Dynamical Model Compensation for Near-Earth Satellite Orbit Determination

AIAA Journal ◽  
1975 ◽  
Vol 13 (3) ◽  
pp. 343-349 ◽  
Author(s):  
KENNETH A. MYERS ◽  
BYRON D. TAPLEY
Keyword(s):  
Orbit Determination ◽  
Satellite Orbit ◽  
Earth Satellite ◽  
Dynamical Model ◽  
Earth Satellite Orbit

Effect of an oblate rotating atmosphere on the orientation of a satellite orbit

1961 ◽  
Vol 261 (1305) ◽  
pp. 246-258 ◽  
Keyword(s):  
Orbital Plane ◽  
Satellite Orbit ◽  
Major Axis ◽  
Earth Satellite ◽  
Semi Major Axis ◽  
Orbital Inclination ◽  
Small Eccentricity ◽  
Earth Satellite Orbit ◽  
The Right ◽  
Right Ascension

For an earth satellite orbit of small eccentricity ( e < 0·2) formulae are derived for the changes per revolution produced by the atmosphere in the argument of perigee, in the right ascension of the ascending node, and in the orbital inclination. These changes are then expressed in terms of the change in length of the semi-major axis, and numerical values are obtained for satellite 1957 β . It is found that the rotation of the major axis in the orbital plane due to the atmosphere is significant, being most important for inclinations between 60 and 70°. The total rotation, due both to the gravitational potential and to the atmosphere, agrees reasonably well with the observed values. The oblateness of the atmosphere is found to have only a small effect on the changes in the orbital inclination and the right ascension of the ascending node.

On active and passive CETI from an earth satellite orbit

1979 ◽  
Vol 6 (1-2) ◽  
pp. 203-212 ◽  
Author(s):  
Mieczyslaw Subotowicz ◽  
Jerzy Usowicz ◽  
Zbigniew Paprotny
Keyword(s):  
Satellite Orbit ◽  
Earth Satellite ◽  
Earth Satellite Orbit
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