Analysis demonstrates improvement in guidance accuracy and control effort for tactical missiles, suggesting the efficacy of Riccati-based methods.
A fully coupled six degrees of freedom modelling of a tactical missile and an optimal control theory-based method are presented aiming at minimizing the autopilot control effort and improving the accuracy of reaching the target by a missile guidance system. A state-dependent Riccati equation-based regulator of controls deflection with an infinite time horizon is employed and its appropriateness for this type of a problem clarified. With the purpose of improving the precision of the autopilot system using a classic three-loop approach, a nonlinear statedependent optimal feedback compensation with anti-windup system has been used incorporating measurements from an accelerometer and gyro rates. The simulated results for the missile model and optimal autopilot structure are compared with classic three-loop autopilot approach in a guidance system.
No takes yet. Share an insight, caveat, or question.
Mikutel et al. (2025) studied this question.
Synapse has enriched 5 closely related papers on similar clinical questions. Consider them for comparative context: