In this paper,by taking the spacecraft with deployable and retractable flexible appendage as the object,the principle and method of intelligent adaptive control are researched so as to realize the control target of high precision,high stability and strong adaptability.

The coupled dynamic equations of a spacecraft with tip mass attached flexible appendage which is deployable are obtained by using the momentum theorem.

The attitude dynamic equations of a spacecraft with flexible appendages are obtained by using the momentum theorem.

Considering the condition that modern spacecraft are always of large flexible appendages and the fact that the flexible vibration often degrades the control system performance,this paper employs a method that consists of a feedforward compensator and a feedback control loop to fulfill attitude maneuver rapidly with little residual vibration.

Considering the condition that modern spacecraft are always of large flexible appendages and the fact that the flexible vibration often degrades the control system performance, this paper employs a method that consists of a feed-forward compensator and a feedback control loop to fulfill attitude maneuver rapidly with little residual vibration.