Performance analysis of recoverable flight control systems using hybrid dynamical models

The main goal of this paper is to describe and validate a specific hybrid dynamical model for NASA´s recoverable computer system subjected to simulated random upsets. The system is closed-looped with a Boeing 737 simulation model which is flying at cruising altitude. The validation is based on a controlled experiment where the computer upsets are injected into the system at a desired rate, and the effects on the output tracking performance of a simulated aircraft are directly observed and quantified. The hybrid model consists of a jump-linear system driven by a finite-state machine with a Markov input. The jump-linear system models the switched dynamics of the closed-loop due to the presence of controller recoveries, the finite-state machine models the recovery logic, and the Markov input acts as an upset generator. Stability analysis is performed on the hybrid model using existing techniques. The paper supplies the additional performance theory for analyzing the tracking error mean output power. The results are compared against experimental data, showing good agreement.