Integrated Design and Accuracy Analysis of Star Sensor and Gyro on the Same Benchmark for Satellite Attitude Determination System
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摘要
As an important sensor in the navigation systems,star sensors and the gyro play important roles in spacecraft attitude determination system. Complex environmental factors are the main sources of error in attitude determination. The error influence of different benchmarks and the disintegration mode between the star sensor and the gyro is analyzed in theory. The integrated design of the star sensor and the gyro on the same benchmark can effectively avoid the error influence and improves the spacecraft attitude determination accuracy. Simulation results indicate that when the stars sensor optical axis vectors overlap the reference coordinate axis of the gyro in the same benchmark, the attitude determination accuracy improves.
As an important sensor in the navigation systems,star sensors and the gyro play important roles in spacecraft attitude determination system. Complex environmental factors are the main sources of error in attitude determination. The error influence of different benchmarks and the disintegration mode between the star sensor and the gyro is analyzed in theory. The integrated design of the star sensor and the gyro on the same benchmark can effectively avoid the error influence and improves the spacecraft attitude determination accuracy. Simulation results indicate that when the stars sensor optical axis vectors overlap the reference coordinate axis of the gyro in the same benchmark, the attitude determination accuracy improves.
As an important sensor in the navigation systems,star sensors and the gyro play important roles in spacecraft attitude determination system. Complex environmental factors are the main sources of error in attitude determination. The error influence of different benchmarks and the disintegration mode between the star sensor and the gyro is analyzed in theory. The integrated design of the star sensor and the gyro on the same benchmark can effectively avoid the error influence and improves the spacecraft attitude determination accuracy. Simulation results indicate that when the stars sensor optical axis vectors overlap the reference coordinate axis of the gyro in the same benchmark, the attitude determination accuracy improves.
引文
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[3]X.J.Wu and X.L.Wang,"A SINS/CNS deep integrated navigation method based on mathematical horizon reference,"Aircraft Engineering and Aerospace Technology,vol.83,no.1,pp.26-34,201 1.
[4]H.M.Qian,X.K.Lang,L.C.Qian,P.Yu,and H.Y.Wang,"Ballistic missile SINS/CNS integrated navigation method,"J.Beijing University of Aeronautics and Astronautics,vol.43,no.5,pp.857-864,2017.
[5]X.B.Yuan,C.Zhang,and C.L.Shi."The cubature Kalman filter and its application in the satellite star-sensor/gyro attitude determination system,"in Proc.China Satellite Navigation Conf.(CSNC),Vol.2,pp.307-316.2017.
[6]P.Wang,Y.C.Zhang,and W.Y.Qiang,"Research on the algorithm of on-orbit calibration based on gyro/star-sensor,"in Proc.Int.Conf.Machine Learn ing and Cybernetics,pp.303-307,2009.
[7]N Venkateswaran,E.K.Kumar,P.S.Goel,and M. S.Bhat,"Star sensor/earth sensor updated gyro reference for precision pointing spacecraft,"J.Spacecraft Technology,vol.3,no.3,pp.25-37,1993.
[8]C.C.Fan,M.Wang,B.Yang,S.Y.Jin,J.Pan,and X.L.Chang,"A method of high-precision ground processing for star sensor and gyro combination and accuracy verification."Acta Optica Sinica,vol.36,no.11,pp.1-13,Nov.2016.
[9]Z.Y.Zheng,Y.B.Gao, K.P.He,and J.J.Hou,"Online error estimation of fiber-optic gyroscope strapdown attitude and heading reference system aided by star sensors,"Binggong Xuebao/acta Armamentarii,vol.35,no.4,pp.509-515,2014.
[10]F.Jiang,Q.Wu,Z.Wang,J.Miao,L.Guo,L.Chen,and X.Yang,"Analysis and verification of structure stability and thermal stability of a bracket of star sensors,"Infrared and Laser Engineering,vol.44,no.11,pp.3463-3468,2015.
[11]C.Zhang,Z.Xiong,R.Wang,J.Liu,and H.Peng,"New INS/CNS integrated algorithm on aerospace vehicle with directly sensing horizon,"Chinese Space Science and Technology,vol.33,no.3,pp.64-71,Nov.2013.
[12]X.F.Chen and Z.J.Guan,"Fiber optic gyro strapdown attitude and heading reference system for ship,"J.Dalian Maritime University,vol.31,no.1,pp.26-28,2005.
[13]AIAA.Sed16 autonomous star sensor product line in flight results,newdevelopments and improvements in progress,in Proc.AIAA Guidance,Navigation,and Control Conf and Exhibit,pp.1585-1 594,Aug.2005.
[14]L.Blarre,J.Ouaknine,L.Oddosmarcel,and P.E.Martinez,"High accuracy sodem star trackers:recent improvements proposed on sed36and hydra star trackers,"in Proc.AIAA Guidance,Navigation,and Control Conf.and Exhibit,pp.21-27,Aug.2006.
[15]J.Q.Wang,Y.Y.Jiao,H.Y.Zhou,and W.U.Yi,"Principle modeling and precision factor simulation on satellite attitude determination for star sensor/gyro combined system,"J.System Simulation,vol.21,no.23,pp.7408-7417,2009.
[16]X.Q.Ji,L.Gao,Z.Liu,and H.Zong,"Spacecraft autonomous navigation system based on sins/ultraviolet sensor/star sensor,"in Proc.Guidance,Navigation and Control Con.f,pp.1660-1664,201 7.
[17]C.J.Gioia and J.A.Christian,"Gyro bias estimation using interior star angles for manual attitude determination,"J.Spacecraft and Rockets,vol.54,no.2,pp.1-11,2016.
[18]Y.S.Zhang,H.Wang,J.B.Chen,W.Huang,and Y.N.Gao,"FOG/star-sensor combination technology for satellite three-axis attitude determination,"J.Chinese Inertial Technology,vol.11,no.2,pp.1-4,Feb.2003.
[19]X.Pan,Y.Jiao,H.Zhou,and J.Wang.Fusion Theory and Methods For Satellite State Estimation.Beijing:Science Press,pp.23-30,20 1 3.
[20]Y.Y.Jiao,H.Y.Zhou,J.Q.Wang,and J.Q.Li,"Linearization errors measure and its influence on the accuracy of MEKF based attitude determination method,"Aerospace Science and Technology,vol.16,no.1,pp.61-69,2012.
[21]Q.H.Zhu and Y.B.Li,"Extended Kalman filter for attitude determination using gyros and quaternion,"Aerospace Shanghai,vol.4,no.1,pp.1-5,Apr.2005.