CN105068415A - satellite-ground timing method for observation station without condition for compatibility test between ground station and satellite - Google Patents
satellite-ground timing method for observation station without condition for compatibility test between ground station and satellite Download PDFInfo
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- CN105068415A CN105068415A CN201410857541.6A CN201410857541A CN105068415A CN 105068415 A CN105068415 A CN 105068415A CN 201410857541 A CN201410857541 A CN 201410857541A CN 105068415 A CN105068415 A CN 105068415A
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Abstract
The present invention provides a satellite-ground timing method for observation stations without any conditions for compatibility tests between ground stations and satellites. By utilizing common-view segmental arcs among observation stations, satellite-ground equipment fixed delays of observation stations without any conditions for carrying out compatibility tests are reckoned through satellite-ground equipment fixed delay of an observation station with conditions for carrying out the compatibility test, and a satellite-ground timing amount is further obtained, thus to realize a satellite-ground timing function of observation stations without compatibility tests. With adoption of the above method, the satellite-ground timing function of the observation stations on the ground is not restrained by geographic positions or task time any more; and when conditions for carrying out the compatibility tests between ground stations and satellites do not exist, the observation stations on the ground still have the timing function, thereby effectively guarantee smooth development of test and control tasks; and a satellite test and control subsystem correction sample does not need to be sent to each observation station for the compatibility test, thereby bringing convenience for smooth implementation of spaceflight test control tasks.
Description
Technical field
The invention belongs to spationautics field, be specifically related to spacecraft observation and control technology field.
Background technology
In spacecraft measurement and control area, for ensureing degree of accuracy and the accuracy of Satellite Orbit Maneuver correction, need to guarantee star ground time consistency, the star ground time difference requires to remain in 5ms, namely on star, the difference of time and ground elapsed time controls within the scope of 5ms, in particular cases then needs to control within the scope of 1ms.Usually, the calculating that Satellite Orbit Maneuver controls correction is generated by ground-based mission center, by ground survey station, the process data at task center is injected on satellite subsequently, if the world time difference does not control in above-mentioned scope in the process, then time reference is inconsistent with controlling the star of correction for Satellite Orbit Maneuver, greatly will affect the precision of rail control.By ground survey station to guaranteeing star ground time consistency during satellite school, be the effective measures promoting satellite rail control quality, with therefore must possessing star during ground survey station task function during school, just can guarantee that the world time difference controls in the threshold value of task restriction.
At present, dock with carrying out star test be survey station with carrying out star school time prerequisite.Because the docking test of ground survey station star ground is the unique channel obtaining star ground equipment fixed delay, and star ground equipment fixed delay and star ground distance decide the star ground time difference of satellite and ground survey station, during for realizing the accurate school to satellite, now positive for Satellite TT subsystem exemplar must be transported to survey station and carry out docking test, star ground equipment fixed delay value could be obtained.Ability when other survey stations are to possess school, then need positive for Satellite TT subsystem exemplar to be transported to each survey station and carry out docking test and could realize.If this ground survey station does not carry out docking test, or this ground survey station remoteness also or far away from external is inconvenient to carry out docking test, then this survey station can not obtain star ground equipment fixed delay and then can not complete.If this survey station remoteness is also or far away from abroad, then Transporting equipment carries out process and the formality redundant and complicated of docking test, in this process, the input of time and goods and materials cost is huge, be unfavorable for very much the cost savings of space flight measurement and control task, simultaneously also complete what affect task the realization as scheduled that time limit is unfavorable for TT&C task.
