CN108023681A - Interweaved the error control method mapped based on perforation - Google Patents
Interweaved the error control method mapped based on perforation Download PDFInfo
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- CN108023681A CN108023681A CN201810069448.7A CN201810069448A CN108023681A CN 108023681 A CN108023681 A CN 108023681A CN 201810069448 A CN201810069448 A CN 201810069448A CN 108023681 A CN108023681 A CN 108023681A
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- 238000000034 method Methods 0.000 title claims abstract description 33
- 238000013507 mapping Methods 0.000 claims abstract description 17
- 238000012937 correction Methods 0.000 claims abstract description 14
- 238000012545 processing Methods 0.000 claims abstract description 4
- 238000009941 weaving Methods 0.000 claims description 9
- 230000005540 biological transmission Effects 0.000 description 14
- 230000006854 communication Effects 0.000 description 11
- 238000004422 calculation algorithm Methods 0.000 description 10
- 238000004891 communication Methods 0.000 description 10
- 230000000875 corresponding effect Effects 0.000 description 9
- 238000013461 design Methods 0.000 description 9
- 230000000903 blocking effect Effects 0.000 description 8
- 238000001514 detection method Methods 0.000 description 8
- 230000001360 synchronised effect Effects 0.000 description 6
- 238000012217 deletion Methods 0.000 description 5
- 230000037430 deletion Effects 0.000 description 4
- 230000009977 dual effect Effects 0.000 description 4
- 239000011159 matrix material Substances 0.000 description 4
- 230000000737 periodic effect Effects 0.000 description 4
- 238000012360 testing method Methods 0.000 description 4
- 238000004364 calculation method Methods 0.000 description 3
- 230000001427 coherent effect Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 238000004080 punching Methods 0.000 description 3
- 238000011160 research Methods 0.000 description 3
- 230000007246 mechanism Effects 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
- 238000012546 transfer Methods 0.000 description 2
- 108020004705 Codon Proteins 0.000 description 1
- 241000854350 Enicospilus group Species 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000002596 correlated effect Effects 0.000 description 1
- 230000003111 delayed effect Effects 0.000 description 1
- 238000005562 fading Methods 0.000 description 1
- 238000009432 framing Methods 0.000 description 1
- 238000009940 knitting Methods 0.000 description 1
- 230000002045 lasting effect Effects 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 230000000306 recurrent effect Effects 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Classifications
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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
- H04B7/18502—Airborne stations
- H04B7/18506—Communications with or from aircraft, i.e. aeronautical mobile service
- H04B7/18508—Communications with or from aircraft, i.e. aeronautical mobile service with satellite system used as relay, i.e. aeronautical mobile satellite service
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L1/00—Arrangements for detecting or preventing errors in the information received
- H04L1/004—Arrangements for detecting or preventing errors in the information received by using forward error control
- H04L1/0056—Systems characterized by the type of code used
- H04L1/0067—Rate matching
- H04L1/0068—Rate matching by puncturing
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L1/00—Arrangements for detecting or preventing errors in the information received
- H04L1/004—Arrangements for detecting or preventing errors in the information received by using forward error control
- H04L1/0056—Systems characterized by the type of code used
- H04L1/0071—Use of interleaving
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L1/00—Arrangements for detecting or preventing errors in the information received
- H04L1/004—Arrangements for detecting or preventing errors in the information received by using forward error control
- H04L1/0072—Error control for data other than payload data, e.g. control data
Abstract
The present invention disclose it is a kind of based on perforation interweave map error control method, for earth station to helicopter (group) communicate when Error Control problem propose new method.Method of the present invention includes：Earth station carries out Error Correction of Coding to sending information, and perforation interleaver is launched after mapping is interleaved to the sequence after Error Correction of Coding；To receiving data after deinterleaving is handled, obtained error coded data is equivalent to earth station and sends the result after Error Correction of Coding perforation using the true form error coding progress equivalent perforation processing to interweave to transmitting terminal airborne station.The present invention more fully excavates helicopter satellite downlink channel capacity, the Error Control that solution lifting airscrew that can be effective blocks.
Description
The application is based on perforation for the application number 201510112636.X denominations of invention of the applying date 2015 year 03 month 13 and interweaves
The divisional application of the error control method of mapping.
Technical field
The present invention relates to a kind of error control method for being interweaved based on perforation and being mapped.
Background technology
In helicopter satellite downlink, when information is transmitted to helicopter (group) in earth station, helicopter rotor blade
Circular motion can cause to block to satellite relay signal.Blocked the period in rotor, the information of earth station's transmission would generally be deleted
Fall, having one section of continuous data in data frame after the helicopter satellite-signal under rotor blocks is deleted, and is deleted
Continuous data is to block deletion data.Influenced at the same time by the helicopter speed of a ship or plane, course and flight attitude, rotor blocks the cycle and accounts for
Sky is than having time variation, and corresponding delete position and deletion length equally have time variation, this gives Error Control increase
Technical difficulty.
The content of the invention
In view of the above-mentioned problems, the present invention provides the mistake that a kind of rotor that can effectively solve the problem that earth station's transmission information blocks
The error control method of the mapping that interweaved based on perforation of control problem.
To reach above-mentioned purpose, the present invention is interweaved the error control method of mapping based on perforation, including：
Earth station carries out Error Correction of Coding to sending information, and perforation interleaver is interleaved mapping to the sequence after Error Correction of Coding
After launched；
To receiving data after deinterleaving is handled, obtained error coded data is equivalent to earth station and sends to be entangled airborne station
Result after miscoding perforation carries out equivalent perforation processing using the true form error coding to interweave to transmitting terminal.
Further, the interleaving units of the perforation interleaver are 1bit, uniform interleaving, with the error correcting code pair mutually cascaded
Based on the punctured code of part system answered, the mapping ruler that interweaves is gone out according to the punching matrix backstepping of perforation interleaver.
Specifically, the specific method of sequence into eleven punch 11 intertexture mapping of the transmitting terminal to Error Correction of Coding is：Using
3 dual port RAMs, are respectively RAM A, RAM B and RAM C,
When the data after error coding flow into interleaver, in turn circulate and write between RAM A, RAM B and RAM C
Enter, when data write length more than 2 (Ls- 1) when, start to perform read operation to dual port RAM, read diagonal according to master when data
Line direction carries out；
Wherein, leading diagonal contains three directions, is respectively A1-B2-C3, B1-C2-A3 and C1-A2-B3, in reading
During, read to end, continue according still further to other direction, until three directions are all run through according to a direction every time
Untill；Intertexture frame length is determined in interleaver input parameter, which kind of reading sequential combination determined according to by input parameter value；It is logical
Cross the simulation calculation that transmitting terminal interweaves and forms superframe.
Further, weaving length L and the equivalent of a group of planes block cycle TLConsistent, code efficiency and transmit power take
Value blocks duty cycle λ according to the equivalent minimum of a group of planesLDepending on value, wherein
Specifically, the frame structure under helicopter satellite downlink high-speed transfer includes：Superframe-synchronized word, secondary superframe-synchronized
Word and sub- superframe-synchronized word, wherein superframe-synchronized word and the gap length of secondary superframe-synchronized word are deleted not less than maximum caused by blocking
Except length, the frame that superframe-synchronized word, secondary superframe-synchronized word and sub- superframe-synchronized word are all located at each error coding is first.
Error control method of the present invention based on intertexture mapping of perforating, perforation interweave the error control method mapped with good
Good stability, that method is realized is convenient, and by the frame structure in design data transmitting procedure, it is convenient distinguish error coding frame it
Between boundary.
Brief description of the drawings
Fig. 1 is error control algorithm principle schematic of the present invention based on perforation intertexture mapping；
Fig. 2 is the superframe structure figure under high rate data transmission of the present invention；
Fig. 3 is superframe-synchronized State Transferring schematic diagram under high rate data transmission of the present invention；
Fig. 4 is present invention perforation interleaver internal RAM write operation precedence diagram；
Fig. 5 is present invention perforation interleaver internal RAM read operation precedence diagram.
Embodiment
With reference to Figure of description, the present invention will be further described.
Helicopter satellite downlink channel the unshielding period usually can approximation regard constant-parameter channel as.And when blocking
Section airborne station receives signal and flutter fading occurs, the signal-to-noise ratio state for receiving signal strongly reduces therewith, and demodulated equipment is at this time
The phenomenon of losing lock in short-term even occurs.Blocking the period, it is believed that the probability of output codons 0 or 1 is identical after demodulation
, i.e., the credibility of channel is minimum at this time, and the information that earth station sends is deleted by channel.It is periodically since rotor blocks
, therefore the confidence level L of channelcAlso periodic characteristics are showed.
Understood based on above-mentioned, the confidence level distribution that channel in the cycle is blocked in i-th of rotor can be expressed as (1) formula, formula
Middle A is constant, and T is blocked the cycle for rotor, and λ is duty cycle, △ TiFor the undulating value of the i-th cycle T, △ λiFor the i-th cycle duty cycle
Undulating value.
Helicopter rotor rotating speed during stabilized flight usually fluctuates very little, therefore rotor blocks the usual of cycle △ T
Very little.And block duty cycle is influenced to occur relatively large fluctuation by helicopter flight attitude, therefore △ λ can be relatively
Greatly.Actual measurement has been carried out to cycle of the helicopter under smooth flight and circular flight state and duty cycle situation, has been measured
The results show rotor blocks cycle maximum fluctuation within 3%, and statistical result showed rotor blocks the cycle and possesses formula (2) feature,
And the fluctuation randomness bigger of duty cycle, its maximum fluctuation can reach 15%.
T (k)=T0+n(k) (2)
T (k) blocks the time span in cycle, T for k-th of rotor in above formula0For constant, n (k) blocks for k-th of rotor
Periodic noise value, n (k)~N (0, μ2), from being analyzed above, μ is a very small value, in helicopter stabilized flight
Cheng Zhong, it is believed that it is T that rotor, which blocks cycle satisfaction statistics unbiased feature and average,.For convenience of explanation, (1) formula can be simplified
Make：
How airborne station recovers Lc=0, (λ+△ λi)T<The information that ground is sent during t≤T is the key solved the problems, such as.
Field of channel coding is to use interleaving technology to the most common solution method of burst error.Intertexture be original transmission sequence by
Upset according to certain rule, received sequence is reverted to and normally sorts and decode by recipient according to the rule of agreement.The mesh of intertexture
And meaning in the error burst in channel is changed into random error, so as to reach the Error Correct Threshold of error coding,
And then ensure the transmitting of data.In the model studied of the present invention, rotor, which blocks, equally will also result in lasting error code and shows
As.If earth station uses interleaving technology when sending data, then airborne station is when receiving data after deinterleaving is handled
The influence that rotor blocks will be averagely to entirely blocking the cycle.Channel confidence level L during in view of blockingc=0, then airborne station solution friendship
Sequence after knitting is equivalent to earth station and sends the result after coding perforation.
Analyzed based on more than, it can be deduced that conclusion：Earth station to send information carry out Error Correction of Coding, then to Error Correction of Coding after
Sequence be interleaved mapping after launch, one section is had in data frame after helicopter satellite channel rotor blocks under continuously
Data are deleted, and for airborne station after deinterleaving is handled, obtained error coded data is equivalent to earth station's transmission error correction volume
Result after code perforation.In order to facilitate understanding, by the above process as shown in Figure 1, the above method is to interweave what is mapped based on perforation
Helicopter downlink error control algolithm.
In order to ensure that the error control method based on perforation intertexture mapping possesses good stability, it is necessary to take into full account
The time variation of parameter is blocked to rotor, particularly blocks the time variation of duty cycle.Since △ λ may be relatively large, setting
Timing must block duty cycle minimum value λ with what is be likely to occurminFor foundation.In order to meet earth station to " the one of multi rack helicopter
To more " TDM broadcast communication demands, error control method should limit constantly from blocking.Therefore during method realization not
Harm assumes that it is traversal within the cycle to block the moment, then rotor blocks the transmission matrix of channel and accordingly promotes as shown in (4) formula：
H=[HNK,0N,N-M-K,HNM] K=0,1 in formula ..., N (4)
Blocked by rotor and its fluctuation is influenced, the interleaver of helicopter satellite communication downlink suffers from more
Constraint.According to above-mentioned definite model, illustrate for convenience, it is clearly as follows that rotor is blocked relevant parameter by us：T hides for rotor
Keep off cycle, λ ∈ (λmin,λmax) it is duty cycle, t0The specific moment blocked for rotor, and meet t0∈ (0, T), error correcting code output
Code word size L be interleaver input weaving length.The periodic feature blocked in view of rotor, causes to reduce intertexture
Delay, should be consistent when setting weaving length with cycle T.If weaving length is L, the length that interlacing frames are deleted by channel
Spend for L0, transmit an interlacing frames and take as TL, then have in theory：
TL=T (5)
L0=L (1)-λ (6)
By above-mentioned setting, each frame length is that the interlacing frames of L include a length of L0Deletion error.And the meaning to interweave is
By varying transmission order, it is randomized the error burst in channel.In general, a length of L0Data disperse in interlacing frames
More uniform, the effect of intertexture is better.Therefore, interweaved based on perforation in the error control algorithm of mapping, interlacing pattern is to influence
The key point of algorithm effect.The error control method mapped that interweaved based on perforation is substantially to utilize the true form to interweave to transmitting terminal
Error coding carries out equivalent perforation processing, therefore the research to interlacing pattern has to the performance study after perforating with error coding
It is combined.Usually, punching matrix can be retained the system position of error coding.But consider that rotor blocks duty cycle
Fluctuation and rotor block the uncertainty at moment, and guarantee system position is not deleted by channel and is difficult to realize.This is because
If system position is not deleted in the Error Control frame for ensureing to send every time, unshielding section model just must be accurately predicted every time
Enclose.Even if the method by reducing window can determine unshielding section, but hidden from (4) formula, each unshielding section
Distribution in the gear cycle is unfixed, if necessary to ensure that system position is not deleted, then when earth station sends data every time
All dynamically adjustment transmission order, hair it must receive both sides and be difficult to treaty rule.Although therefore the punctured code of system possesses optimal performance,
But in helicopter satellite communication downlink, being blocked fluctuation by rotor is influenced, intertexture is difficult to complete equivalent transmitting terminal mistake
The system position of coding is not perforated, the work that check bit is uniformly perforated.
Although interleaving algorithm can not be equivalent to the perforation just for check bit, small part system actually after error coding
The punctured code of part system obtained from system position participates in perforation still possesses good performance, and corresponding interlacing pattern remains to
Enough obtain preferable effect.In helicopter satellite communication downlink, different type, the error coding of different code checks, it is corresponded to
Perforation interleaving device designing method it is also different.According to being analyzed above, different from conventional interleaver, perforation interleaver has following
Feature：
1. interleaving units are 1bit.
2. must be uniform interleaving.
3. do not pursue interleave depth and width.Based on the punctured code of the corresponding part system of the error correcting code mutually cascaded, root
Go out the mapping ruler that interweaves according to its punching matrix backstepping.
In order to realize the superframe-synchronized under helicopter satellite downlink high rate data transmission, three kinds of synchronizations are devised altogether
Word：Superframe-synchronized word, secondary superframe-synchronized word and synchronizing sub-frame word.In fig. 2, superframe length, L are represented with LdRepresent superframe-synchronized
Word and secondary superframe-synchronized word space length.Secondary superframe-synchronized word is the equal of the backup to superframe-synchronized word, its significance lies in that
Remain to complete superframe-synchronized after superframe-synchronized word is deleted by channel, therefore have Ld≥L(1-λmin), i.e., superframe-synchronized word with
Secondary superframe-synchronized word interval length is not less than the maximum deletion length caused by blocking.Superframe-synchronized word, secondary superframe-synchronized word and
The frame that synchronizing sub-frame word is all located at each error coding frame is first, can distinguish the boundary between error coding frame.
If representing that recipient detects successfully superframe-synchronized word with event A, event B represents to detect secondary superframe-synchronized word
Success, event C represent detect successfully sub- superframe-synchronized word, if representing desynchronizing state with digital 0,3 expression synchronous regimes, 1,2,
5 and 6 represent the plesiochronous mode under different situations respectively, and 4 represent quasi- desynchronizing state, then the superframe-synchronized machine under high rate data transmission
System is as shown in Figure 3.
In figure 3, it is necessary to especially emphasize some following problem：
1. for airborne station when synchronizing detection to receiving sequence, testing mechanism is different in the state of difference.
During desynchronizing state 0, airborne station carries out continuous coherent detection to receiving sequence；Once into plesiochronous mode 1,2,5 or 6
When, the position of next synchronization character will be calculated according to synchronous word location and the error coding frame length detected, carry out designated position
Coherent detection；When in synchronous regime 3 or quasi- desynchronizing state 4, by the match condition of designated position and its synchronization character into
Row detection.
2. if superframe-synchronized word and secondary superframe-synchronized word are referred to as superframe level synchronization character, then by desynchronizing state 0 into
Entering synchronous regime 3 needs receiving terminal to detect a superframe level synchronization character and more than twice synchronizing sub-frame word in succession, by synchronous shape
The necessary and sufficient condition that state 3 is transferred to desynchronizing state 0 is superframe-synchronized word, secondary superframe-synchronized word and all synchronizing sub-frames therebetween
Word all detection failures.
3. phase fuzzy problem caused by for being blocked as rotor, can be disappeared by using the mode that synchronization character detects
Remove.Airborne station is known to blocking section when receiving signal, thus can according to block arrive before and block end
Synchronization character testing result afterwards corrects phase ambiguity, and synchronization character detection here includes all types of synchronization characters.
In helicopter satellite communication downlink, earth station generally requires to face the problem of communicating with multi rack helicopter, special
It is not that ground needs to establish the TDM broadcast communications of " one-to-many ", therefore downlink error control with going straight up to a group of planes under some situations
Algorithm processed can compatible multi-model there is realistic meaning.In order to meet compatibility of the error control algorithm to multi-model, it is contemplated that
Duty cycle is blocked there may be significantly difference and fluctuation between helicopter inside a group of planes, in specific system design
When, in order to farthest ensure the robustness of system, we can be blocked in duty cycle set most with going straight up to group of planes rotor
Small value is design considerations.In this case, duty cycle of the error control algorithm mapped using being interweaved based on perforation to a group of planes
Fluctuation adaptability and the fluctuation adaptability to single rack helicopter duty cycle do not have essential distinction.
Rotor, which blocks the otherness of cycle T, between helicopter can be equivalent to the fluctuation of duty cycle λ.Brought in multi-model
A variety of rotors are blocked under cycle situation, and weaving length can not meet the matching that the cycle is blocked with all rotors.When weaving length with
Rotor block the cycle it is inconsistent when, rotor blocks can disagree intertexture frame deletion ratio with blocking duty cycle.At this time, due to
The influence that weaving length is brought with cycle mismatch is considered as duty cycle λ and is fluctuated.Therefore, interweaved based on perforation and mapped
Fluctuation of the error control algorithm to duty cycle λ it is adaptable.
It is assumed that it is T={ T that its rotor of a group of planes for N framves helicopter composition, which blocks periodic set,1,T2,……,TN, minimum hides
Keep off duty cycle set λ={ λ1,λ2,……,λN, then the average value that group of planes rotor blocks the cycle is：
If system is μ={ μ to the priority factors that every frame helicopter communication stability requires1,μ2,……,μN, wherein 0
≤μi≤ 1, then equivalent rotor corresponding with intertexture frame length blocks cycle TLCalculation procedure is as follows：
TL=TLN(9)
Every frame helicopter is in equivalent period T at this timeLIn equivalent minimum block duty cycle and be：
In order to ensure the stability of system design, we block duty cycle to set using the minimum equivalent being likely to occur in a group of planes
Foundation is counted, therefore is had：
By result above, when error-control schemes design, weaving length L should block cycle T with the equivalent of a group of planesLXiang Yi
Cause, and the value of code efficiency and transmit power also needs to block duty cycle λ according to the equivalent minimum of a group of planesLDepending on value.To list
The correlative study of one helicopter is actually a special case in group of planes research, i.e. group of planes aircraft frame number is 1, and the above is to a group of planes
Rotor blocks the cycle and after duty cycle has carried out Equivalent Calculation, perforation interleaving device designing method corresponding with a group of planes and to list
No any difference is compared in the design of one helicopter.
The present invention proposes the error control algorithm based on perforation interleaver suitable for helicopter satellite downlink, with
General purpose communication module is different, and perforation interleaver and its distinctive frame structure have specificity feature.It is of the invention main to introduce pair
It carries out the method for Project Realization.
The broadband connections advantage possessed in view of helicopter satellite communication, therefore research object of the present invention is mainly to exist
High-speed transfer RsCarried out under the conditions of >=625Kbps, at the same in also supporting low rate transmission, using the mechanism of superframe transmissions,
Rate-matched, interleaver, framing module, synchronization module and deinterleaver are mainly completed when system algorithm is realized.
During carrying out Project Realization to the method for the present invention, the exploitation of Atera companies Quartus II 11.0 editions has been used
Software, and the simulation software of Modelsim 6.5f editions are emulated.(note：The English being related to below is in the simulation software
The title used, these English usages are known for those skilled in the art.)
1. transmitting terminal correlation module structure design
According to superframe design scheme under high rate data transmission, the present invention provides form superframe after transmitting terminal perforated interleaver
Implementation method, the data after Error Correction of Coding is exported first are input to perforation interleaver, if Error Correction of Coding clock during this
With perforation interleaver clock it is inconsistent when, it is also necessary to carry out rate-matched.When data input perforation interleaver, in interleaving block
Portion has mainly used two-port RAM, and perforation interleaving process is realized by way of the address function to two-port RAM.
In transmitting terminal, the implementation method for interleaver of perforating is core place.With block interleaver general at present, convolutional interleave
Device is different, and perforation interleaver proposed by the present invention belongs to tailored version interleaver, employs 3 dual port RAMs, be referred to as RAM A,
RAM B and RAM C, when the data after error coding flow into interleaver, we in turn RAM A, RAM B and RAM C it
Between recurrent wrIting, as shown in figure 4, when data write length more than 2 (Ls- 1) when, start to perform dual port RAM read operation, such as scheme
Shown in 5, read to carry out according to leading diagonal direction when data.
It must be noted that in Figure 5, leading diagonal contains three directions, is referred to as A1-B2-C3, B1-
C2-A3 and C1-A2-B3.During data are read, read every time according to a direction to end, according still further to other direction after
It is continuous, untill three directions are all run through.Intertexture frame length, therefore root are determined in interleaver i_rate_type input parameters
Which kind of reading sequential combination can be determined according to by i_rate_type values.Interweaved by transmitting terminal and form the emulation meter of superframe
Calculate, its output waveform data compares the correctness for demonstrating perforation intertexture Mapping implementation, and interleaving delay is about 34ms.
2. receiving terminal correlation module structure design
Receiving terminal main modular includes Synchr synchronization modules and Deintleaver deinterleaver modules, in helicopter machine
Station demodulated equipment output log-likelihood ratio data are carried, Synchr modules are after log-likelihood ratio data are connected to, according to synchronous machine
Principle work processed, and the data after synchronization are exported and implement according to perforation interleaving mode corresponding to deinterleaver, deinterleaver
Deinterleave operation, data after deinterleaving i.e. with the corresponding likelihood ratio information of error coding.
There is identical i_rate_type input parameters in two modules, the input parameter of this and interleaver is consistent
, for confirming the superframe length under different rates.Synchr modules are before the coherent detection to synchronization character, first to likelihood ratio number
According to carrying out hard decision, when carrying out relevant peaks calculating to hard decision sequence, core dumped transition probability during generally according to channel unshielding
Set threshold value.Detection synchronization character includes to synchronization character in itself and the fuzzy pattern that is likely to occur of synchronization character is examined comprehensively
Survey, and corresponding fringe o_phase_state is exported according to testing result.In view of above to the specific of perforation interleaver
Operation principle elaborates, and it is entirely the mirrored procedure realized and interweaved to deinterleave, therefore to the specific implementation of deinterleaving
Do not repeat.
Us are designed more than realizes receiving terminal superframe-synchronized and the correlated process deinterleaved, is provided compared to transmitting terminal
Source takes quantity and has increased, this is because taking 6bit bit wides, logarithm with sending the corresponding reception log-likelihood ratio of coding
Likelihood ratio takes bit wide and can lengthen or reduce as needed.In order to actual closer to helicopter communication, in Modelsim emulation
During, it with the addition of the influence that rotor blocks when test script is write, simulation result Display Realization superframe-synchronized and be directed to
Perforation interweave mapping deinterleaving work, deinterleave delay be about 34ms, with reference to transmitting terminal be delayed communication process in interweave altogether
Delay is about 68ms.
More than, it is only presently preferred embodiments of the present invention, but protection scope of the present invention is not limited thereto, and it is any to be familiar with sheet
Those skilled in the art the invention discloses technical scope in, the change or replacement that can readily occur in should all be covered
Within protection scope of the present invention.Therefore, protection scope of the present invention should be subject to the protection domain that claim is defined.
Claims (1)
- A kind of 1. error control method for the mapping that interweaved based on perforation, it is characterised in that including：Earth station carries out Error Correction of Coding to sending information, and it is laggard that perforation interleaver is interleaved the sequence after Error Correction of Coding mapping Row transmitting；To receiving data after deinterleaving is handled, obtained error coded data is equivalent to earth station and sends error correction volume airborne station Result after code perforation carries out equivalent perforation processing using the true form error coding to interweave to transmitting terminal；Weaving length L and a group of planes Equivalent block cycle TLConsistent, the value of code efficiency and transmit power blocks duty cycle λ according to the equivalent minimum of a group of planesL Depending on value, wherein
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810069448.7A CN108023681B (en) | 2015-03-13 | 2015-03-13 | Error control method based on puncture interleaving mapping |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810069448.7A CN108023681B (en) | 2015-03-13 | 2015-03-13 | Error control method based on puncture interleaving mapping |
| CN201510112636.XA CN104796224B (en) | 2015-03-13 | 2015-03-13 | Interweaved the error control method mapped based on perforation |
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| CN201510112636.XA Division CN104796224B (en) | 2015-03-13 | 2015-03-13 | Interweaved the error control method mapped based on perforation |
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| CN108023681A true CN108023681A (en) | 2018-05-11 |
| CN108023681B CN108023681B (en) | 2020-06-05 |
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| CN201810069450.4A Active CN107979448B (en) | 2015-03-13 | 2015-03-13 | Error control method based on puncture interleaving mapping |
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| CN1567731A (en) * | 1999-03-31 | 2005-01-19 | 松下电器产业株式会社 | Radio communication device and method |
| CN101322317A (en) * | 2005-05-12 | 2008-12-10 | 高通股份有限公司 | Apparatus and method for channel interleaving in communications system |
| EP2249501A2 (en) * | 2009-05-04 | 2010-11-10 | Electronics and Telecommunications Research Institute | Method and apparatus for transmitting/receiving data using satellite channel |
| US20140229801A1 (en) * | 2013-02-10 | 2014-08-14 | Hughes Network Systems, Llc | Apparatus and method for improved modulation and coding schemes for broadband satellite communications systems |
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| CN100393012C (en) * | 2002-09-09 | 2008-06-04 | 西南交通大学 | Method for parallelly-redundantly transmitting and parallelly-merging and receiving block data in mixed automatic retransmission request system |
| DE60313505T2 (en) * | 2003-02-13 | 2007-12-27 | Ntt Docomo Inc. | DIFFERENTIAL TRANSMISSION AND RECEPTION DIVERSITY WITH MULTIPLE LENGTH |
| US8566676B2 (en) * | 2007-01-05 | 2013-10-22 | Qualcomm Incorporated | FEC code and code rate selection based on packet size |
| CN102201881B (en) * | 2010-03-23 | 2014-08-13 | 中国电子科技集团公司第三十六研究所 | Blind identification method of convolutional interleaving |
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| CN1567731A (en) * | 1999-03-31 | 2005-01-19 | 松下电器产业株式会社 | Radio communication device and method |
| CN101322317A (en) * | 2005-05-12 | 2008-12-10 | 高通股份有限公司 | Apparatus and method for channel interleaving in communications system |
| EP2249501A2 (en) * | 2009-05-04 | 2010-11-10 | Electronics and Telecommunications Research Institute | Method and apparatus for transmitting/receiving data using satellite channel |
| US20140229801A1 (en) * | 2013-02-10 | 2014-08-14 | Hughes Network Systems, Llc | Apparatus and method for improved modulation and coding schemes for broadband satellite communications systems |
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| CN104796224B (en) | 2018-02-09 |
| CN108282267B (en) | 2020-06-05 |
| CN108023681B (en) | 2020-06-05 |
| CN107979448A (en) | 2018-05-01 |
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