Abstract
Rotational motion of a spacecraft with elastic and dissipative elements as a whole about its center of mass taking into account the control elements designed as single-axis gyrostabilizers in the attitude control mode is studied. Oscillatory processes related to the spacecraft attitude control when the terms emerging due to the elastic oscillations of the structure are comparable with gyroscopic terms. A model problem of spacecraft reorientation is considered. Conditions under which the elastic oscillations do not affect the flat slew of the satellite and assumptions under which no flat slew is possible are obtained. Analytical expressions for estimating the spacecraft deviations from the programmed motion (drift of the angular velocity) are found.
Sign-in/Register to access full text options 
Free) 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
