CN103808330B - A kind of star sensor field trial satellite ephemeris computational methods - Google Patents
A kind of star sensor field trial satellite ephemeris computational methods Download PDFInfo
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- CN103808330B CN103808330B CN201210439239.XA CN201210439239A CN103808330B CN 103808330 B CN103808330 B CN 103808330B CN 201210439239 A CN201210439239 A CN 201210439239A CN 103808330 B CN103808330 B CN 103808330B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C25/00—Manufacturing, calibrating, cleaning, or repairing instruments or devices referred to in the other groups of this subclass
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C21/00—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00
- G01C21/02—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 by astronomical means
Abstract
The invention discloses a kind of star sensor field trial satellite ephemeris computational methods, it includes the steps of determining that calculating input and output amount parameter, utilizes input quantity, calculates output according to formula such as spherical triangle, astronomical ephemeris computation.Compared with prior art, its advantage and providing the benefit that: solve satellite under ground static operating mode with the problem that flight track ephemeris is inconsistent in-orbit, it is achieved that the simulation of process of the test Satellite Live Flying track.The method empirical tests result is correct, respond well, except can be applicable to star sensor field trial, applies also for the system-level field trial of other optical measurement such as sun sensor.
Description
Technical field
The present invention relates to a kind of star sensor field trial technology, the especially track ephemeris computation method of satellite when carrying out star sensor system level field trial.
Background technology
Field trial currently for star sensor is mainly product-level, is connected with spaceborne computer by star sensor so that it is the system-level test in outfield accessing satellite attitude control system closed loop did not also carry out.But in order to fully verify that in star sensor installation polarity in satellite attitude control system, service behaviour and systems soft ware, star sensor data processes the correctness with attitude algorithm, it is necessary for carrying out the system-level test in star sensor outfield.
System-level test is exactly the field trial place at broad view, select fine night, mounting means on analog satellite, star sensor is arranged on turntable, and be connected with spaceborne computer, allowing star sensor be operated in and operating mode approximate in orbit, output inertial attitude data are to spaceborne computer, and spaceborne computer calculates the track profile of satellite according to inertial attitude data in conjunction with track almanac data.
Test there is the problem that, the ephemeris of satellite and orbit parameter and situation about truly flying in-orbit inconsistent at present, test location longitude and latitude is exactly test the substar longitude and latitude that moment satellite orbital position is corresponding, the known quantity determined that, the semi-major axis of track, eccentricity, orbit inclination angle takes satellite actual value in-orbit, circular orbit satellite is constant value by these several parameters, above-mentioned parameter can be arranged in spaceborne computer software as constant in advance, and track argument, right ascension of ascending node, during test, on the star of spaceborne computer, the parameter such as clock can not directly obtain, therefore situation in-orbit can not truly be simulated.
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of star sensor field trial satellite ephemeris computational methods.It can meet star sensor field trial needs.
For solving above-mentioned technical problem, a kind of star sensor field trial satellite ephemeris computational methods of the present invention, are utilize known inclination of satellite orbit i, test location latitudeAnd longitude, calculate local correspondence time on-test in moment of ascending node of orbit and the track argument of spaceborne computer clock, satellite position in track segmental arc and the method reflecting orbital plane and the right ascension of ascending node of equatoriat plane relative position.
Described star sensor field trial satellite ephemeris computational methods, it comprises the steps:
1) calculating input and output amount parameter is determined
Determine test location longitude, latitude, inclination of satellite orbit i, ascending node local time tdAs input quantity, moment on-test t0And the track argument U that the moment is corresponding0, right ascension of ascending nodeFor output；
2) test moment track argument U is calculated0
Utilize orbit inclination angle i first to calculate orbital plane and equatoriat plane angle, utilize its angle, location latitude, calculate test moment track argument U according to spherical triangle formula0；
3) moment on-test t is calculated0
Utilize orbit inclination angle i first to calculate orbital plane and equatoriat plane angle, recycle its angle andAscending node and meridian plane angle is calculated, the t local time in of utilizing its angle and ascending node according to spherical triangle formulad, longitudeCalculate moment on-test t0；
4) right ascension of ascending node is calculated
Utilize the t calculated0Calculate Julian date, and then calculate t0Greenwich sidereal time in moment angle, utilize t0、td、Calculate right ascension of ascending node。
The method that the present invention adopts, compared with prior art, its advantage and providing the benefit that: the present invention proposes a kind of system-level test satellite ephemeris computation method in general star sensor outfield, solve satellite under ground static operating mode with flight track ephemeris is inconsistent in-orbit problem, it is achieved that the simulation of process of the test Satellite Live Flying track.The method empirical tests result is correct, respond well, except can be applicable to star sensor field trial, applies also for the system-level field trial of other optical measurement such as sun sensor.
Accompanying drawing explanation
Below with reference to drawings and Examples, the invention will be further described.
Satellite orbital position and attitude embodiment schematic diagram when Fig. 1 is for test.
Detailed description of the invention
As it is shown in figure 1, satellite orbital position and attitude schematic diagram during for test, in figure, symbol implication is as follows:
For the earth's core；
N, S represent earth north, the South Pole respectively；
C is ascending node；
Face, place is earth equatorial plane；
For test location warp；
For ascending node place warp；
Face, place is satellite orbit plane；
For orbital plane withIntersection point, namely tests location；
For the celestial body coordinate system in zero attitude situation.
Known input quantity is:
Orbit inclination angle；
B point longitude and latitude、；
The t local time in of ascending node of orbitd。
Output to be asked is:
Track argument U0；
Moment on-test t0；
Right ascension of ascending node。
Calculating process is as follows:
From trirectangular spherical triangle
,, then by spherical triangle formula
Can obtain
So obtaining track argument U0:
Again by spherical triangle formula
Can obtain
Longitude corresponding to Beijing time is
Then should be during Beijing during test
t0=td+
If date respectively year, month, day during test, first calculate Julian date
Greenwich sidereal time, angle was:
Right ascension of ascending nodeFor:
Spaceborne computer calculates the parametric results of gained in aforementioned manners and carries out Orbit simulation computing, operation result can keep consistent with satellite Live Flying track when the overtesting location, analog satellite situation in orbit more truly, for the operating condition of test that the checking test offer of star sensor is more true to nature.
Claims (1)
1. star sensor field trial satellite ephemeris computational methods, utilize known inclination of satellite orbit i, test location latitudeAnd longitudeIt is characterized in that: the calculating to local correspondence time on-test in moment of ascending node of orbit and spaceborne computer clock, the track argument of reflection satellite position in track segmental arc and reflection orbital plane with the right ascension of ascending node of equatoriat plane relative position, including: 1) determine calculating input and output amount parameter
Determine test location longitude, latitude, inclination of satellite orbit i, ascending node local time tdAs input quantity, moment on-test t0And the track argument U that the moment is corresponding0, right ascension of ascending nodeFor output；
2) test moment track argument U is calculated0
Utilize orbit inclination angle i first to calculate orbital plane and equatoriat plane angle, utilize its angle, location latitude, calculate test moment track argument U according to spherical triangle formula0；
3) moment on-test t is calculated0
Utilize orbit inclination angle i first to calculate orbital plane and equatoriat plane angle, recycle its angle andAscending node and meridian plane angle is calculated, the t local time in of utilizing its angle and ascending node according to spherical triangle formulad, longitudeCalculate moment on-test t0；
4) right ascension of ascending node is calculated
Utilize the t calculated0Calculate Julian date, and then calculate t0Greenwich sidereal time in moment angle, utilize t0、td、Calculate right ascension of ascending node。
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| CN103808330B true CN103808330B (en) | 2016-07-20 |
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| CN104965208A (en) * | 2015-04-01 | 2015-10-07 | 北京理工雷科电子信息技术有限公司 | Ephemeris for simulation of satellite navigation signals, and almanac obtaining method |
| CN108710379B (en) * | 2018-06-14 | 2021-02-02 | 上海卫星工程研究所 | Method for calculating yaw guide angle in imaging of stationary satellite |
| CN113532423A (en) * | 2021-07-22 | 2021-10-22 | 哈尔滨工业大学 | Astronomical platform autonomous positioning method based on tilt angle sensor |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN101082494A (en) * | 2007-06-19 | 2007-12-05 | 北京航空航天大学 | Self boundary marking method based on forecast filtering and UPF spacecraft shading device |
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| KR100666160B1 (en) * | 2004-12-29 | 2007-01-09 | 한국항공우주연구원 | Satellite Magnetometer Bias Correction Method Using Orbit Geometry |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN101082494A (en) * | 2007-06-19 | 2007-12-05 | 北京航空航天大学 | Self boundary marking method based on forecast filtering and UPF spacecraft shading device |
Non-Patent Citations (2)
| Title |
|---|
| 基于GPS非差观测值的CHAMP卫星约化动力学定轨方法研究;周建;《中国优秀硕士学位论文全文数据库信息科技辑》;20120715(第7期);正文第2,10-12,38-39页 * |
| 基于星敏感器的卫星瞬时姿态计算方法;郑万波;《吉林大学学报》;20030228;第21卷(第1期);第27-30页 * |
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