CN106549701B - A kind of retrievable satellite separation assembly time calibrating method - Google Patents
A kind of retrievable satellite separation assembly time calibrating method Download PDFInfo
- Publication number
- CN106549701B CN106549701B CN201610848240.6A CN201610848240A CN106549701B CN 106549701 B CN106549701 B CN 106549701B CN 201610848240 A CN201610848240 A CN 201610848240A CN 106549701 B CN106549701 B CN 106549701B
- Authority
- CN
- China
- Prior art keywords
- time
- ctu
- satellite
- rmu
- bus
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- 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
- H04B7/1851—Systems using a satellite or space-based relay
- H04B7/18519—Operations control, administration or maintenance
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04J—MULTIPLEX COMMUNICATION
- H04J3/00—Time-division multiplex systems
- H04J3/02—Details
- H04J3/06—Synchronising arrangements
- H04J3/0635—Clock or time synchronisation in a network
Landscapes
- Engineering & Computer Science (AREA)
- Computer Networks & Wireless Communication (AREA)
- Signal Processing (AREA)
- Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Physics & Mathematics (AREA)
- Electric Clocks (AREA)
- Position Fixing By Use Of Radio Waves (AREA)
Abstract
The invention discloses a kind of retrievable satellites to separate assembly time calibrating method, in-orbit section is calibrated satellite time reference using RMU calibration method, then periodically the CTU time is calibrated using the autonomous calibration method of RMU, finally the terminal of time is respectively used satellite to carry out time broadcast using CTU time broadcasting method, Satellite attitude track is realized accurately to control, return capsule is successfully separated safe retrieving, meets in-orbit section of the satellite high-precision use demand to the time；Rail section is stayed to calibrate using CTU calibration method to satellite time reference, then the terminal of time is respectively used satellite to carry out time broadcast using CTU time broadcasting method, successfully carry out the load test that satellite stays rail section, meets the normal use demand that satellite stays rail section to the time.
Description
Technical field
A kind of the invention belongs to retrievable satellite star the technical field of time synchronization, and in particular to retrievable satellite separation
Assembly time calibrating method.
Background technique
The retrievable satellite time includes time generation, time maintenance, time publication and time tranfer.The retrievable satellite time
System design is exactly to pass through ad hoc approach and necessary means to meet the needs of time user is to time precision and synchronization accuracy
Time on star is generated, maintenance and issue mechanism carry out corresponding system design.Retrievable satellite using serial data bus as
Time tranfer channel provides the transmission path of temporal information stream.
Since retrievable satellite is multi cabin structure, satellite is divided into two bay sections of instrument room and return capsule, wherein instrument room
Including service module and sealed compartment, return capsule includes recovery capsule and retro module.Retrievable satellite is with return capsule during in orbit
With the mode flight of instrument room assembly, return capsule independently returns to ground after a period of time in orbit, and instrument room continues
Stay rail section aerial mission.
The satellite in current China all uses single time system, and retrievable satellite includes two independent time systems:
1) " in-orbit section of assembly of return capsule and instrument room " time system；2) after the separation of two cabins, " instrument room stays rail section " time system.It returns
The operating mode for returning formula satellite different time system is also not exactly the same.Therefore, the time system of retrievable satellite how is designed,
And optimizing makes it complete different task in different phase, is the key point of retrievable satellite time system design.
Summary of the invention
In view of this, the present invention provides a kind of retrievable satellites to separate assembly time calibrating method, so that recoverable
Satellite completes different time tasks in different phase, and has taken into account the variation of satellite number pipe time reference, i.e., in-orbit section use
Recovery capsule administrative unit (Reentry Management Unit, the RMU) time stays rail section to use central processing unit
(Central Terminal Unit, CTU) time, demand when can satisfy the star of each time user of satellite.
Realize that technical scheme is as follows:
A kind of retrievable satellite separation assembly time calibrating method, comprising the following steps:
(1) time calibration of in-orbit section of assembly of return capsule and instrument room:
Step 11, the time difference Δ T1 of earth station's measurement satellite recovery capsule administrative unit RMU time and ground elapsed time；
Step 12, when the time difference Δ T1 of satellite RMU time and ground elapsed time be greater than or equal to setting threshold value when, earth station
It injects telecommand by uplink RMU is calibrated, amount is Δ T1 when school, is consistent the RMU time with ground elapsed time；
When the time difference Δ T1 of satellite RMU time and ground elapsed time are less than the threshold value of setting, earth station is injected by uplink
Telecommand is calibrated RMU using uniform calibration method, is consistent the RMU time with ground elapsed time；The uniform school
Shi Fangfa is periodically to calibrate to time difference Δ T1, and each period calibrates the time less than Δ T1 of a setting to Δ T1
Interval；
When step 13, satellite RMU independently carry out primary school to central processing unit CTU per minute, make CTU time and RMU
Time is consistent；
The CTU time is published to each bus using the method for broadcast by serial data bus by step 14, satellite CTU
Terminal device.
(2) instrument room stays the time calibration of rail section:
Step 21, the time difference Δ T2 of earth station's measurement satellite CTU time and ground elapsed time；
Step 22, when the time difference Δ T2 of satellite CTU time and ground elapsed time be greater than or equal to setting threshold value when, earth station
It injects telecommand by uplink CTU is calibrated, amount is Δ T2 when school, is consistent the CTU time with ground elapsed time；
When the time difference Δ T2 of satellite CTU time and ground elapsed time are less than the threshold value of setting, earth station is injected by uplink
Telecommand is calibrated CTU using uniform calibration method, is consistent the satellite RMU time with ground elapsed time；
The CTU time is published to each bus using the method for broadcast by serial data bus by step 23, satellite CTU
Terminal device.
Further, the time when RMU carries out initial power-on, software reset before the step 11 or cuts machine is extensive
Resurgent journey is as follows:
Step 1: RMU proposes the service request that the time restores on star to CTU；
Step 2: if CTU has responded the service request of RMU in 3 timeslices or in 3 timeslices, wherein when per
Between piece be 100 milliseconds, then RMU removes the service request immediately, and obtains time data, while clock synchronization from the corresponding subaddressing of bus
Between data data head and data tail verified；If check results are correct, the time data that will acquire are stored to the local RMU
Then memory block is taken out CTU timing code from time data, is verified to CTU timing code microsecond portion；If microsecond portion is being set
Determine in range, then time on RMU star is calibrated according to the timing code obtained；If microsecond portion exceeds zone of reasonableness, recognize
For CTU timing code format error, restore to fail when star, the RMU time starts from scratch timing；
If data head and data tail check results mistake to time data, show from CTU recovery time data failure,
The RMU time starts from scratch timing.
Step 3: RMU is terminated to be restored from CTU if the time is more than that 3 timeslice CTU do not respond the service request yet
Time data, RMU time start from scratch timing.
Further, the time when CTU carries out initial power-on, software reset before the step 11 or cuts machine is extensive
Resurgent journey is as follows:
Step 1: CTU is sent to attitude and orbit control computer AOCC for calculating the time difference by bus | tAOCC-
tCTU| CTU timing code；Wherein, tAOCCFor the satellite AOCC time at current time, tCTUFor the satellite CTU time at current time；
Step 2: after CTU is waited 1 second, it is poor from AOCC acquisition time by bus | tAOCC-tCTU|, CTU is by the time difference
Increase on the present satellites CTU time as the satellite CTU time after restoring；
Step 3: the operating process for restoring the satellite CTU time terminates if restoring the success of satellite CTU time from AOCC；
If failed from the AOCC recovery satellite CTU time, four-step 6 are thened follow the steps；
Step 4: CTU is sent to RMU for calculating the time difference by bus | tRMU-tCTU| CTU timing code；Wherein,
tRMUFor the satellite RMU time at current time；
Step 5: after CTU is waited 1 second, it is poor from RMU acquisition time by bus | tRMU-tCTU|, CTU increases the time difference
It is added on the present satellites CTU time as the satellite CTU time after restoring；
Step 6: the operating process for restoring the satellite CTU time terminates if restoring the success of satellite CTU time from RMU；
Fail if restoring the satellite CTU time from RMU, the satellite CTU time starts from scratch timing.
The utility model has the advantages that
(1) present invention firstly provides return satellite time reference construction scheme, in-orbit section using RMU as master clock source, CTU
It as secondary clock source, stays rail section using CTU as master clock source, provides required clock for the satellite different task stage
Source.
(2) present invention is for the first time according to the different phase for returning to satellite task, and using the star of different mode the time is same respectively
Step system；With solving the star between return combinations of satellites cabin time synchronization problem, time synchronization deviation, is effective with reducing star
Load star coordination accurate time reference is provided.
(3) satellite time reference is calibrated using RMU calibration method for in-orbit section, then uses the autonomous school when side RMU
Method periodically calibrates the CTU time, when finally respectively using satellite the terminal of time to carry out using CTU time broadcasting method
Between broadcast, realize Satellite attitude track and accurately control, return capsule is successfully separated safe retrieving, meets in-orbit section of satellite
To the high-precision use demand of time.
(4) it stays rail section to calibrate using CTU calibration method to satellite time reference, then uses CTU time broadcaster
Method respectively uses satellite the terminal of time to carry out time broadcast, has successfully carried out the load test that satellite stays rail section, has met and defend
Star stays rail section to the normal use demand of time.
(5) star in the present invention calibration method be that a kind of inexpensive, highly reliable, precision meets the requirements and stable
Method, meet requirement of the retrievable satellite separation assembly time system for time synchronization, there is good application value.
Detailed description of the invention
Fig. 1 is in-orbit section of assembly time system operating mode flow chart of return capsule of the present invention and instrument room.
Fig. 2 is that instrument room of the present invention stays rail section time system operating mode flow chart.
Specific embodiment
The present invention will now be described in detail with reference to the accompanying drawings and examples.
The present invention provides a kind of retrievable satellites to separate assembly time calibrating method, return capsule and in-orbit section of instrument room
Assembly time system introduction:
(1) time of RMU generates, and the time of CTU generates
The work clock that retrievable satellite generates several pipe crystal oscillators is as time source on star, including when CTU time and RMU
Between.Retrievable satellite all can serve as time source on star from section in orbit, the work clock of number pipe CTU and RMU is emitted to, but
Since RMU crystal oscillator stability is better than CTU, section uses RMU internal clocking as whole star time reference in orbit, and when star is steady
Fixed degree is ± 5 × 10-6Second/day, daily maximum deviation are ± 0.432 second.Retrievable satellite stays rail target phase, due to RMU
With landing of return capsule ground, therefore satellite stays rail section that number pipe CTU internal clocking can only be used as whole star time reference, and when star is steady
Fixed degree is ± 1 × 10-5Second/day, daily maximum deviation are ± 0.864 second.
(2) RMU time initial value and time restore
As RMU initial power-on, software reset or when cutting machine, by bus from CTU recovery time data.Specific steps are such as
Under:
1), RMU from CTU recovery time data when need to propose service request.
2), if CTU has responded the service request of RMU in 3 timeslices or in 3 timeslices, i.e. RMU is in the bus
Detect that receiving RMU time data pointer resets synchronization character in disconnected, wherein every timeslice is 100 milliseconds, then RMU is removed immediately
The service request, and time data are obtained from the corresponding subaddressing of bus, while data head and the progress of data tail to time data
Verification；If check results are correct, the time data that will acquire are stored to RMU local storage, then take from time data
CTU timing code out verifies CTU timing code microsecond portion；If microsecond portion is within the set range, according to the time obtained
Code calibrates the time on RMU star；If microsecond portion exceeds zone of reasonableness, then it is assumed that CTU timing code format error restores star
When fail；The RMU time starts from scratch timing；
If data head and data tail check results mistake to time data, show from CTU recovery time data failure,
The RMU time starts from scratch timing.
Step 3: RMU is terminated to be restored from CTU if the time is more than that 3 timeslice CTU do not respond the service request yet
Time data show from CTU recovery time data failure, and the RMU time starts from scratch timing.
(3) CTU time initial value and time restore
It is extensive from orbits controlling computer AOCC and RMU by bus as CTU initial power-on, software reset or when cutting machine
Multiple time data.Specific step is as follows:
1) CTU is sent to attitude and orbit control computer AOCC for calculating the time difference by bus | tAOCC-tCTU|
CTU timing code；Wherein, tAOCCFor the satellite AOCC time at current time, tCTUFor the satellite CTU time at current time；
2) poor from AOCC acquisition time by bus after CTU is waited 1 second | tAOCC-tCTU|, CTU increases to the time difference
As the satellite CTU time after restoring on the present satellites CTU time.
If 3) restore the success of satellite CTU time from AOCC, this restores the operating process knot of satellite CTU time
Beam；If failed from the AOCC recovery satellite CTU time, go to step 4), continues to restore the satellite CTU time from RMU.
4) CTU is sent to RMU for calculating the time difference by bus | tRMU-tCTU| CTU timing code, wherein tRMUTo work as
The satellite RMU time at preceding moment；
5) poor from RMU acquisition time by bus after CTU is waited 1 second | tRMU-tCTU|, CTU, which increases to the time difference, to be worked as
As the satellite CTU time after restoring on the preceding satellite CTU time.
If 6) restore the success of satellite CTU time from RMU, this operating process for restoring the satellite CTU time terminates；
Fail if restoring the satellite CTU time from RMU, the time restores to fail on star, then the satellite CTU time starts from scratch timing.
After RMU and CTU normally powers on recovery time data, the assembly time is separated using a kind of retrievable satellite of the present invention
Calibration method is calibrated, as depicted in figs. 1 and 2, comprising the following steps:
(1) time calibration of in-orbit section of assembly of return capsule and instrument room:
Step 1: the time difference Δ T1 of earth station's measurement satellite RMU time and ground elapsed time；
Step 2: earth station is logical after the time difference Δ T1 of satellite RMU time and ground elapsed time are more than or equal to the threshold value of setting
It crosses uplink injection telecommand RMU is calibrated, amount is Δ T1 when school, is consistent the RMU time with ground elapsed time；
After the time difference Δ T1 of satellite RMU time and ground elapsed time are less than the threshold value of setting, earth station is injected by uplink
Telecommand is calibrated RMU using uniform calibration method, is consistent the RMU time with ground elapsed time；The uniform school
Shi Fangfa is periodically to calibrate to time difference Δ T1, and each period calibrates the time less than Δ T1 of a setting to Δ T1
Interval；
When RMU collection lieutenant colonel and when uniform school
When there are star the time difference, retrievable satellite when collecting lieutenant colonel, when uniform school by the way of carry out time dimension on star
Shield.I.e. by requirement is instructed when the school of ground, on the basis of the time on the current star of satellite, the time on star is increased and decreased into a requirement
Value, with the absolute error of with correcting star time.
When RMU collection lieutenant colonel: section can pass through retrievable satellite when star time difference absolute value is Δ T1 seconds in orbit
On ground note instruction to RMU collection lieutenant colonel when carry out time difference amendment, amount is Δ T1 when school, when realizing RMU time and ground UTC on star
Between synchronization, random error is microsecond (us) magnitude when integrating lieutenant colonel.Collection lieutenant colonel is being carried out constantly in poor makeover process, it is also contemplated that
Satellite-ground link time delay.
When the uniform school RMU: when star the time difference leads to periodically occur T1 milliseconds of aggregate-value Δ due to the offset of RMU time crystal oscillator
When, and Δ T1 is less than the threshold value of setting, and accumulative time difference amendment is carried out when can instruct school uniform to RMU by infusing on ground.RMU
At a certain time interval, T3 milliseconds of minimum interval Δ periodically is increased or decreased to the RMU time, reaches and mentions
The accurate timing purpose of time cumulation on high star.
Step 3: being consistent the CTU time with the RMU time when satellite RMU independently carries out primary school to CTU per minute；
The time of retrievable satellite is managed collectively by several pipe CTU.Satellite section in orbit, devises the autonomous school RMU
Shi Fangfa, when realizing periodical school of the RMU to CTU.Realize that the CTU time is synchronous with the RMU time on star when the autonomous school RMU.Tool
Body step are as follows:
1) CTU sends the newest timing code of CTU by bus cycles property (1 minute 1 time) to RMU.
2) whether effective RMU detects bus interruption, if it is valid, obtaining CTU timing code in processing of breaking in the bus, together
When get current RMU timing code.
3) RMU completes the time difference of RMU and CTU in 1 second | tRMU-tCTU| it calculates, and CTU is sent to by bus.
4) CTU waits 1 second after ± 125 milliseconds, obtains the time difference of RMU and CTU from RMU by bus | tRMU-tCTU|, it will
Time difference and CTU time do add operation, and operation result is as the new CTU time.After when the autonomous school RMU of the every completion of CTU,
CTU time and RMU time difference absolute value can be guaranteed less than 1 millisecond.
Step 4: the CTU time is published to each bus using the method for broadcast by serial data bus by satellite CTU
Terminal device.
In such a way that CTU is broadcasted, realize that each subsystem is synchronous with the CTU time.Timing code is sent bus by CTU
Software time delay and bus transfer time delay compensate；Time user carries out time benefit to the software time delay after getting timing code
It repays.CTU is broadcasted the CTU time by bus to remote terminal equipment, once per second, A/B bus alternating.When broadcasting the CTU time,
All interruptions are closed, the software time delay that CTU is sent to bus to timing code compensates (us), therefore when can guarantee CTU
Between the error broadcasted be us grades.
(2) instrument room stays the time calibration of rail section:
Step 1: the time difference Δ T2 of earth station's measurement satellite CTU time and ground elapsed time；
Step 2: earth station is logical after the time difference Δ T2 of satellite CTU time and ground elapsed time are more than or equal to the threshold value of setting
It crosses uplink injection telecommand CTU is calibrated, amount is Δ T2 when school, is consistent the CTU time with ground elapsed time；
After the time difference Δ T2 of satellite CTU time and ground elapsed time are less than the threshold value of setting, earth station is injected by uplink
Telecommand is calibrated CTU using uniform calibration method, is consistent the satellite RMU time with ground elapsed time；
When CTU collection lieutenant colonel and when uniform school
When there are star the time difference, retrievable satellite is using two ways carries out the time on star when collecting lieutenant colonel, when uniform school
Maintenance.I.e. by requirement is instructed when the school of ground, on the basis of the time on the current star of satellite, the time on star is increased and decreased into a requirement
Value, with the absolute error of with correcting star time.
When CTU collection lieutenant colonel: retrievable satellite stays rail target phase, when star time difference absolute value is Δ T2 seconds, can pass through
On ground note instruction to CTU collection lieutenant colonel when carry out time difference amendment, amount is Δ T2 when school, when realizing CTU time and ground UTC on star
Between synchronization, random error is microsecond (us) magnitude when integrating lieutenant colonel.In carrying out time difference makeover process, it is also contemplated that satellite-ground link
Time delay.
When the uniform school CTU: when star the time difference leads to periodically occur T2 milliseconds of aggregate-value Δ due to the offset of CTU time crystal oscillator
When, accumulative time difference amendment is carried out when can instruct school uniform to CTU by infusing on ground.CTU is at a certain time interval, all
T4 milliseconds of minimum interval Δ is increased or decreased to phase property to the CTU time, reaches time cumulation on raising star and accurately counts
When purpose.
Step 3: the CTU time is published to each bus using the method for broadcast by serial data bus by satellite CTU
Terminal device.
In such a way that CTU is broadcasted, realize that each subsystem is synchronous with the CTU time.Timing code is sent bus by CTU
Software time delay and bus transfer time delay compensate；Time user carries out time benefit to the software time delay after getting timing code
It repays.CTU is broadcasted the CTU time by bus to remote terminal equipment, once per second, A/B bus alternating.When broadcasting the CTU time,
All interruptions are closed, the software time delay that CTU is sent to bus to timing code compensates (us), therefore when can guarantee CTU
Between the error broadcasted be us grades.
In conclusion the above is merely preferred embodiments of the present invention, being not intended to limit the scope of the present invention.
All within the spirits and principles of the present invention, any modification, equivalent replacement, improvement and so on should be included in of the invention
Within protection scope.