Summary of the invention
The object of the invention is to solve ground survey station and dock test with unconditionally carrying out star, cannot obtain star ground equipment fixed delay with completing survey station star school time problem.There is provided a kind of without star with docking test survey station star school time method, to meet demand during dock the ground survey station star of test with unconditionally carrying out star school.In order to achieve the above object, the technical solution used in the present invention comprises the steps: as follows
Step one, look in segmental arc altogether at survey station A and B, obtain star ground time difference of survey station A by formula (1) and school time
ΔT
A＝T
cz-(T
0+T
wx)-Δt
A-Δt
AR(1)
Step 2, look in segmental arc altogether at survey station A and B, calculated the star ground equipment fixed delay of survey station B by formula (2)
Δt
B＝T
cz-(T
0+T
wx)-ΔT
A-Δt
BR(2)
Step 3, to follow the tracks of in segmental arc at survey station B, obtain the B survey station star ground time difference by formula (3) and school time
ΔT
B＝T
cz-(T
0+T
wx)-Δt
B-Δt
BR(3)
Step 4, look altogether in segmental arc at survey station B and C, circulation step two, three obtains C survey station star ground equipment fixed delay Δ t respectively
cwith star ground time difference Δ T
cand during school;
Step 5, other acquisition without the star ground docking test survey station star ground time difference are with step 2 to four;
Wherein: A is for there being docking test survey station, and B, C are without docking test survey station, have and look segmental arc altogether between survey station A and B and B and C; Δ T
afor the A survey station star ground time difference; T
czfor the ground survey station time; T
0for time initial time on star; T
wxfor the time on telemetry frame culminant star, relative to initial time timing on star, T
0+ T
wxconstitute the time on star; Δ t
afor A survey station star ground equipment fixed delay, be as the criterion with the data that observing and controlling positive sample docking in the world obtains; Δ t
aRfor A survey station is to the space propagation time delay of satellite, obtained by task center calculation; Δ t
bfor B survey station star ground equipment fixed delay; Δ t
bRfor B survey station is to the space propagation time delay of satellite; Δ T
bfor the B survey station star ground time difference.
The advantage that the present invention has and good effect are:
1, the present invention can when only carrying out a survey station star ground observing and controlling docking, utilize in task have with this survey station altogether depending on segmental arc other survey station with carrying out star school time, and this can be extrapolated to other survey stations, so information when information infers that other do not carry out docking the school of testing survey station when can be convenient to carry out the survey station school of docking test by one, function when making the survey station into ground docking test also can possess school, greatly enhances dirigibility during survey station school.
2, realization of the present invention, during survey station school, ground, ability will no longer limit by geographic position or retrain task time, will not be transported to each survey station and carry out docking and test by the positive exemplar of Satellite TT subsystem simultaneously, while cost-saving, facilitate the normal enforcement of TT&C task.
Embodiment
At present, local and overseas Chinese survey stations reaches dozens of, all exists look segmental arc altogether in a large number to all kinds of low rail, middle high rail and lunar exploration satellite, and the duration much looking segmental arc altogether even reaches a few hours more than.What is called looks segmental arc altogether, refers to that survey station A and survey station B can carry out observing and controlling to certain satellite in section sometime simultaneously, then this time period is called as and looks segmental arc altogether between survey station A and survey station B.The present invention utilizes the characteristic of looking segmental arc altogether, by there being the survey station star ground equipment fixed delay of docking test condition with calculating other survey station stars without docking test condition equipment fixed delay, measures, with realizing survey station star function during school when obtaining school, star ground further.
Be located in the positive sample docking of world observing and controlling, only carry out star ground equipment fixed delay to A survey station to measure, if A, B survey station has look segmental arc altogether, measure when distance obtains A survey station school with then can utilizing A survey station star ground equipment fixed delay and star, B survey station star ground equipment fixed delay is released again by B survey station star ground distance is anti-, calculate the star ground time difference further, thus can be calibrated with B survey station.
If B survey station and C survey station have look segmental arc altogether, then measure when the method can be utilized to extrapolate star ground equipment fixed delay and the school of C survey station.Measure when can extrapolate star ground equipment fixed delay and the school had between two altogether depending on the survey station of segmental arc by that analogy, thus complete without docking test survey station star school time ability realization, ensure the smooth enforcement of space flight measurement and control task.
Reenter for moon exploration program three phase below and return flight test mission.In the docking of world observing and controlling positive sample, only measure survey station star ground, Qingdao equipment fixed delay, during the school at station, Qingdao, will be used for guaranteeing that service module to be separated moment returner and to navigate the time reference of initial value with returner.But, be separated to cabin device after during school, station, Qingdao and need through several hours, because service module clock drift amount is comparatively large, therefore cannot ensure correcting delay precision.Before cabin device is separated, Namibia station need be utilized to be calibrated, but detector development time progress, Engineering Overall funds and handling of procedure for going abroad all cannot ensure to carry out docking at Namibia station.In the face of complicated case, utilize Namibia stand with station, Keshen look segmental arc altogether, the difficult problem with solving multistation star during school altogether depending on segmental arc and station, Keshen and station, Qingdao.Concrete grammar is as follows:
Step one: the star ground time difference obtaining docking test A survey station (Qingdao)
Look altogether in segmental arc at A survey station (Qingdao) and B survey station (Keshen), utilize formula (1) to calculate the star ground time difference Δ T at A station
a;
ΔT
A＝T
cz-(T
0+T
wx)-Δt
A-Δt
AR(1)
In formula:
● Δ T
afor the star ground time difference, that is measure during school, as Δ T
aduring > 0, set clock on star ahead, as Δ T
aduring < 0, set clock on star back;
● T
czfor the ground survey station time;
● T
0for time initial time on star;
● T
wxfor the time on telemetry frame culminant star, relative to initial time timing on star, T
0+ T
wxconstitute the time on star;
● Δ t
afor A survey station star ground equipment fixed delay, be as the criterion with the data that observing and controlling positive sample docking in the world obtains;
● Δ t
aRfor A survey station is to the space propagation time delay of satellite, obtained by task center calculation.
