Robustness analysis of a reusable launch vehicle flight control law

This paper describes a novel optimisation-based framework for analysing the robustness of advanced flight control laws for reusable launch vehicles. The proposed analysis methods are applied and tested on an industrial-standard simulation model of a reusable launch vehicle equipped with a full authority nonlinear dynamic inversion-based flight control law. The reliability, computational complexity and efficiency of the framework are evaluated against standard industrial approaches based on Monte Carlo simulation. The results of the study show that the proposed approach has the potential to significantly improve both the reliability and efficiency of the flight clearance process for future reusable launch vehicles. © 2008 Elsevier Ltd. All rights reserved.

flight control hybrid optimisation nonlinear systems robustness analysis analysis methods flight clearances flight control flight control laws hybrid optimisation monte carlo simulations non-linear dynamic inversions re-usable launch vehicles robustness analysis simulation models automobile exhibitions computational complexity computational efficiency hybrid systems launching missile launching systems monte carlo methods nonlinear analysis nonlinear systems reusability reusable rockets robust control robustness (control systems) trajectories vehicles flight control systems

Robustness analysis of a reusable launch vehicle flight control law Articles