Stability Analysis on Earth Observing System AM-1 Spacecraft Attitude Determination

1997 ◽  
Vol 20 (5) ◽  
pp. 1042-1044 ◽  
Author(s):  
Xipu Li ◽  
Jeffrey B. Boka ◽  
Arthur J. Throckmorton
Keyword(s):  
Stability Analysis ◽  
Attitude Determination ◽  
Spacecraft Attitude ◽  
Earth Observing System

A quantum search algorithm for future spacecraft attitude determination

2011 ◽  
Vol 68 (7-8) ◽  
pp. 1208-1218 ◽  
Author(s):  
Jack Tsai ◽  
Fu-Yuen Hsiao ◽  
Yi-Ju Li ◽  
Jen-Fu Shen
Keyword(s):  
Attitude Determination ◽  
Search Algorithm ◽  
Spacecraft Attitude ◽  
Quantum Search ◽  
Quantum Search Algorithm

Stability analysis on Earth Observing System AM-1 spacecraft Earth acquisition

1996 ◽  
Vol 19 (3) ◽  
pp. 512-519
Author(s):  
Xipu Li ◽  
Arthur J. Throckmorton ◽  
Jeffrey B. Boka
Keyword(s):  
Stability Analysis ◽  
Earth Observing System

A Correction Algorithm of Aberration of Light for Spacecraft Attitude Determination System

2012 ◽  
Vol 166-169 ◽  
pp. 3197-3201
Author(s):  
Bao Hua Li ◽  
Xi Jun Chen ◽  
Yang Pang ◽  
Bo Qi Xi
Keyword(s):  
Mathematical Models ◽  
Coordinate System ◽  
Attitude Determination ◽  
Spacecraft Attitude ◽  
Star Sensor ◽  
Correction Algorithm ◽  
Attitude Error ◽  
Determination System ◽  
Space Coordinate ◽  
Celestial Sphere

There is the long periodicity attitude error between true attitude and measurement attitude using star sensor for spacecraft attitude determination system because of aberration of light. Aberration of light occurs because the spacecraft’s velocity has a component that is perpendicular to the line traveled by the light incoming from the star. The type of aberration is analyzed and their constants of aberration are calculated in this paper. According to the constants the aberration, the correction mathematical models of parallax of aberration of light of these types of aberration are derived. The parallax of aberration of light of the recognized stars in the FOV of star sensor is calculated with the mathematical models. Then the true vectors of recognized stars at image space coordinate system of star sensor are calculated. The measurement attitude of star sensor is calculated with the true vectors of recognized stars and their vectors at celestial sphere coordinate system. The simulations show the long periodicity attitude error is corrected with the method in this paper. At last the correction of aberration of light was successfully demonstrated using two star sensors with real sky experiment in 2011.

Stand-alone spacecraft attitude determination using real flight GPS data from UOSAT-12

2002 ◽  
Vol 51 (1-9) ◽  
pp. 261-268 ◽  
Author(s):  
Martin Unwin ◽  
P. Purivigraipong ◽  
Alex da Silva Curiel ◽  
Martin Sweeting
Keyword(s):  
Attitude Determination ◽  
Gps Data ◽  
Spacecraft Attitude
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