Claims (3)
1. a kind of retrievable satellite separates assembly time calibrating method, which comprises the following steps:
(1) time calibration of in-orbit section of assembly of return capsule and instrument room:
Step 11, the time difference Δ T1 of earth station's measurement satellite recovery capsule administrative unit RMU time and ground elapsed time；
Step 12, when the time difference Δ T1 of satellite RMU time and ground elapsed time be greater than or equal to setting threshold value when, earth station passes through
RMU is calibrated in uplink injection telecommand, and amount is Δ T1 when school, is consistent the RMU time with ground elapsed time；
When the time difference Δ T1 of satellite RMU time and ground elapsed time are less than the threshold value of setting, earth station is injected by uplink to be remotely controlled
Instruction, is calibrated RMU using uniform calibration method, is consistent the RMU time with ground elapsed time；The uniform school when side
Method is periodically to calibrate to time difference Δ T1, the time less than Δ T1 that each period calibrates a setting to Δ T1
Every；
When step 13, satellite RMU independently carry out primary school to central processing unit CTU per minute, make CTU time and RMU time
It is consistent；
The CTU time is published to each bus termination using the method for broadcast by serial data bus by step 14, satellite CTU
Equipment；
(2) instrument room stays the time calibration of rail section:
Step 21, the time difference Δ T2 of earth station's measurement satellite CTU time and ground elapsed time；
Step 22, when the time difference Δ T2 of satellite CTU time and ground elapsed time be greater than or equal to setting threshold value when, earth station passes through
CTU is calibrated in uplink injection telecommand, and amount is Δ T2 when school, is consistent the CTU time with ground elapsed time；
When the time difference Δ T2 of satellite CTU time and ground elapsed time are less than the threshold value of setting, earth station is injected by uplink to be remotely controlled
Instruction, is calibrated CTU using uniform calibration method, is consistent the satellite RMU time with ground elapsed time；The uniform school
When specifically: CTU at a certain time interval, periodically increases or decreases a minimum interval Δ to the CTU time
T4 milliseconds；
The CTU time is published to each bus termination using the method for broadcast by serial data bus by step 23, satellite CTU
Equipment.
2. a kind of retrievable satellite as described in claim 1 separates assembly time calibrating method, which is characterized in that described
It is as follows that time when RMU carries out initial power-on, software reset before the step 11 or cuts machine restores process:
Step 1: RMU proposes the service request that the time restores on star to CTU；
Step 2: if CTU has responded the service request of RMU in 3 timeslices or in 3 timeslices, wherein every timeslice
It is 100 milliseconds, then RMU removes the service request immediately, and obtains time data from the corresponding subaddressing of bus, while to time number
According to data head and data tail verified；If check results are correct, the time data that will acquire are stored to RMU and are locally stored
Then area takes out CTU timing code from time data, verifies to CTU timing code microsecond portion；If microsecond portion is in setting model
In enclosing, then time on RMU star is calibrated according to the timing code obtained；If microsecond portion exceeds zone of reasonableness, then it is assumed that CTU
Timing code format error restores to fail when star, and the RMU time starts from scratch timing；
If data head and data tail check results mistake to time data, show from CTU recovery time data failure, RMU
Time starts from scratch timing；
Step 3: RMU was terminated from CTU recovery time if the time is more than that 3 timeslice CTU do not respond the service request yet
Data, RMU time start from scratch timing.
3. a kind of retrievable satellite as described in claim 1 separates assembly time calibrating method, which is characterized in that described
It is as follows that time when CTU carries out initial power-on, software reset before the step 11 or cuts machine restores process:
Step 1: CTU is sent to attitude and orbit control computer AOCC for calculating the time difference by bus | tAOCC-tCTU|
CTU timing code；Wherein, tAOCCFor the satellite AOCC time at current time, tCTUFor the satellite CTU time at current time；
Step 2: after CTU is waited 1 second, it is poor from AOCC acquisition time by bus | tAOCC-tCTU|, CTU increases to the time difference
As the satellite CTU time after restoring on the present satellites CTU time；
Step 3: the operating process for restoring the satellite CTU time terminates if restoring the success of satellite CTU time from AOCC；If
Fail from the AOCC recovery satellite CTU time, thens follow the steps four-step 6；
Step 4: CTU is sent to RMU for calculating the time difference by bus | tRMU-tCTU| CTU timing code；Wherein, tRMUFor
The satellite RMU time at current time；
Step 5: after CTU is waited 1 second, it is poor from RMU acquisition time by bus | tRMU-tCTU|, CTU increases to the time difference
As the satellite CTU time after restoring on the present satellites CTU time；
Step 6: the operating process for restoring the satellite CTU time terminates if restoring the success of satellite CTU time from RMU；If
Restore the satellite CTU time from RMU to fail, then the satellite CTU time starts from scratch timing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610848240.6A CN106549701B (en) | 2016-09-23 | 2016-09-23 | A kind of retrievable satellite separation assembly time calibrating method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610848240.6A CN106549701B (en) | 2016-09-23 | 2016-09-23 | A kind of retrievable satellite separation assembly time calibrating method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106549701A CN106549701A (en) | 2017-03-29 |
| CN106549701B true CN106549701B (en) | 2019-05-17 |
Family
ID=58368165
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610848240.6A Active CN106549701B (en) | 2016-09-23 | 2016-09-23 | A kind of retrievable satellite separation assembly time calibrating method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106549701B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111880204B (en) * | 2020-06-28 | 2023-03-24 | 北京空间飞行器总体设计部 | Hierarchical time frequency system for navigation satellite |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102291169A (en) * | 2011-09-09 | 2011-12-21 | 航天东方红卫星有限公司 | Onboard high-accuracy time synchronization method for satellite |
| CN102882586B (en) * | 2012-10-15 | 2014-11-19 | 北京空间飞行器总体设计部 | Satellite time synchronization system |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2000131474A (en) * | 1998-10-27 | 2000-05-12 | Fujitsu Ltd | Time synchronization system, satellite system and ground system applied thereto, time synchronization method and medium with recorded program for execution of method on computer |
-
2016
- 2016-09-23 CN CN201610848240.6A patent/CN106549701B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102291169A (en) * | 2011-09-09 | 2011-12-21 | 航天东方红卫星有限公司 | Onboard high-accuracy time synchronization method for satellite |
| CN102882586B (en) * | 2012-10-15 | 2014-11-19 | 北京空间飞行器总体设计部 | Satellite time synchronization system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106549701A (en) | 2017-03-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US12099126B2 (en) | Navigation satellite time system and its autonomous recovery method | |
| RU2608763C2 (en) | Advanced timing and time transfer for satellite constellations using crosslink ranging and accurate time source | |
| CN101615964B (en) | For circuit arrangement and the method for synchronised clock in a network | |
| CN102291169B (en) | Onboard high-accuracy time synchronization method for satellite | |
| Tarabini et al. | Ground guided CX-OLEV rendez-vous with uncooperative geostationary satellite | |
| KR101651647B1 (en) | Time synchronization method between satellite and ground equipment, and satellite system thereof | |
| EP2895882A1 (en) | Maintaining integrity against erroneous ephemeris | |
| CN103675804A (en) | Inter-satellite ranging method based on dual-satellite time synchronization | |
| US6182927B1 (en) | Medium earth orbit augmentation of a global positioning system for global navigation | |
| CN105577309A (en) | Whole-network clock synchronization method of satellite communication system | |
| CN106549701B (en) | A kind of retrievable satellite separation assembly time calibrating method | |
| CN113341685A (en) | Satellite time management method, electronic device and medium | |
| CN108540207B (en) | Satellite load distributed time synchronization method and system | |
| CN112817022B (en) | Low-orbit satellite time-frequency synchronization method, system, electronic equipment and storage medium | |
| Antreasian et al. | The design and navigation of the near Shoemaker landing on Eros | |
| CN110109155B (en) | Bidirectional time correction method without application software interruption on satellite | |
| Anderson et al. | Low earth orbit navigation system (leons): Scalable gnss-independent time transfer and positioning for space users | |
| Anzalone et al. | Ground-testing of One-way Ranging from a Lunar Beacon Demonstrator Payload (Lunar Node-1) | |
| CN118921732A (en) | Method and system for realizing time synchronization of networking satellites | |
| NL2026210B1 (en) | Timescale dissemination using global navigation satellite systems and applications thereof | |
| KR20230063166A (en) | System and method for positioning using low earth orbit satellite | |
| RU2767605C1 (en) | Small-sized radio station for transmitting control commands of an unmanned aerial vehicle | |
| Succa et al. | IXV avionics architecture: Design, qualification and mission results | |
| CN111880204B (en) | Hierarchical time frequency system for navigation satellite | |
| Karutin et al. | 4.1 GLONASS Overview |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |