CN102745343B - Rapid forecasting method for disturbance arc segment of synchronous satellite early-stage measurement and control segment - Google Patents
Rapid forecasting method for disturbance arc segment of synchronous satellite early-stage measurement and control segment Download PDFInfo
- Publication number
- CN102745343B CN102745343B CN201210239598.0A CN201210239598A CN102745343B CN 102745343 B CN102745343 B CN 102745343B CN 201210239598 A CN201210239598 A CN 201210239598A CN 102745343 B CN102745343 B CN 102745343B
- Authority
- CN
- China
- Prior art keywords
- satellite
- point
- synchronous
- synchronous satellite
- fixed
- 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
Abstract
The invention discloses a rapid forecasting method for a disturbance arc segment of a synchronous satellite early-stage measurement and control segment, belongs to the field of aerospace measurement and control, and relates to a satellite spatial geometry disturbance computing method based on an observation station beam range and a synchronous satellite dot frequency. The method comprises forecasting the positions bar(r(t)) of satellites in the arc segment according to the precise orbit calculation of synchronous satellites to be positioned and sequentially judging whether the synchronous satellites to be positioned can cause disturbance on the ith positioned synchronous satellite, i=1, 2, ellipsis, N, wherein N is the total number of positioned synchronous satellites, and the disturbance arc segment and time are also given. The method disclosed by the invention has the beneficial effects that disturbance arc segment forecasting is carried out rapidly and accurately, satellites possibly to be disturbed and periods are determined, the arrangement of measurement and control incidents are properly adjusted, real-time measurement and control tasks are smoothly completed, at the same time disputes are avoided, and the smooth completion of synchronous satellite positioning is guaranteed.
Description
Technical field
Patent of the present invention belongs to aerospace measurement and control field, relates to a kind of based on survey station beam area and how much interference calculation methods of synchronous asterism satellite spatial frequently.
Background technology
The accurate sync section of synchronous satellite before fixed point, because its orbit altitude and cycle all approach synchronous satellite very much, in addition all synchronous satellites are all the overhead under the line of fixing a point, so the angle between the vector of this TT&C station is very little in section sometime relatively may to cause certain satellite that the vectorial sum of the relatively a certain TT&C station of satellite fixed a point, at this moment TT&C station is issued an order and just may be caused interference in various degree to the signal of the synchronous satellite of having fixed a point, and brings much inconvenience to the user of this star.For successfully to satellite control not to its synchronous satellite through region cause interference, just should avoid controlling within the time period that may produce interference.How to calculate accurately the segmental arc that these may produce interference, method is in the past to calculate according to the fixed point longitude of the current position of satellite and near synchronous satellite, and synchronous satellite is after fixed point, be subject to the impact of some perturbation factors can depart from original position, according to the fixed point scope of the regulation synchronous satellite of International Satellite Organization, it is ± 0.05 degree, so synchronous satellite must regularly be controlled it after fixed point, to guarantee the normal operation of satellite, so the result of calculating with fixed point longitude and actual deviation are larger, may cause some and actual just in time contrary result, cause unnecessary trouble, this project provides a kind of method of calculating that disturbs segmental arc that forecasts according to TLE in view of the foregoing.
Summary of the invention
The object of the invention is: in order to solve the large problem of deviation that in prior art, the early stage observing and controlling section of synchronous satellite disturbs segmental arc Fast Prediction method to exist, the present invention provides a kind of method of disturbing segmental arc of forecasting according to TLE.
Technical scheme of the present invention is: the early stage observing and controlling section of synchronous satellite is disturbed segmental arc Fast Prediction method, comprises the steps:
Step 1: according to the position of satellite in the Precise Orbit CALCULATING PREDICTION segmental arc of point to be located synchronous satellite
Step 2: i=1;
Step 3: filter out synchronous satellite according to i the number of turns that the TLE Satellite of stationary satellite has moved for a day, if i satellite is synchronous satellite, enter step 4, otherwise, think that point to be located synchronous satellite can not cause interference to i satellite, enters step 7;
Step 4: the fixed point longitude a that calculates i the synchronous satellite of having fixed a point
iif, | a
i-b
i|≤5 °, enter step 5; Otherwise, think that point to be located synchronous satellite can not cause interference to i the synchronous satellite of having fixed a point, and enters step 7; Wherein, b
icurrent longitude for point to be located synchronous satellite;
Step 5: calculate the position of this satellite in forecast segmental arc according to the TLE of i the synchronous satellite of having fixed a point
according to point to be located synchronous satellite position
calculate t and constantly to i, fixed a point synchronous satellite at the elevation angle of certain survey station, if the elevation angle is greater than zero degree, i.e. tracking is visible, enters step 6, otherwise, think that point to be located synchronous satellite can not cause interference to i the synchronous satellite of having fixed a point, and enters step 7;
Step 6: according to the position of t moment i fixed a point synchronous satellite and point to be located synchronous satellite
with
calculate the vector angle of two relative survey stations of satellite:
In above formula
position for survey station;
If θ
i(t)≤θ
0, given value θ
0meet 0.01 °≤θ
0≤ 0.1 °, think that this moment point to be located synchronous satellite can cause interference to i the synchronous satellite of having fixed a point;
Step 7: if i<N: i=i+1, enters step 3; Otherwise: the early stage observing and controlling section of synchronous satellite disturbs segmental arc Fast Prediction to complete.
The invention has the beneficial effects as follows: disturb rapidly and accurately segmental arc forecast, determine satellite and the time period that may be disturbed, arrangement to TT&C event is suitably adjusted, when completing smoothly real-time TT&C task, also avoid the generation of this type of dispute, guaranteed completing smoothly of synchronous satellite fixed point work.
The specific embodiment
In the present embodiment, stationary satellite number is 60, and needing to calculate the survey station disturbing is Sta_A, and in the present embodiment, the early stage observing and controlling section of synchronous satellite disturbs segmental arc Fast Prediction method to comprise the steps:
Step 1: according to the position of satellite in the Precise Orbit CALCULATING PREDICTION segmental arc of point to be located synchronous satellite
Step 2: i=1;
Step 3: filter out synchronous satellite according to i the number of turns that the TLE Satellite of stationary satellite has moved for a day, if i satellite is synchronous satellite, enter step 4, otherwise, think that point to be located synchronous satellite can not cause interference to i satellite, enters step 7;
Step 4: the fixed point longitude a that calculates i the synchronous satellite of having fixed a point
iif, | a
i-b
i|≤5 °, enter step 5, otherwise, think that point to be located synchronous satellite can not cause interference to i the synchronous satellite of having fixed a point, and enters step 7; Wherein, b
icurrent longitude for point to be located synchronous satellite;
Step 5: calculate the position of this satellite in forecast segmental arc according to the TLE of i the synchronous satellite of having fixed a point
according to point to be located synchronous satellite position
calculate t and constantly to i, fixed a point synchronous satellite at the elevation angle of certain survey station, if the elevation angle is greater than zero degree, i.e. tracking is visible, enters step 6, otherwise, think that point to be located synchronous satellite can not cause interference to i the synchronous satellite of having fixed a point, and enters step 7;
Step 6: according to the position of t moment i fixed a point synchronous satellite and point to be located synchronous satellite
with
calculate the vector angle of two relative survey stations of satellite:
In above formula
position for Sta_A survey station;
If θ
i(t)≤θ
0, given value θ in the present embodiment
0=0.05 °, think that this moment point to be located synchronous satellite can cause interference to i the synchronous satellite of having fixed a point;
Step 7: if i<60: i=i+1, enters step 3; Otherwise: the early stage observing and controlling section of synchronous satellite disturbs segmental arc Fast Prediction to complete.
Through all TLE that download are calculated, point to be located satellite can cause interference to the 12nd, 35 synchronous satellites of fixing a point, and disturbs segmental arc to see the following form:
In the present embodiment, disturb segmental arc forecast result
Claims (1)
1. the early stage observing and controlling section of synchronous satellite is disturbed segmental arc Fast Prediction method, comprises the steps:
Step 1: according to the position of satellite in the Precise Orbit CALCULATING PREDICTION segmental arc of point to be located synchronous satellite
Step 2: i=1;
Step 3: filter out synchronous satellite according to i the number of turns that the TLE Satellite of stationary satellite has moved for a day, if i satellite is synchronous satellite, enter step 4, otherwise, think that point to be located synchronous satellite can not cause interference to i satellite, enters step 7;
Step 4: the fixed point longitude a that calculates i the synchronous satellite of having fixed a point
iif, | a
i-b
i|≤5 °, enter step 5; Otherwise, think that point to be located synchronous satellite can not cause interference to i the synchronous satellite of having fixed a point, and enters step 7; Wherein, b
icurrent longitude for point to be located synchronous satellite;
Step 5: calculate the position of this satellite in forecast segmental arc according to the TLE of i the synchronous satellite of having fixed a point
according to point to be located synchronous satellite position
calculate t and constantly to i, fixed a point synchronous satellite at the elevation angle of certain survey station, if the elevation angle is greater than zero degree, i.e. tracking is visible, enters step 6, otherwise, think that point to be located synchronous satellite can not cause interference to i the synchronous satellite of having fixed a point, and enters step 7;
Step 6: according to the position of t moment i fixed a point synchronous satellite and point to be located synchronous satellite
with
calculate the vector angle of two relative survey stations of satellite:
In above formula
position for survey station;
If θ
i(t)≤θ
0, given value θ
0meet 0.01 °≤θ
0≤ 0.1 °, think that this moment point to be located synchronous satellite can cause interference to i the synchronous satellite of having fixed a point;
Step 7: if i<N: i=i+1, enters step 3; Otherwise: the early stage observing and controlling section of synchronous satellite disturbs segmental arc Fast Prediction to complete.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210239598.0A CN102745343B (en) | 2012-07-12 | 2012-07-12 | Rapid forecasting method for disturbance arc segment of synchronous satellite early-stage measurement and control segment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210239598.0A CN102745343B (en) | 2012-07-12 | 2012-07-12 | Rapid forecasting method for disturbance arc segment of synchronous satellite early-stage measurement and control segment |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102745343A CN102745343A (en) | 2012-10-24 |
| CN102745343B true CN102745343B (en) | 2014-08-13 |
Family
ID=47025942
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210239598.0A Active CN102745343B (en) | 2012-07-12 | 2012-07-12 | Rapid forecasting method for disturbance arc segment of synchronous satellite early-stage measurement and control segment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102745343B (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6078286A (en) * | 1998-06-03 | 2000-06-20 | Motorola, Inc. | Method and apparatus for efficient acquisition and tracking of satellites |
| FR2809831A1 (en) * | 2000-06-06 | 2001-12-07 | Loral Space Systems Inc | CORRECTION OF PERIGEE ARGUMENT WITH LONGITUDE CONTROL FOR GEOSYNCHRONOUS SATELLITES IN INCLINED ECCENTRIC ORBIT |
| CN1486545A (en) * | 2000-11-13 | 2004-03-31 | Լ����E����ķ | System and method for implementing a constellation of non-geostationary satellites that does not interfere with the geostationary satellite ring |
| DE102007041994A1 (en) * | 2007-09-04 | 2009-04-02 | Schepelmann, Jürgen | Device, particularly auxiliary satellite for ejecting impulse mass for deflecting disturbing satellite on tolerable path by collision, has drive unit for ejecting impulse mass on trajectory in direction of target satellite |
| CN102126564A (en) * | 2010-01-19 | 2011-07-20 | 泰勒斯公司 | Method and device for optimization of the mass of a satellite |
| CN102494676A (en) * | 2011-12-12 | 2012-06-13 | 中国科学院长春光学精密机械与物理研究所 | Satellite automatic recognition device under complicated backgrounds |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8041118B2 (en) * | 2007-02-16 | 2011-10-18 | The Boeing Company | Pattern recognition filters for digital images |
-
2012
- 2012-07-12 CN CN201210239598.0A patent/CN102745343B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6078286A (en) * | 1998-06-03 | 2000-06-20 | Motorola, Inc. | Method and apparatus for efficient acquisition and tracking of satellites |
| FR2809831A1 (en) * | 2000-06-06 | 2001-12-07 | Loral Space Systems Inc | CORRECTION OF PERIGEE ARGUMENT WITH LONGITUDE CONTROL FOR GEOSYNCHRONOUS SATELLITES IN INCLINED ECCENTRIC ORBIT |
| CN1486545A (en) * | 2000-11-13 | 2004-03-31 | Լ����E����ķ | System and method for implementing a constellation of non-geostationary satellites that does not interfere with the geostationary satellite ring |
| DE102007041994A1 (en) * | 2007-09-04 | 2009-04-02 | Schepelmann, Jürgen | Device, particularly auxiliary satellite for ejecting impulse mass for deflecting disturbing satellite on tolerable path by collision, has drive unit for ejecting impulse mass on trajectory in direction of target satellite |
| CN102126564A (en) * | 2010-01-19 | 2011-07-20 | 泰勒斯公司 | Method and device for optimization of the mass of a satellite |
| CN102494676A (en) * | 2011-12-12 | 2012-06-13 | 中国科学院长春光学精密机械与物理研究所 | Satellite automatic recognition device under complicated backgrounds |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102745343A (en) | 2012-10-24 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP2290226A2 (en) | Systems and methods for interfacing renewable power sources to a power grid | |
| CN106841778B (en) | PMU-based subsynchronous and supersynchronous harmonic parameter processing method | |
| CN104077928B (en) | Be applicable to the navigation of irregular flight outside air route dot position information update method | |
| CN107339991A (en) | A kind of detection method and device at aircraft course angle | |
| CN102435912A (en) | Method for positioning fault disturbance point in power grid | |
| CN105738918A (en) | Satellite-navigation-information-fusion-based power transmission line displacement monitoring system ad method | |
| CN104484717A (en) | Onboard flight path prediction method based on current air route | |
| EP2290407A2 (en) | Systems and methods for interfacing renewable power sources to a power grid | |
| CN102319882A (en) | Method for establishing and determining slab caster-overhauling reference coordinate system | |
| CN105068148A (en) | Wind power plant gust prediction method and system | |
| CN107664096B (en) | Yaw wind control method, device and system | |
| CN104950196A (en) | Combined criterion method for identifying oscillation center of power system | |
| CN102901451A (en) | Method and device for accurately quickly measuring power transmission and distribution project leads | |
| CN112540390A (en) | Tracking forecast calculation method and device for spacecraft | |
| CN106247988B (en) | Celestial body posture based on laser tracker and solar wing spreading frame accuracy measurement method | |
| CN102745343B (en) | Rapid forecasting method for disturbance arc segment of synchronous satellite early-stage measurement and control segment | |
| CN111983509B (en) | Distributed line fault detection method and device | |
| CN102305929B (en) | Method for compensating lever arm error of onboard synthetic aperture radar | |
| CN103248063B (en) | A kind of many direct currents based on PMU coordinate wide area damper control method | |
| CN105071388A (en) | Power distribution network state estimation method based on maximum likelihood estimation theory | |
| CN103129701A (en) | Positioning method of stream guidance cover on segmentation | |
| JP2016031621A (en) | Photovoltaic power generation amount prediction method and photovoltaic power generation amount prediction system | |
| CN106840130A (en) | A device and method is put in high accuracy engineering survey setting-out | |
| CN204832531U (en) | Accurate positioning system of bucket wheel machine | |
| US20220235738A1 (en) | Method and device for determining a rotor orientation of a rotor of a wind turbine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |