Spacecraft orbit correction on high-elliptic orbit with low-trust engines

Space technologies


Protopopov A. P.*, Bogachev A. V.**, Vorob'yeva Y. A.***

Korolev Rocket and Space Corporation «Energia», 4а, Lenin str., Korolev, Moscow region, 141070, Russia



Orbit inclination correction problem of spacecraft with inertial actuators is considered, spacecraft is found on high elliptic orbit, correction is provided by using the electrojet engines under undisturbance orbit period. Main complexity of this problem is non-linear changing of angular rate and it leads to the difficulty of determination of elector jet cyclogram.
Given algorithm was developed based on equations for undisturbance orbit period and equations for inertial actuators angular momentum. Equations for orbit period were obtained from 3rd Kepler law. Equations for angular momentum of inertial actuators were obtained from angular momentum variation law. Spacecraft inertia tensor is considered as diagonal matrix.
This algorithm can be used in spacecraft software in the cases when spacecraft is found on high elliptic orbit and it uses inertial actuators for attitude control.
The present study provides a starting-point for further research and optimizing this algorithm to apply it for satellite angular momentum control while orbit correction is in progress. Body reference frame coincides with the orbital reference frame (it is similar to LVLH – local vertical local horizontal) while orbit correction is in progress.
Equations for operating engines cyclogram calculation and angular momentum estimation at the end of orbit correction were developed. This algorithm probably will be used in future satellite software to optimize orbit correction.


high elliptic orbit, orbit correction, electrojet engines, orbit period, inertial actuators


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