Step 2: obtain B survey station (Keshen) star ground equipment fixed delay
Look altogether in segmental arc at A survey station and B survey station, utilize formula Δ T
a=T
cz-(T
0+ T
wx)-Δ t
b-Δ t
bRextrapolate B survey station star ground equipment fixed delay Δ t
b, Δ t
b==T
cz-(T
0+ T
wx)-Δ T
a-Δ t
bR, Δ t in formula
bRfor B survey station is to the space propagation time delay of satellite.
Step 3: the star ground time difference obtaining B survey station (Keshen)
Follow the tracks of in segmental arc at B survey station, utilize formula (2) to calculate B survey station star ground time difference Δ T
b
ΔT
B＝T
cz-(T
0+T
wx)-Δt
B-Δt
BR(2)
And be calibrated.
Step 4: the star ground time difference obtaining C survey station (Namibia)
B survey station (Keshen) and C survey station (Namibia) have looks segmental arc altogether, then circulation step two, three can obtain C survey station star ground equipment fixed delay Δ t respectively
cwith C survey station star ground time difference Δ T
c.
Step 5: by that analogy, other acquisition without the star ground docking test survey station star ground time difference with step 2 to four, can make other multiple without docking survey station with possessing star school time function.
Method during a kind of school, survey station star ground without docking test provided by the invention, good by the above-mentioned test effect putting into practice task, the difficult problem with solving multistation star during school, with improve survey station star quality during school.The present invention makes full use of the characteristic of looking segmental arc between two survey stations altogether, for do not carry out docking test survey station with realizing star school time provide new method.
Claims (1)
1., without method during docking test survey station star school, ground, star ground, it is characterized in that following steps:
Step one: look in segmental arc altogether at survey station A and B, obtain star ground time difference of survey station A by formula (1) and school time
ΔT
A＝T
cz-(T
0+T
wx)-Δt
A-Δt
AR(1)
Step 2: look in segmental arc altogether at survey station A and B, is calculated the star ground equipment fixed delay of survey station B by formula (2)
Δt
B＝T
cz-(T
0+T
wx)-ΔT
A-Δt
BR(2)
Step 3: follow the tracks of in segmental arc at survey station B, obtain the B survey station star ground time difference by formula (3) and school time
ΔT
B＝T
cz-(T
0+T
wx)-Δt
B-Δt
BR(3)
Step 4: look altogether in segmental arc at survey station B and C, circulation step two, three obtains C survey station star ground equipment fixed delay Δ t respectively
cwith star ground time difference Δ T
cand during school;
Step 5: other acquisition without the star ground docking test survey station star ground time difference is with step 2 to four;
Wherein: A is for there being docking test survey station, and B, C are without docking test survey station, have and look segmental arc altogether between survey station A and B and B and C; Δ T
afor the A survey station star ground time difference; T
czfor the ground survey station time; T
0for time initial time on star; T
wxfor the time on telemetry frame culminant star, relative to initial time timing on star, T
0+ T
wxconstitute the time on star; Δ t
afor A survey station star ground equipment fixed delay, be as the criterion with the data that observing and controlling positive sample docking in the world obtains; Δ t
aRfor A survey station is to the space propagation time delay of satellite, obtained by task center calculation; Δ t
bfor B survey station star ground equipment fixed delay; Δ t
bRfor B survey station is to the space propagation time delay of satellite; Δ T
bfor the B survey station star ground time difference.
