CN106772484A - Power ratio and carrier phase relationship method of adjustment between satellite navigation signals multi -components - Google Patents
Power ratio and carrier phase relationship method of adjustment between satellite navigation signals multi -components Download PDFInfo
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- CN106772484A CN106772484A CN201611241209.2A CN201611241209A CN106772484A CN 106772484 A CN106772484 A CN 106772484A CN 201611241209 A CN201611241209 A CN 201611241209A CN 106772484 A CN106772484 A CN 106772484A
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- permanent envelope
- look
- signal
- envelope look
- latch cicuit
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Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/13—Receivers
- G01S19/35—Constructional details or hardware or software details of the signal processing chain
- G01S19/37—Hardware or software details of the signal processing chain
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/13—Receivers
- G01S19/24—Acquisition or tracking or demodulation of signals transmitted by the system
- G01S19/29—Acquisition or tracking or demodulation of signals transmitted by the system carrier including Doppler, related
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/13—Receivers
- G01S19/34—Power consumption
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- Engineering & Computer Science (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Computer Networks & Wireless Communication (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Signal Processing (AREA)
- Radio Relay Systems (AREA)
Abstract
Power ratio and carrier phase relationship method of adjustment between satellite navigation signals multi -components, permanent envelope look-up table is produced first and upper note to satellite-signal generates load, then control navigation signal generation load receives latch cicuit and receives and store permanent envelope look-up table using the triplication redundancy with feedback branch, permanent envelope look-up table is inserted into FPGA inside Slice, finally controls navigation signal generation load to generate navigation signal using permanent envelope look-up table.The present invention carries out triplication redundancy design by the circuit with feedback branch, solve the problems, such as the correction after single-particle inversion, can be corrected when permanent envelope look-up table is because of single-particle inversion, single-particle inversion will not be accumulated, it is ensured that the steady and continuous of navigation signal are broadcast.
Description
Technical field
The present invention relates to Satellite Navigation Technique, power ratio and carrier wave phase between particularly a kind of satellite navigation signals multi -components
Position relation method of adjustment.
Background technology
There are multiple component of signals inside single frequency point in satellite navigation signals, in satellite navigation signals generating process, will
Multiple component of signals synthesize complex signal orthogonal all the way by fixed permanent envelope look-up table, are then realized by orthogonal modulation
The generation of navigation signal, the method has the disadvantage that：
(1) multiple component of signals are complex as by signal all the way by fixed permanent envelope look-up tables'implementation, it is impossible to realize letter
The adjustment of power ratio and carrier phase relationship between number component；
(2) fixed permanent envelope look-up table is vulnerable to the influence of space single-particle inversion, and look-up table is navigation signal generation
In single-point, once look-up table is overturned by single-particle, then down navigation signal generation produces mistake, in causing navigation Service function
Disconnected, the problem can be solved by triplication redundancy, but critical registers be reinforced using three general mould methods for designing, nothing
Method realizes error correcting function, causes the in-orbit accumulation of single-particle inversion of permanent envelope look-up table, when the accumulation of a certain bit occurs two
During the single-particle inversion mistake of position, navigation signal generation produces mistake.
The content of the invention
Present invention solves the technical problem that being：Overcome the deficiencies in the prior art, there is provided between satellite navigation signals multi -components
Power ratio and carrier phase relationship method of adjustment, solve the power ratio and carrier phase that cannot be realized between component of signal
The adjustment of relation, when more than two single-particle inversion mistakes occurs in a certain bit accumulation, navigation signal generation produces asking for mistake
Topic, can be adjusted flexibly navigation signal multiple component of signals between power ratio and carrier phase relationship, with reliability it is high,
It is not easily susceptible to the advantage of single-particle inversion influence.
Technical solution of the invention is：Power ratio and carrier phase relationship are adjusted between satellite navigation signals multi -components
Method, comprises the following steps：
(1) permanent envelope look-up table is produced on ground；Described permanent envelope look-up table includes that satellite navigation signals institute is important
Between power ratio and carrier phase, can according to satellite navigation signals single frequency point exist multiple component of signals generation all the way
Orthogonal complex signal, and carry out orthogonal modulation and obtain navigation signal；
(2) will be noted on permanent envelope look-up table to navigation signal and generate load, control navigation signal generation load is using carrying
The triplication redundancy of feedback branch receives latch cicuit and receives and store permanent envelope look-up table, then inserts permanent envelope look-up table
FPGA inside Slice；It is the reception lock with feedback branch that the described triplication redundancy with feedback branch receives latch cicuit
The triplication redundancy design of circuit is deposited, it is superfluous that the mould court verdict of permanent envelope look-up table three is fed back to three moulds with feedback branch by realization
The remaining input for receiving latch cicuit, is carried out using the mould court verdict of permanent envelope look-up table three to input signal perseverance envelope look-up table
Correction；Described reception latch cicuit be by FPGA inside d type flip flop, LUT realize, realization permanent envelope look-up table is connect
Receive function；
(3) control navigation signal generation load generates navigation signal using permanent envelope look-up table；
(4) power ratio between need to change satellite navigation signals component and during carrier phase, produces new permanent envelope
Look-up table and above note to satellite-signal generate load, are then transferred to step (2).
The method of the described reception latch cicuit with feedback branch comprises the following steps：
(1) the reception all of trigger of latch cicuit is found out；
(2) the set critical point that will receive latch cicuit trigger is disconnected, and set port then is connected into low level；
(3) output signal of d type flip flop is connect the input port of LUT in FPGA, realizes that CPU is inserted；
(4) change the truth table of LUT, until when write FPGA control signal is effective and during correct address, LUT is output as
The signal that ground is inserted, when write FPGA control signal is invalid or during incorrect address, LUT is output as the electricity of input port 1
It is flat, then LUT output ports are connect the input port of d type flip flop.
The described triplication redundancy for having feedback branch receives latch cicuit and uses TMRTool instruments.
Present invention advantage compared with prior art is：
(1) present invention increases grouting socket by permanent envelope look-up table, is not interrupting the situation of satellite navigation signals
The content of look-up table is changed on lower permission ground by way of injecting order parameter, is solved ground control system and cannot be changed and leads
The problem of the permanent envelope look-up table of boat satellite, realizes the spirit of the power ratio and carrier phase relationship between multiple component of signals
Adjustment living；
(2) present invention carries out triplication redundancy design by the circuit with feedback branch, after solving single-particle inversion
Correction problem, when permanent envelope look-up table because can be corrected during single-particle inversion, single-particle inversion will not be accumulated, it is ensured that
The steady and continuous of navigation signal are broadcast.
Brief description of the drawings
Fig. 1 is power ratio and carrier phase relationship method of adjustment principle between a kind of satellite navigation signals multi -components of the invention
Flow chart；
Fig. 2 is that the FPGA of common perseverance envelope look-up table is received and storage circuit；
Fig. 3 is that the FPGA receptions of common perseverance envelope look-up table and the full triplication redundancy of storage circuit are designed；
Fig. 4 is the FPGA receptions of common perseverance envelope look-up table and the part triplication redundancy design of storage circuit；
Fig. 5 is that the FPGA of the permanent envelope look-up table with feedback branch is received and storage circuit；
Fig. 6 is FPGA receptions and the Quan Sanmo or the mould of part three of storage circuit of the permanent envelope look-up table with feedback branch
Redundancy Design circuit.
Specific embodiment
The present invention overcomes the deficiencies in the prior art, proposes power ratio and carrier wave phase between a kind of satellite navigation signals multi -components
Position relation method of adjustment, solves the adjustment that cannot realize power ratio and carrier phase relationship between component of signal, a certain
When more than two single-particle inversion mistakes occurs in bit accumulation, navigation signal generation produces the problem of mistake, can be adjusted flexibly
Navigation signal multiple component of signals between power ratio and carrier phase relationship, with reliability it is high, be not easily susceptible to single-particle
The advantage of influence is overturn, the inventive method is illustrated below in conjunction with the accompanying drawings.
