Abstract
This paper deals with the compensator design of launch vehicle attitude control in atmospheric phase using optimization algorithm. Traditionally compensator design is carried out intuitively based on physical parameters of launch vehicle. It is arrived at after a long trial and error procedure to fulfil frequency domain requirements. In this paper a multi-constraint satisfaction algorithm is used to design compensator for attitude control, which takes into account the frequency and time domain requirements. The effect of actuator non-linear behavior on slosh dynamics is investigated and the analytical expression for slosh response with respect to actuator amplitude is derived. The slosh closed loop pole migration with the variation in actuator command amplitudes in root locus is discussed and the implication of acceptable actuator limit cycle amplitude on vehicle body rate is brought out.
Sign-in/Register to access full text options 
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
