Minimum Trajectory Sensitivity of a Large Launch Booster Control System

An optimal closed-loop control scheme is developed for a linear timevarying system. The system has two independent parameters which may deviate from their nominal values. The problem is motivated by the possible failure of the control system of the large launch booster after takeoff. The computational scheme involves an iterative algorithm and requires the solution to a matrix Riccati equation. An example is given as an illustration.