It is as shown in Figure 1 power ratio between satellite navigation signals multi -components disclosed by the invention and carrier phase relationship adjustment
Method flow diagram, comprises the following steps：
(1) navigation signal generation load prestores a perseverance envelope look-up table, realizes that multiple component of signals of navigation signal are answered
With.Assuming that the number of component of signal is N in the inventive method, then the line number of permanent envelope look-up table is 2NOK, columns is 1 row；Often
The level of individual component of signal is+1 or -1, therefore each component of signal can use 1bit binary number representations；N number of component of signal can
Using N number of binary number representation；At a time, each component of signal is a certain stationary state (+1 or -1), N number of signal
The binary number that component is constituted is m=0~2NAny one number between -1, the m in number correspondence perseverance envelope look-up table
The content of the row of row the 1st.Permanent envelope look-up table is sharp with the power ratio and carrier phase relationship between component of signal as input condition
With mature technology, such as POCET algorithms, it is 2 to produce line numberNOK, columns is the form of 1 row.
(2) if terrestrial user needs the carrier phase relationship and power ratio of the multiple component of signals of change, generate new
Permanent envelope look-up table, and inject new permanent envelope look-up table to aeronautical satellite using ground control system；
(3) the new look-up table of navigation signal generation payload reception, inserts in FPGA in sequence.
(4) after FPGA receives permanent envelope look-up table, store in Slice inside FPGA, electricity of the design with feedback branch
Realize the reception and storage of permanent envelope look-up table in road.
(5) part triplication redundancy design is carried out to the above-mentioned circuit with feedback branch；Three moulds in the inventive method are superfluous
Remaining design process is realized using TMRTool instruments.
(6) by designing whether circuit check realizes that three mould court verdicts feed back to input, it is ensured that three mould court verdicts
Input signal is corrected, the correction of 1 bit single-particle inversion is realized.
(7) look-up table of ground injection replaces original look-up table, realizes navigation signal constant enveloped modulation.
The implementation method of the circuit with feedback branch in step (4), comprises the following steps：
(1) CPU in aeronautical satellite payload receives the permanent envelope look-up table of ground injection, then by the look-up table
Content is transmitted to FPGA；
(2) FPGA realizes being received from CPU the circuit of permanent envelope look-up table data；
(3) all of trigger in the partial circuit is found out；
(4) Fig. 2 show FPGA receptions and the storage circuit of common perseverance envelope look-up table, and the circuit can be realized receiving ground
The permanent envelope of injection searches table function, and full triplication redundancy design is carried out to the partial circuit, obtains circuit as shown in Figure 3, such as
The full triplication redundancy of FPGA receptions and storage circuit that Fig. 3 show common perseverance envelope look-up table is designed；The partial circuit is entered
The design of row part triplication redundancy, obtains circuit as shown in Figure 4, be illustrated in figure 4 common perseverance envelope look-up table FPGA receive and
The part triplication redundancy design of storage circuit；As can be seen that the triplication redundancy design shown in Fig. 3 and Fig. 4 is only to LUT look-up tables electricity
Road and D the device circuit that sets out have carried out triplication redundancy design, do not have feedback modifiers function, in the event of single-particle inversion, can lead
Cause mistake bit with the time accumulation.
(5) the set critical point of trigger is disconnected, set port is then connected into low level.
(6) output signal of d type flip flop is accessed the input port 1 of the LUT inside FPGA, is realized using backfeed loop
CPU inserts function, and the FPGA for being illustrated in figure 5 the permanent envelope look-up table with feedback branch is received and storage circuit.
(7) content of the truth table of modification LUT, implements function such as：
If CPU write enter FPGA control signal is effective and address correct, LUT is output as the signal that ground is inserted；Such as
The control signal that fruit CPU write enters FPGA is invalid or address is incorrect, then LUT is output as the level of input port 1.
(8) LUT outputs are accessed the input of d type flip flop.
The FPGA for being illustrated in figure 2 common perseverance envelope look-up table is received and storage circuit, complete three mould is carried out to the circuit superfluous
Remaining design, obtains circuit as shown in Figure 3, and part triplication redundancy design is carried out to the circuit, obtains circuit as shown in Figure 4.