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|---|---|---|---|
| CN201410857541.6A CN105068415B (en) | 2014-12-31 | 2014-12-31 | Method during with testing survey station star school is docked without star |
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|---|---|---|---|
| CN201410857541.6A CN105068415B (en) | 2014-12-31 | 2014-12-31 | Method during with testing survey station star school is docked without star |
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| CN105068415B CN105068415B (en) | 2017-11-03 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114943061A (en) * | 2022-06-28 | 2022-08-26 | 北京航天驭星科技有限公司 | Satellite time difference data processing method and system, electronic device and medium |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4897661A (en) * | 1987-04-10 | 1990-01-30 | Sony Corporation | Method and apparatus for determining the position of a vehicle |
| US20030208317A1 (en) * | 1998-12-10 | 2003-11-06 | Hughes Electronics Corporation | Position location of multiple transponding platforms and users using two-way ranging as a calibration reference for GPS |
| CN201110949Y (en) * | 2007-10-12 | 2008-09-03 | 丁志军 | Self-checking satellite synchronous standard clock |
| CN101383653A (en) * | 2008-10-30 | 2009-03-11 | 航天东方红卫星有限公司 | Automatic time synchronizing method on satellite |
| CN201294513Y (en) * | 2008-09-26 | 2009-08-19 | 华东电网有限公司 | System for synchronizing whole network time based on satellite common vision |
| CN102012671A (en) * | 2009-09-08 | 2011-04-13 | 上海卫星工程研究所 | Simple multimode high-stability satellite clock device |
| CN102118847A (en) * | 2009-12-31 | 2011-07-06 | 北京控制工程研究所 | Satellite clock and ground clock unifying method and device for ground test |
| CN102566408A (en) * | 2010-12-10 | 2012-07-11 | 上海卫星工程研究所 | Calibration system for satellite clock and calibration method thereof |
| CN102981402A (en) * | 2012-11-20 | 2013-03-20 | 北京控制工程研究所 | Method for calibrating satellite-to-ground time |
| CN103197535A (en) * | 2013-04-12 | 2013-07-10 | 北京空间飞行器总体设计部 | Method for satellite-ground timing with oscilloscope |
-
2014
- 2014-12-31 CN CN201410857541.6A patent/CN105068415B/en not_active Expired - Fee Related
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4897661A (en) * | 1987-04-10 | 1990-01-30 | Sony Corporation | Method and apparatus for determining the position of a vehicle |
| US20030208317A1 (en) * | 1998-12-10 | 2003-11-06 | Hughes Electronics Corporation | Position location of multiple transponding platforms and users using two-way ranging as a calibration reference for GPS |
| CN201110949Y (en) * | 2007-10-12 | 2008-09-03 | 丁志军 | Self-checking satellite synchronous standard clock |
| CN201294513Y (en) * | 2008-09-26 | 2009-08-19 | 华东电网有限公司 | System for synchronizing whole network time based on satellite common vision |
| CN101383653A (en) * | 2008-10-30 | 2009-03-11 | 航天东方红卫星有限公司 | Automatic time synchronizing method on satellite |
| CN102012671A (en) * | 2009-09-08 | 2011-04-13 | 上海卫星工程研究所 | Simple multimode high-stability satellite clock device |
| CN102118847A (en) * | 2009-12-31 | 2011-07-06 | 北京控制工程研究所 | Satellite clock and ground clock unifying method and device for ground test |
| CN102566408A (en) * | 2010-12-10 | 2012-07-11 | 上海卫星工程研究所 | Calibration system for satellite clock and calibration method thereof |
| CN102981402A (en) * | 2012-11-20 | 2013-03-20 | 北京控制工程研究所 | Method for calibrating satellite-to-ground time |
| CN103197535A (en) * | 2013-04-12 | 2013-07-10 | 北京空间飞行器总体设计部 | Method for satellite-ground timing with oscilloscope |
Non-Patent Citations (2)
| Title |
|---|
| 任金彬等: "《嫦娥一号卫星星地时差校正量计算方法》", 《航天器工程》 * |
| 陶春燕等: "《一种适用于外场站接收机设备时延的标定方法》", 《现代导航》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114943061A (en) * | 2022-06-28 | 2022-08-26 | 北京航天驭星科技有限公司 | Satellite time difference data processing method and system, electronic device and medium |
| CN114943061B (en) * | 2022-06-28 | 2022-10-25 | 北京航天驭星科技有限公司 | Satellite time difference data processing method and system, electronic device and medium |
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| CN105068415B (en) | 2017-11-03 |
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