CN108282267B - Error control method based on puncture interleaving mapping - Google Patents
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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 invention discloses an error control method based on puncture interleaving mapping, and provides a new method aiming at the problem of error control when a ground station communicates with helicopters (groups). The method comprises the following steps: the ground station carries out error correction coding on the transmitted information, and the puncture interleaver carries out interleaving mapping on the sequence after error correction coding and then transmits the sequence; the airborne station de-interleaves the received data to obtain error coded data equivalent to the result of the ground station transmitting error correction coding and puncturing, and performs equivalent puncturing on the original code error coding of the transmitting end by interleaving. The invention can more fully excavate the downlink channel capacity of the helicopter satellite and effectively solve the problem of error control of helicopter rotor shielding.
Description
The present application is filed as a divisional application of the invention title 2015, 03/13, application No. 201510112636, X, based on an error control method of punctured interleaving mapping.
Technical Field
The invention relates to an error control method based on puncture interleaving mapping.
Background
In a helicopter satellite downlink, when a ground station transmits information to a helicopter (group), the circular motion of the helicopter rotor blades can cause obstruction to satellite relay signals. In the rotor wing sheltering time period, information transmitted by the ground station is usually deleted, a section of continuous data is deleted in a data frame after the helicopter satellite signal passes through the rotor wing sheltered, and the deleted continuous data is sheltered deletion data. Meanwhile, the rotor is influenced by the navigational speed, the course and the flight attitude of the helicopter, the shielding period and the duty ratio of the rotor have time-varying property, and the corresponding deleting position and deleting length also have time-varying property, so that the technical difficulty is increased for error control.
Disclosure of Invention
In view of the above problems, the present invention provides an error control method based on puncture interleaving mapping, which can effectively solve the problem of error control of rotor occlusion when information is transmitted from a ground station.
In order to achieve the above object, the present invention provides an error control method based on punctured interleaving mapping, comprising:
the ground station carries out error correction coding on the transmitted information, and the puncture interleaver carries out interleaving mapping on the sequence after error correction coding and then transmits the sequence;
the airborne station de-interleaves the received data to obtain error coded data equivalent to the result of the ground station transmitting error correction coding and puncturing, and performs equivalent puncturing on the original code error coding of the transmitting end by interleaving.
Furthermore, the interleaving unit of the puncturing interleaver is 1bit, uniform interleaving is performed, and an interleaving mapping rule is reversely deduced according to a puncturing matrix of the puncturing interleaver on the basis of partial system erasure codes corresponding to the cascaded error correcting codes.
Specifically, the specific method for the transmitting end to perform the puncture interleaving mapping on the error correction coded sequence is as follows: adopts 3 double-port RAMs which are respectively RAM A, RAM B and RAM C,
when error-encoded data flows into the interleaver, the data is cyclically written among the RAM A, the RAM B and the RAM C in sequence, and when the data writing length exceeds 2 (L)s-1), starting to execute read operation on the dual-port RAM, and reading data according to the main diagonal direction;
the main diagonal line comprises three directions, namely A1-B2-C3, B1-C2-A3 and C1-A2-B3, in the process of reading data, reading is carried out to the end according to one direction each time, and then the reading is continued according to the other direction until all the three directions are completely read; the length of an interleaving frame is determined by inputting parameters in the interleaver, and the reading sequence combination is determined according to the input parameter values; and (4) carrying out simulation calculation by interleaving and forming a superframe through a transmitting end.
Further, the interleaving length L is equal to the equivalent occlusion period T of the clusterLThe consistency is consistent with that of the raw materials,the coding efficiency and the sending power are taken according to the equivalent minimum shielding duty ratio lambda of the clusterLIs given a value, wherein
Specifically, the frame structure under helicopter satellite downlink high-speed transmission includes: the super frame synchronous words, the sub super frame synchronous words and the sub super frame synchronous words are arranged at the head of each error coding frame.
