Synthesis of adaptive algorithm to control motion of the space platform with a rotating solar sail

The task of constructing an adaptive control law with a model adjustable for the spacecraft angular motion control with incomplete measurements of the state vector and parametric uncertainty of the control object has been considered. A space platform with a rotating solar sail was studied as the control object. The spacecraft structure consists of a solar sail as a rotating film disk with the central rigid insert, the instrument compartment with the payload equipment and a compensating powered gyro with a controlled rotor rate. The synthesis of the (feedback) controller and the adaptive observer is made using the motion modes sequential interlocking method (the modified modal control method which is an iterative numerical algorithm allowing to operate with dynamic systems of large dimensions). Mathematical simulation of the phase of the initial angular velocity cancellation of spacecraft has been provided, the results of which demonstrate the effectiveness of the considered adaptive control algorithms and numerical modal control procedures.