Optimal Factorization of the State-Dependent Riccati Equation Technique in a Satellite Attitude and Orbit Control System

The satellite attitude and orbit control system (AOCS) can be designed with success by linear theory if the has slow angular motions small maneuver. However, for large fast maneuvers, linearized models are not able to represent all perturbations due effects of nonlinear terms present in dynamics actuators (e.g., saturation). Therefore, such cases, it is expected that techniques yield better performance than techniques. One candidate technique design AOCS law under a maneuver State-Dependent Riccati Equation (SDRE). SDRE entails factorization (that is, parameterization) into state vector product matrix-valued function depends on itself. In doing so, brings (nonunique) structure having state-dependent coefficient (SDC) matrices then minimizes index quadratic-like structure. nonuniqueness SDC creates extra degrees freedom, which used enhance controller performance, however, poses challenges since fulfill requirements. Moreover, regarding satellite's kinematics, there plethora options, e.g., Euler angles, Gibbs vector, modified Rodrigues parameters (MRPs), quaternions, etc. Once again, some kinematics formulation do this paper, we evaluate options (SDC matrices) exploring requirements technique. Considering Brazilian National Institute Space Research (INPE) typical mission, must stabilize three-axis, application equipped optimal gains missions. initial results show MRPs provides an matrix.