The error control method based on the perforation interleaving mapping has good stability and convenient realization, and the boundary between error coding frames is conveniently distinguished by designing the frame structure in the data transmission process.
Drawings
FIG. 1 is a schematic diagram of the error control algorithm based on the punctured interleaving mapping according to the present invention;
FIG. 2 is a block diagram of a superframe at high rate transmission according to the present invention;
FIG. 3 is a diagram illustrating the transition of superframe synchronization status in high rate transmission according to the present invention;
FIG. 4 is a diagram illustrating a sequence of RAM write operations within a puncture interleaver according to the present invention;
fig. 5 is a diagram of a read operation sequence of the RAM inside the punctured interleaver of the present invention.
Detailed Description
The invention is further described with reference to the accompanying drawings.
The helicopter satellite downlink channel can be generally considered approximately as a constant parameter channel during periods of non-occlusion. And in the sheltering period, the receiving signal of the airborne station can be sharply faded, the signal-to-noise ratio state of the receiving signal is sharply reduced, and the demodulation equipment can even have the phenomenon of short-time lock losing. In the sheltered time period, the probability of outputting the code word 0 or 1 after demodulation is considered to be the same, namely the credibility of the channel is the lowest at the moment, and the information sent by the ground station is deleted by the channelIs removed. Since rotor shadowing is periodic, the confidence L of the channelcAlso exhibits a periodic character.
Based on the above, the confidence distribution of the channel in the ith rotor-wing shielding period can be expressed as formula (1), where a is a constant, T is the rotor-wing shielding period, λ is the duty cycle, and Δ T isiIs the fluctuation value of the ith period T, Δ λiIs the fluctuation value of the duty ratio of the ith period.
The rotor speed typically fluctuates very little during steady flight of the helicopter, and therefore the rotor shading period Δ T is typically very small. Whereas the shading duty cycle may fluctuate relatively much as a result of the helicopter flight attitude and so Δ λ may be relatively large. The period and duty ratio conditions of the helicopter in the stable flight state and the circumferential flight state are actually measured, the measurement result shows that the maximum fluctuation of the rotor shielding period is within 3%, the statistical result shows that the rotor shielding period has the characteristic of the formula (2), the fluctuation randomness of the duty ratio is larger, and the maximum fluctuation can reach 15%.
T(k)＝T0+n(k) (2)
Where T (k) is the length of time of the kth rotor period of occlusion, T0Is constant, N (k) is the k-th rotor blade shading period noise value, N (k) N (0, mu)2) From the above analysis, it can be seen that μ is a very small value, and during the steady flight of the helicopter, the rotor occlusion period is considered to satisfy the statistical unbiased characteristic and the mean value is T. For convenience of explanation, equation (1) may be simplified as follows:
how an onboard station recovers Lc＝0,(λ+Δλi) The key to solve the problem is the information sent by the time when T is more than T and less than T. The most common solution to burst errors in the field of channel coding is to use interleaving. The interleaving is to make the original transmission sequence according to a certain ruleAnd (4) scrambling, and restoring the received sequence to normal sequence and decoding by the receiver according to an agreed rule. The purpose and meaning of interleaving is to convert burst bit errors in a channel into random bit errors, so that the error correction threshold of error coding can be reached, and reliable transmission of data is further ensured. In the model studied by the invention, rotor occlusion also causes continuous error phenomena. If the ground station adopts the interleaving technology when sending data, the influence of rotor occlusion after the airborne station receives the data and carries out de-interleaving processing can be averaged to the whole occlusion period. Channel confidence L when occlusion is consideredcWhen the value is 0, the sequence after the deinterleaving of the airborne station is equivalent to the result after the coded puncture is sent by the ground station.
Based on the above analysis, it can be concluded that: the ground station carries out error correction coding on the transmitted information, then carries out interleaving mapping on the sequence after the error correction coding and then transmits the sequence, a section of continuous data in a data frame is deleted after the helicopter satellite channel under the shielding of the rotor wing, and the error coding data obtained after the airborne station carries out de-interleaving processing is equivalent to the result of the ground station transmitting the error correction coding and puncturing. For ease of understanding, the above process is illustrated in fig. 1, and the above method is a helicopter downlink error control algorithm based on a punctured interleaving map.
In order to ensure good stability of the error control method based on the puncture interleaving mapping, the time-varying property of the rotor occlusion parameters, especially the time-varying property of the occlusion duty ratio, must be fully considered. Since Δ λ may be relatively large, it is necessary to design with the minimum value λ of the shading duty cycle that may occurminThe basis is. In order to meet the requirement of the ground station for the one-to-many TDM broadcast communication of a plurality of helicopters, the error control method should not be limited by the blocking time. Therefore, in the implementation process of the method, it is not assumed that the occlusion time is traversed in the period, and the transmission matrix of the rotor occlusion channel is correspondingly generalized as shown in formula (4):
H＝[HNK,0N,N-M-K,HNM]where K is 0,1, … …, N (4)
Under the influence of rotor shielding and fluctuation thereof, the interleaver of the satellite communication downlink of the helicopterAre more constrained. From the above-identified model, for convenience of explanation, we make explicit the rotor occlusion related parameters as follows: t is the rotor shielding period, and lambda belongs to (lambda)min,λmax) Is the duty ratio, t0For a specific moment of rotor-wing shelter, and satisfy t0E (0, T), the codeword length L of the error correction code output is the interleaving length of the interleaver input. In order to reduce the delay caused by interleaving, considering the periodic characteristic of rotor shielding, the interleaving length should be set to be consistent with the period T. If the interleaving length is L, the length of the interleaved frame deleted by the channel is L0The transmission of an interlaced frame takes time TLThen, theoretically:
TL＝T (5)
L0＝L(1-λ) (6)
with the above setting, each interleaved frame with the length of L includes the length of L0The deletion error of (2). The significance of interleaving is to randomize burst errors in the channel by changing the transmission order. In general, the length is L0The more evenly the data of (a) is dispersed in the interleaved frame, the better the interleaving effect. Therefore, in the error control algorithm based on the punctured interleaving map, the interleaving pattern is the key to influence the algorithm effect. The error control method based on the puncture interleaving mapping is essentially to perform equivalent puncturing processing on the original code error coding of a transmitting end by utilizing interleaving, so that the research on an interleaving pattern needs to be combined with the performance research after error coding puncturing. Typically, the puncturing matrix will retain error coded systematic bits. However, it is difficult to ensure that the system bits are not deleted by the channel considering the fluctuation of the rotor occlusion duty cycle and the uncertainty of the rotor occlusion time. This is because the non-occlusion interval range must be accurately predicted each time if it is guaranteed that systematic bits are not erased in the error control frame transmitted each time. Even though the non-shielding interval can be determined by the window reduction method, the formula (4) shows that the distribution of the non-shielding interval in the shielding period is not fixed every time, if the system bit is required to be ensured not to be deleted, the ground station must dynamically adjust the transmission sequence every time the data is transmitted, and the transmitter and the receiver have difficulty in agreeing with the rule. Thereby exhausting the pipe systemThe systematic erasure code has the optimal performance, but in a helicopter satellite communication downlink, due to the influence of rotor shielding fluctuation, interleaving is difficult to complete the work of systematic bit non-puncturing and check bit uniform puncturing of the error code of the equivalent sending end.
Although the interleaving algorithm is not equivalent to puncturing only for the check bits, in practice, partial systematic erasure codes obtained by puncturing a small number of systematic bits after error coding still have good performance, and the corresponding interleaving patterns still can achieve ideal effects. In a helicopter satellite communication downlink, error codes with different types and different code rates have different corresponding puncture interleaver design methods. According to the above analysis, unlike the conventional interleaver, the punctured interleaver has the following characteristics:
1. the interleaving unit is 1 bit.