Although Fig. 3, Fig. 4 have carried out triplication redundancy design, but due to no backfeed loop, it is impossible to the amendment of single-particle inversion is realized,
The FPGA for being illustrated in figure 6 the permanent envelope look-up table with feedback branch receives superfluous with the Quan Sanmo or the mould of part three of storage circuit
Remaining design circuit, Fig. 6 still suffers from backfeed loop due to there is backfeed loop after triplication redundancy, be capable of achieving repairing for single-particle inversion
Just.As can be seen that either full triplication redundancy is designed or part triplication redundancy method for designing, critical registers are added
Gu, error correcting function cannot be realized, cause the in-orbit accumulation of single-particle inversion of permanent envelope look-up table, when the accumulation of a certain bit
When there are two single-particle inversion mistakes, navigation signal generation produces mistake.
The FPGA for being illustrated in figure 5 the permanent envelope look-up table with feedback branch is received and storage circuit, and the circuit is entered
The full triplication redundancy of row or the design of part triplication redundancy, obtain circuit as shown in Figure 6.As can be seen that the circuit is by after triplication redundancy
Output result feedback return input, the single-particle inversion failure to input is corrected, it is ensured that single-particle inversion will not
With accumulated time.
The content not being described in detail in description of the invention belongs to the known technology of those skilled in the art.
Claims (3)
1. power ratio and carrier phase relationship method of adjustment between satellite navigation signals multi -components, it is characterised in that including following step
Suddenly：
(1) permanent envelope look-up table is produced on ground；Described permanent envelope look-up table include satellite navigation signals important
Power ratio and carrier phase, the multiple component of signals generation that can be existed according to satellite navigation signals single frequency point are orthogonal all the way
Complex signal, and carry out orthogonal modulation and obtain navigation signal；
(2) will be noted on permanent envelope look-up table to navigation signal and generate load, control navigation signal generation load is used with feedback
The triplication redundancy of branch road receives latch cicuit and receives and store permanent envelope look-up table, then inserts in FPGA permanent envelope look-up table
Portion Slice；It is the reception latch cicuit with feedback branch that the described triplication redundancy with feedback branch receives latch cicuit
Triplication redundancy design, realize that the mould court verdict of permanent envelope look-up table three is fed back into triplication redundancy with feedback branch receives
The input of latch cicuit, is corrected using the mould court verdict of permanent envelope look-up table three to input signal perseverance envelope look-up table；
Described reception latch cicuit be by FPGA inside d type flip flop, LUT realize, realize to the reception work(of permanent envelope look-up table
Energy；
(3) control navigation signal generation load generates navigation signal using permanent envelope look-up table；
(4) power ratio between need to change satellite navigation signals component and during carrier phase, produces new permanent envelope to search
Table and above note to satellite-signal generate load, are then transferred to step (2).
2. power ratio and carrier phase relationship method of adjustment between satellite navigation signals multi -components according to claim 1,
It is characterized in that：The method of the described reception latch cicuit with feedback branch comprises the following steps：
(1) the reception all of trigger of latch cicuit is found out；
(2) the set critical point that will receive latch cicuit trigger is disconnected, and set port then is connected into low level；
(3) output signal of d type flip flop is connect the input port of LUT in FPGA, realizes that CPU is inserted；
(4) change the truth table of LUT, until when write FPGA control signal is effective and during correct address, LUT is output as ground
The signal inserted, when write FPGA control signal is invalid or during incorrect address, LUT is output as the level of input port 1, so
LUT output ports are connect the input port of d type flip flop afterwards.
3. power ratio and carrier phase relationship adjustment side between satellite navigation signals multi -components according to claim 1 and 2
Method, it is characterised in that：The described triplication redundancy for having feedback branch receives latch cicuit and uses TMRTool instruments.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112684476A (en) * | 2020-11-23 | 2021-04-20 | 中国人民解放军国防科技大学 | Method for reducing false alarm rate of signal channel of navigation receiver and satellite-borne navigation receiver |
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| CN106772484B (en) | 2019-09-06 |
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