurement transmission frame-form submodel comprises as shown in table 2, join by its corresponding remote measurement transmission frame-form
Put code as follows：
Table 2 remote measurement transmission frame-form submodel design parameter
| Sequence number | Design parameter | Variable code name | Design load | Types of variables |
| 1 | Frame version number | VERSION | 1 | 10 systems |
| 2 | Spacecraft identifies | SCID | 0x10 | 16 systems |
| 3 | Transmission frame data field length | FRAME_DATA_LENGTH | 962 | 10 systems |
| 4 | Remote measurement bit rate | TM_RATE | 5000 | 10 systems |
| 5 | Transmission frame inserts length of field | INSERTION_LENGTH | 50 | 10 systems |
| 6 | Error Control length of field | ERROR_CTRL_LENGTH | 2 | 10 systems |
| 7 | Frame swynchronization code | SYN_CODE | 0x1ACFFC1D | 16 systems |
| 8 | Error Control domain algorithm | ERROR_CTRL_ALG | CRC16 | Enumeration type |
(3) remote measurement head-coating structure submodel
As shown in table 3, its corresponding remote measurement head-coating structure configures generation to the design parameter that remote measurement head-coating structure submodel comprises
Code is as follows：
Table 3 remote measurement head-coating structure submodel design parameter
(4) pseudo channel planning
Pseudo channel plans that the design parameter that submodel comprises is as shown in table 4, its corresponding pseudo channel planning and configuration generation
Code is as follows：
Table 4 pseudo channel plans submodel design parameter
| Sequence number | Pseudo channel title | Code name | Data field type |
| 1 | Conventional remote measurement | VC1 | Multiplexing data |
| 2 | Delayed telemetry | VC2 | Bit stream data |
| 3 | Internal memory reads | VC3 | Bit stream data |
| 4 | Event data | VC4 | Bit stream data |
| 5 | Load data | VC5 | Bit stream data |
(5) packet planning submodel
Packet plans that the design parameter that submodel comprises is as shown in table 5, its corresponding packet planning
Configuration code is as follows：
Enum { PK01=0；PK02=1 }；/ * telemetry data packet enumerated variable */
Int PK_NUMBER=PK02-PK01+1；/ * telemetry data packet number definition */
Int APID_ARRAY []={ 17,29 }；/ * telemetry data packet APID coding array definition */
Table 5 packet plans submodel design parameter
| Sequence number | Packet code name | Package name | Application process identifies (APID) |
| 1 | PK01 | Navigation neceiver speed becomes remote measurement | 17 |
| 2 | PK02 | Intelligent temperature control instrument remote measurement | 29 |
2. detailed design model
(1) hard passage telemetry parameter submodel
The design parameter that hard passage telemetry parameter submodel is comprised is as shown in table 6, including the generation of hard passage telemetry parameter
Number, title, the channel number gathering this telemetry parameter, parameter type, its corresponding hard telemetry parameter configuration code is：
The hard passage telemetry parameter submodel design parameter of table 6
| Telemetry parameter code name | Telemetry parameter title | Channel number | Parameter type |
| TMC001 | Answering machine remote control mode piece locks | A1-AN01 | BL |
| TMC002 | Answering machine carrier lock | A1-AN02 | BL |
| TMC003 | Answering machine ranging code locks | A1-AN03 | BL |
| TMC004 | Remote control PCM is effective for answering machine | A1-AN04 | BL |
| TMS020 | CTU clock active/standby state | A1-AN05 | BL |
| TMS021 | CTU independently cuts machine state | A1-AN06 | BL |
| TMS022 | CTU system mode | A1-AN07 | BL |
| TMS023 | CTU PCM telemetering state | A1-AN08 | BL |
(2) bus telemetry parameter submodel
The design parameter that bus telemetry parameter submodel is comprised is for example shown in table 7, table 8 (with navigation neceiver, intelligent control
As a example warm two subsystems of instrument), the telemetry parameter list passing through the telemetry data packet of bus transfer including each terminal (comprises generation
Number, title, position, length), its corresponding bus telemetry parameter configuration code is：
Table 7 navigation neceiver bus remote measurement design parameter
| Telemetry parameter code name | Telemetry parameter title | Length (byte) |
| TMC005 | Location data | 16 |
| TMC006 | Orbit determination data | 16 |
The intelligent temperature control instrument bus remote measurement design parameter of table 8
| Telemetry parameter code name | Telemetry parameter title | Length (byte) |
| TMR001 | Temperature Quantity 1 | 2 |
| TMR002 | Temperature Quantity 2 | 2 |
| TMR003 | Temperature Quantity 3 | 2 |
| TMR004 | Temperature Quantity 4 | 2 |
| TMR005 | Temperature Quantity 5 | 2 |
| TMR006 | Temperature Quantity 6 | 2 |
| TMR007 | Temperature Quantity 7 | 2 |
| TMR008 | Temperature Quantity 8 | 2 |
(3) system-level telemetry parameter submodel
The design parameter that system-level telemetry parameter submodel is comprised is as shown in table 9, including system-level telemetry parameter list
(code name containing telemetry parameter, title, length), its corresponding system-level telemetry parameter configuration code is：
The system-level telemetry parameter submodel design parameter of table 9
| Telemetry parameter code name | Telemetry parameter title | Length (byte) |
| TMS200 | Receive remote control frame count | 2 |
| TMS201 | Up remote control bag counts | 2 |
| TMS202 | SMU execution remote control bag counts | 2 |
3. System Integration Model
(1) data acquisition protocol submodel
The design parameter that data acquisition protocol submodel is comprised is as shown in table 10, including telemetry data packet title, data
Flow direction, mailing address, communication cycle, data length, its corresponding data acquisition protocol configuration code is：
Table 10 data acquisition protocol submodel design parameter
(2) downlink telemetry data packets model
The design parameter that downlink telemetry data packets model comprises is for example shown in table 11, table 12 (with TTC channel status number
As a example bag, intelligent temperature control instrument critesistor module temperature packet), the remote measurement being comprised including downlink telemetry packet is joined
The code name of number, title, length and relative position, its corresponding configuration code is：
Table 11 TTC channel state data packets (PK01) design parameter
Intelligent temperature control instrument critesistor module temperature packet (PK02) design parameter of table 12
| Telemetry parameter code name | Telemetry parameter title | Length (byte) |
| TMR001 | Temperature Quantity 1 | 2 |
| TMR002 | Temperature Quantity 2 | 2 |
| TMR003 | Temperature Quantity 3 | 2 |
| TMR004 | Temperature Quantity 4 | 2 |
| TMR005 | Temperature Quantity 5 | 2 |
| TMR006 | Temperature Quantity 6 | 2 |
| TMR007 | Temperature Quantity 7 | 2 |
| TMR008 | Temperature Quantity 8 | 2 |
(3) telemetry data packet scheduling submodel
, the design parameter that telemetry data packet scheduling sublayer model comprises is as shown in table 13 taking pseudo channel VC1 as a example, including
Transmission cycle under the telemetry data packet title of this pseudo channel transmission, code name and each telemetry mode, it is corresponding descending
Telemetry packet scheduling configuration code is：
Table 13 telemetry data packet scheduling sublayer modelling parameter
(4) pseudo channel transmission submodel
The design parameter that pseudo channel transmission submodel is comprised is as shown in table 14, including the transmission number of every kind of pseudo channel
According to the transmission priority of frame and this pseudo channel, its corresponding pseudo channel transmission configuration code is：
Table 14 pseudo channel transmits submodel design parameter
| Sequence number | Pseudo channel code name | Transmission frame | Priority |
| 1 | VC1 | 0 | 1 |
| 2 | VC2 | 1,2,3 | 4 |
| 3 | VC3 | 1,2,3 | 1 |
| 4 | VC4 | 1,2,3 | 2 |
| 5 | VC5 | 1,2,3 | 3 |
Step 4：Complete the configuration code combination that above-mentioned steps are generated, provide configuration generation for spaceborne telemetering software component
Code.
Spacecraft topological arrangement code definition spacecraft terminal enumerated variable, terminal number variable and terminal address number
Group, data acquisition protocol configuration code defines the data acquisition protocol aray variable of each terminal of spacecraft, and aray variable includes
Data flow, mailing address, terminal address, communication cycle, data length etc., both form data acquisition configuration code, for number
There is provided runnable interface data according to acquisition member, data acquisition component polling data acquisition protocols array, according to the data flow of regulation
To, terminal address, mailing address, communication cycle gather corresponding length telemetry, formed telemetry pond.
Hard telemetry parameter configuration code, bus telemetry parameter configuration code, system-level telemetry parameter configuration code definition boat
Index enumerated variable corresponding to its device standalone hardware remote measurement, spacecraft software telemetry, spacecraft housekeeping software remote measurement,
And the length variable of this telemetry parameter, three's formation data pool configuration code, provide runnable interface data for data pool component,
Retrieval and the extraction of spacecraft telemetry parameter realized accordingly by data pool component.
Packet planning and configuration code definition telemetry data packet number, telemetry data packet enumerated variable, telemetry data packet
APID encodes aray variable；Remote measurement head-coating structure configuration code defines remote measurement header data structure and remote measurement packet header constant, and complete
Become the initialization of remote measurement header data structure；Downlink telemetry packet configuration code defines telemetry parameter position alignment enumerated variable,
And successively define telemetry data packet telemetry parameter group bag configuration array, this array include telemetry parameter enumerate index variables and
Align enumerated variable in telemetry parameter position, for identifying original position in data pool for the telemetry parameter that telemetry data packet comprised
And length, three's formation remote measurement bag configuration code, provide runnable interface data for remote measurement group bag component, remote measurement group bag component is accordingly
Realize the functions such as telemetry parameter contained by remote measurement bag extracts, packet header is organized, calculating packet length, ultimately form each remote measurement number of spacecraft
According to bag.
Telemetry packet scheduling configuration code defines spacecraft telemetry mode enumerated variable, telemetry mode number, each remote measurement
Telemetry data packet multichannel cycle array under pattern, and at the beginning of the telemetry data packet multichannel cycle aray variable under each telemetry mode
Beginningization, the remote measurement source packet scheduling under each telemetry mode realized accordingly by source packet scheduling component.
Pseudo channel planning and configuration code definition pseudo channel enumerated variable, pseudo channel number variable, pseudo channel number
According to field type enumerated variable, each virtual channel data field type aray variable etc., and complete each virtual channel data field type number
Group initialization of variable；Remote measurement transmission frame-form configuration code defines remote measurement frame head data structure and remote measurement transmission frame synchronous head is normal
Amount, and complete the initialization of remote measurement frame head data structure, both form pseudo channel configuration code, are that pseudo channel framing component carries
For runnable interface data, pseudo channel framing component completes the layout that pseudo channel removes the overseas other specification of data accordingly.
Pseudo channel planning and configuration code definition pseudo channel number, pseudo channel enumerated variable；Pseudo channel transmission is joined
Put code and pseudo channel transmission state array is defined according to pseudo channel number, with pseudo channel enumerated variable for index, definition
The transmission frame information of each pseudo channel and transmission priority, both form virtual channel schedule configuration code, are pseudo channel
Scheduling component provides runnable interface data, and virtual channel schedule component completes pseudo channel transmitting and scheduling accordingly.
Remote measurement transmission frame-form configuration code defines downlink telemetry transmission frame synchronous head constant, and downlink telemetry frame error
Control encryption algorithm enumerated variable, both form down-going synchronous and verification configuration code, be that full frames of data generates and conveying member
There is provided service data interface, full frames of data generates increases downstream synchronization code word for telemetry frame accordingly with conveying member, and raw
Become the Error Control code word of telemetry frame, realize remote measurement transmission frame transmitting.
After automatically generating configuration code combination, it is data acquisition component, data pool component, remote measurement group bag component, source bag tune
Degree component, pseudo channel framing component, virtual channel schedule component, full frames of data generate and conveying member offer operational factor,
High efficiency, homodyne meet the use demand of different model wrongly.
Step 5：On-board software remote measurement component read configuration code, complete spacecraft Telemetry Data Acquisition, storage, retrieval,
Group bag, scheduling, framing, virtual channel schedule, full frames of data generate and transmission.
It is illustrated in figure 3 spacecraft telemetry system work process, spaceborne telemetering software component reads this method and automatically generates
Configuration code, complete spacecraft Telemetry Data Acquisition, retrieval, group bag, source packet scheduling, pseudo channel framing, pseudo channel tune
Degree, full frames of data generation and transmission etc., work process is as follows：
(1) Telemetry Data Acquisition
Data acquisition component reads data acquisition configuration code, according to regulation frequency acquisition from the son of each bus termination
The telemetry of seismic acquisition corresponding length, forms telemetry pond.
(2) telemetry storage, retrieval and extraction
Data pool component according to data pool configuration code, to including hard passage telemetry parameter, bus telemetry parameter, system-level
Telemetry parameter is realized unified storage, retrieval in interior all telemetry parameters and is updated.
(3) remote measurement source bag extracts
Remote measurement group bag component reads remote measurement bag configuration code, realizes telemetry parameter extraction contained by remote measurement bag, packet header tissue, meter
Calculate the functions such as packet length, generate all kinds of telemetry sources bag.
(4) remote measurement source packet scheduling
Source packet scheduling component reads telemetry packet scheduling configuration code, completes all kinds of pseudo channels in current telemetry pattern
Under remote measurement source packet scheduling, ultimately form the valid data of remote measurement pseudo channel.
(5) pseudo channel framing
Pseudo channel framing component reads pseudo channel configuration code, forms spacecraft telemetry frame, and tune is wrapped in source
The pseudo channel valid data that degree component is formed are filled in virtual channel data area, form virtual channel data frame.
(6) virtual channel schedule
Virtual channel schedule component reads virtual channel schedule configuration code, according to pseudo channel transmission frame and transmission preferences
Level selects next remote measurement transmission frame, realizes the virtual channel schedule of telemetry.
(7) full frames of data generates and transmission
Full frames of data generates and reads down-going synchronous and verification configuration code with conveying member, reads down-going synchronous and joins with verification
Put code, calculate and generate wrong plug control routine, in remote measurement transmission frame forward and backward increase frame synchronization head and error control code respectively,
Realize telemetry frame transmitting.
The content not being described in detail in description of the invention belongs to the known technology of those skilled in the art.
Claims (1)
1. a kind of spacecraft method of telemetering based on quantitation model is it is characterised in that include：
(1) set up the quantitation remote measurement of spacecraft to design a model, the quantitation remote measurement of described spacecraft designs a model and further includes
Data system system model, detailed design model, System Integration Model；
Described data system system model includes：
Spacecraft topological arrangement submodel：Including terminal name, terminal code name, terminal address；
Remote measurement transmission frame-form submodel：Including synchronous head, leading head, insertion domain, data field, Error Control domain arrangement side
Formula and length；
Remote measurement head-coating structure submodel：Including bag version number, Packet type, secondary top guide mark, application process mark, group character,
Packet sequence counting, the arrangement mode of packet length and length；
Pseudo channel plans submodel：Including pseudo channel title, code name, data field type；
Packet plans submodel：Including telemetry data packet code name, title, application process mark；
Described detailed design model includes：
Hard passage telemetry parameter submodel：Reflection spacecraft standalone hardware remote measurement design point, distant including spacecraft standalone hardware
The code name of survey parameter, title, channel number, parameter type；
Bus telemetry parameter submodel：Reflection spacecraft software telemetry design point, including each subsystem of spacecraft eventually
The telemetry parameter list that end is comprised by the telemetry data packet of bus transfer, each telemetry parameter includes code name, title, position
Put, length；
System-level telemetry parameter submodel：Reflection spacecraft housekeeping software remote measurement design point, distant including spacecraft housekeeping software
Survey parameter list, each telemetry parameter includes code name, title, length；
Described System Integration Model includes：
Data acquisition protocol submodel：Telemetry data packet host-host protocol in each terminal, including each distant in each terminal
Survey package name, data flow, mailing address, communication cycle, data length；
Downlink telemetry data packets model：The telemetry parameter list being comprised including each downlink telemetry packet, including code name,
Title, data length；
Telemetry data packet dispatches submodel：The telemetry data packet being comprised including all kinds of telemetry mode under all kinds of pseudo channels
Code name and transmission cycle；
Pseudo channel transmits submodel：Including the transmission frame of each pseudo channel, transmission priority；
(2) it is sequentially completed the relevant parameter design of data system system model, detailed design model and System Integration Model；
The spacecraft topological arrangement code that (3) the data system system model conversation after parameter designing can be compiled for computer,
Remote measurement transmission frame-form configuration code, remote measurement head-coating structure configuration code, pseudo channel planning and configuration code, packet planning are joined
Put code；Hard telemetry parameter configuration code that detailed design model conversation after parameter designing can be compiled for computer, bus
Telemetry parameter configuration code, system-level telemetry parameter configuration code；System Integration Model after parameter designing is converted into calculating
Data acquisition protocol configuration code that machine can compile, downlink telemetry packet configuration code, telemetry packet scheduling configuration code,
Pseudo channel transmission configuration code；
(4) complete configuration code combination, provide configuration code for spaceborne telemetering software component；Wherein, spacecraft topological arrangement generation
Code, data acquisition protocol configuration code are collectively forming data acquisition configuration code, provide runnable interface number for data acquisition component
According to；Hard telemetry parameter configuration code, bus telemetry parameter configuration code, system-level telemetry parameter configuration code are collectively forming data
Pond configuration code, provides runnable interface data for data pool component；Packet planning and configuration code, remote measurement head-coating structure configuration generation
Code, downlink telemetry packet configuration code are collectively forming remote measurement bag configuration code, provide runnable interface number for remote measurement group bag component
According to；Telemetry packet scheduling configuration code provides runnable interface data for source packet scheduling component；Remote measurement transmission frame-form configures generation
Code, pseudo channel planning and configuration code are collectively forming pseudo channel configuration code, provide operation to connect for pseudo channel framing component
Mouth data；Pseudo channel planning and configuration code, pseudo channel transmission configuration code are collectively forming virtual channel schedule configuration code,
There is provided runnable interface data for virtual channel schedule component；The downlink telemetry transmission frame of remote measurement transmission frame-form configuration code definition
Synchronous head constant, and downlink telemetry frame error control encryption algorithm enumerated variable formation down-going synchronous and verification configuration code,
Generating for full frames of data provides runnable interface data with conveying member；
(5) the data acquisition component of On-board software, data pool component, remote measurement group bag component, source packet scheduling component, pseudo channel group
Frame component, virtual channel schedule component, full frames of data generate and read corresponding configuration code with conveying member, complete spacecraft distant
Survey data acquisition, storage, retrieval, group bag, scheduling, framing, virtual channel schedule, the generation of remote measurement transmission frame and transmission.
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Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
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| CN115801100A (en) * | 2022-11-07 | 2023-03-14 | 银河航天(北京)通信技术有限公司 | Method, device and storage medium for remote control-based channel number-to-telemetry scheduling |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102436465A (en) * | 2011-09-01 | 2012-05-02 | 北京空间飞行器总体设计部 | Telemetry data compression storage and rapid query method of ontrack spacecraft |
| CN102984220A (en) * | 2012-11-13 | 2013-03-20 | 北京空间飞行器总体设计部 | Burst data downloading communication method for spacecraft multilevel subnets |
| CN102999331A (en) * | 2012-11-13 | 2013-03-27 | 北京空间飞行器总体设计部 | Hardware blocking layer of onboard software and onboard data communication method |
-
2016
- 2016-09-05 CN CN201610804517.5A patent/CN106407531B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102436465A (en) * | 2011-09-01 | 2012-05-02 | 北京空间飞行器总体设计部 | Telemetry data compression storage and rapid query method of ontrack spacecraft |
| CN102984220A (en) * | 2012-11-13 | 2013-03-20 | 北京空间飞行器总体设计部 | Burst data downloading communication method for spacecraft multilevel subnets |
| CN102999331A (en) * | 2012-11-13 | 2013-03-27 | 北京空间飞行器总体设计部 | Hardware blocking layer of onboard software and onboard data communication method |
Non-Patent Citations (2)
| Title |
|---|
| 张亚航等: "一种基于星内路由的航天器数管软件框架设计", 《航天器工程》 * |
| 张亚航等: "一种基于构件的可重配置通用星载遥测软件设计", 《航天器工程》 * |
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