2. Uniform interleaving is necessary.
3. Interleaving depth and width are not pursued. Based on partial system erasure codes corresponding to the cascaded error correcting codes, the interleaving mapping rule is reversely deduced according to the puncturing matrix.
In order to realize superframe synchronization under helicopter satellite downlink high-rate transmission, three types of synchronization words are designed: super frame sync words, sub-super frame sync words, and sub-frame sync words. In fig. 2, the superframe length is denoted by L, LdIndicating the interval length of the super frame sync word and the sub-super frame sync word. The sub-super frame sync word is equivalent to a backup of the super frame sync word in the sense that super frame synchronization is still accomplished after the super frame sync word is deleted by the channel, and thus has Ld≥L(1-λmin) That is, the interval length between the super frame sync word and the sub-super frame sync word is not less than the maximum deletion length caused by occlusion. The super, sub-super and sub-frame sync words are located at the beginning of each error encoded frame and can distinguish the boundaries between error encoded frames.
If the event a indicates that the receiving side successfully detects the superframe sync word, the event B indicates that the sub-superframe sync word is successfully detected, the event C indicates that the sub-superframe sync word is successfully detected, and if the number 0 indicates the out-of-sync state, 3 indicates the sync state, 1, 2, 5, and 6 respectively indicate the quasi-sync states in different situations, and 4 indicates the quasi-out-of-sync state, the superframe synchronization mechanism under high-rate transmission is as shown in fig. 3.
In fig. 3, the following problems need to be particularly emphasized:
1. when the airborne station carries out synchronous detection on the received sequence, the detection mechanism is different under different states. When the out-of-step state is 0, the airborne station carries out continuous correlation detection on the received sequence; once entering into quasi-synchronous state 1, 2, 5 or 6, calculating the position of next synchronous word according to the detected synchronous word position and error coding frame length, and carrying out relative detection of designated position; when in the synchronous state 3 or the quasi-asynchronous state 4, the matching condition of the specified position and the synchronous word thereof is detected.
2. If the super frame sync word and the sub-super frame sync word are collectively referred to as super frame level sync word, entering the sync state 3 from the out-of-sync state 0 requires the receiving end to successively detect the super frame level sync word and the sub-frame sync word more than twice, and the sufficient condition for entering the out-of-sync state 0 from the sync state 3 is that all detection of the super frame sync word, the sub-super frame sync word and all the sub-frame sync words therebetween fails.
3. The phase ambiguity problem caused by rotor occlusion can be eliminated by adopting a synchronous word detection mode. The on-board station is known for the occlusion interval when receiving the signal, and can therefore correct the phase ambiguity according to the detection results of the sync word before the occlusion comes and after the occlusion ends, where the sync word detection contains all types of sync words.
In a helicopter satellite communication downlink, a ground station is often required to face the problem of communicating with a plurality of helicopters, particularly in some cases, the ground is required to establish one-to-many TDM broadcast communication with a helicopter group, and therefore, whether a downlink error control algorithm can be compatible with a plurality of helicopter types has a practical significance. In order to meet the compatibility of an error control algorithm to multiple models, considering that the shielding duty ratio between helicopters in a helicopter fleet can have large-degree difference and fluctuation, when a specific system is designed, in order to guarantee the robustness of the system to the maximum degree, the minimum value in a helicopter fleet rotor shielding duty ratio set can be used as a design basis. In this case, the error control algorithm based on the perforation interleaving mapping is adopted, so that the fluctuation adaptability of the duty ratio of the cluster and the fluctuation adaptability of the duty ratio of the single helicopter are not essentially different.
The difference in rotor blade shading periods T between helicopters can be equated to fluctuations in duty ratio λ. Under the condition of multiple rotor wing shielding periods brought by multiple models, the interweaving length cannot meet the requirement of matching with all rotor wing shielding periods. When the interweaving length is inconsistent with the rotor wing sheltering period, the rotor wing sheltering frame deleting proportion and the sheltering duty ratio can be in and out. At this time, the influence of mismatch between the interleaving length and the period may be considered as fluctuation of the duty ratio λ. Therefore, the error control algorithm based on the punctured interleaving map has adaptability to the fluctuation of the duty ratio λ.
Assuming that the rotor shielding period set of the cluster consisting of N helicopters is T ═ T1,T2,……,TNH, a set of minimum occlusion duty cycles λ ═ λ1,λ2,……,λNAnd the average value of the blocking period of the fleet rotors is:
the priority factor of the system for the communication stability requirement of each helicopter is set as mu ═ mu1,μ2,……,μ N0 is less than or equal to muiLess than or equal to 1, so that the equivalent rotor wing shielding period T corresponding to the interweaving frame lengthLThe calculation steps are as follows:
TL＝TLN(9)
at the moment, each helicopter is in an equivalent period TLThe equivalent minimum occlusion duty cycle in (1) is:
in order to ensure the stability of system design, we use the minimum equivalent occlusion duty cycle that may occur in the cluster as the design basis, so there are:
from the above results, the interleaving length L should be equal to the equivalent occlusion period T of the cluster when the error control scheme is designedLConsistent with each other, the values of the coding efficiency and the transmission power also need to be obtained according to the equivalent minimum shielding duty ratio lambda of the clusterLThe value depends on. The related research on a single helicopter is actually a special case in the research on the fleet, namely the number of the aircraft frames in the fleet is 1, and after equivalent calculation is carried out on the rotor shielding period and the duty ratio of the fleet, no difference exists between the design method of the perforated interleaver corresponding to the fleet and the design of the single helicopter.
The invention provides an error control algorithm based on a puncture interleaver, which is suitable for a helicopter satellite downlink, and different from a universal communication module, the puncture interleaver and a special frame structure thereof have special characteristics. The invention mainly introduces a method for realizing engineering of the system.
Considering the advantages of broadband communication of helicopter satellite communication, the invention mainly aims to transmit R at high speedsThe method is carried out under the condition of being more than or equal to 625Kbps, meanwhile, the transmission of medium and low rates is supported, a superframe transmission mechanism is adopted, and rate matching, an interleaver, a framing module, a synchronization module and a deinterleaver are mainly completed when a system algorithm is realized.
In the process of implementing the engineering of the method, development software of the Atera company Quartus II 11.0 version and simulation software of the Modelsim 6.5f version are used for simulation. (Note: the English words referred to below are names used in the simulation software, and the usage of the English words is known to those skilled in the art.)
1. Structure design of related module of transmitting terminal
According to the super-frame design scheme under high-speed transmission, the invention provides a method for realizing the super-frame formation by a transmitting terminal through a puncture interleaver. When data is input into the puncturing interleaver, the interleaving module mainly uses a dual-port RAM, and the puncturing interleaving process is realized by operating the address of the dual-port RAM.
At the transmitting end, the implementation method of the puncture interleaver is the core. Different from the current general block interleaver and convolution interleaver, the puncture interleaver provided by the invention belongs to a special interleaver, 3 double-port RAMs are adopted and respectively called as RAM A, RAM B and RAM C, when error-coded data flows into the interleaver, the data are circularly written among the RAM A, the RAM B and the RAM C in sequence, as shown in figure 4, when the data writing length exceeds 2(L is L)s-1), starting to perform read operation on the dual-port RAM, as shown in fig. 5, and reading data according to the main diagonal direction.
It should be noted that in FIG. 5, the main diagonal contains three directions, which are referred to as A1-B2-C3, B1-C2-A3, and C1-A2-B3, respectively. In the process of reading data, after reading to the end according to one direction each time, continuing according to the other direction until all the data are read in the three directions. Since the interleaving frame length is determined by the interleaver i _ rate _ type input parameter, which readout order combination can be determined by the i _ rate _ type value. Through the simulation calculation of interleaving and forming a superframe at the transmitting end, the output waveform data comparison proves the correctness of the realization of the perforation interleaving mapping, and the interleaving delay is about 34 ms.
2. Receiving end related module structure design
The main module of the receiving end comprises a Synchr synchronization module and a deinteleaver de-interleaver module, log likelihood ratio data is output from a demodulation device of a helicopter airborne station, the Synchr module works according to the principle of a synchronization mechanism after receiving the log likelihood ratio data and outputs the synchronized data to a de-interleaver, the de-interleaver implements corresponding de-interleaving operation according to a perforation interleaving mode, and the de-interleaved data is likelihood ratio information corresponding to error codes.
There is the same i _ rate _ type input parameter in both modules, which is consistent with the input parameter of the interleaver, to confirm the superframe length at different rates. Before the synchronous word correlation detection, the Synchr module performs hard decision on the likelihood ratio data, and when the hard decision sequence is subjected to correlation peak calculation, a threshold value is usually set according to the error transfer probability of a channel non-shielding period. Detecting sync words includes detecting the sync words themselves and possible fuzzy patterns of the sync words comprehensively and outputting corresponding fuzzy states o _ phase _ state based on the detection results. In view of the foregoing detailed description of the specific working principle of the hole interleaver, the de-interleaving is a mirror process for implementing the interleaving, and therefore the detailed implementation of the de-interleaving is not described again.
Through the design, the relative processes of superframe synchronization and deinterleave of the receiving end are realized, and compared with the fact that the number of occupied resources of the sending end is increased, the receiving log-likelihood ratio corresponding to the sending code occupies 6bit of bit width, and the bit width occupied by the log-likelihood ratio can be lengthened or reduced according to needs. In order to be closer to helicopter communication practice, in the process of Modelsim simulation, the influence of rotor shielding is added during test script writing, and simulation results show that superframe synchronization and de-interleaving work aiming at perforation interleaving mapping are realized, the de-interleaving delay is about 34ms, and the total interleaving delay in the delay communication process of a sending end is about 68 ms.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are also included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope defined by the claims.
Claims (1)
1. An error control method based on punctured interleaving mapping, comprising:
the ground station carries out error correction coding on the transmitted information, and the puncture interleaver carries out interleaving mapping on the sequence after error correction coding and then transmits the sequence;
the machine carries on the deinterleave to the received data, the error coded data obtained is equivalent to the result after the ground station sends the error correction code and punctures, the error control method uses the interleaving to process the equivalent puncture to the original code error code of the sending end;
the interleaving unit of the puncturing interleaver is 1bit, uniform interleaving is carried out, and an interleaving mapping rule is reversely deduced according to a puncturing matrix of the puncturing interleaver on the basis of partial system erasure codes corresponding to the cascaded error correcting codes.
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1567731A (en) * | 1999-03-31 | 2005-01-19 | 松下电器产业株式会社 | Radio communication device and method |
| EP2249501A2 (en) * | 2009-05-04 | 2010-11-10 | Electronics and Telecommunications Research Institute | Method and apparatus for transmitting/receiving data using satellite channel |
| CN102201881A (en) * | 2010-03-23 | 2011-09-28 | 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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| 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 |
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| US8566676B2 (en) * | 2007-01-05 | 2013-10-22 | Qualcomm Incorporated | FEC code and code rate selection based on packet size |
| US9246634B2 (en) * | 2013-02-10 | 2016-01-26 | Hughes Network Systems, Llc | Apparatus and method for improved modulation and coding schemes for broadband satellite communications systems |
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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 |
| EP2249501A2 (en) * | 2009-05-04 | 2010-11-10 | Electronics and Telecommunications Research Institute | Method and apparatus for transmitting/receiving data using satellite channel |
| CN102201881A (en) * | 2010-03-23 | 2011-09-28 | 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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| CN107979448B (en) | 2020-06-05 |
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| CN107979448A (en) | 2018-05-01 |
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| CN108023681B (en) | 2020-06-05 |
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