This study describes the development and application of new analysis techniques using the structured singular value m for the clearance of flight control laws for highly augmented aircraft. Motivated by the limitations of the classical methods currently used by industry, these new techniques have been developed to provide a more rigours and efficient analysis of worst-case aircraft stability and performance characteristics. The classical approaches currently used in industry for the clearance of flight control laws are explained and evaluated. New m-tools are developed to directly address specific clearance criteria currently used by industry. Different approaches to represent uncertain linear and nonlinear systems as Linear Fractional Tran...
In this work, a successive robust flutter prediction technique is developed by coupling nominal anal...
Abstract: In this paper, global optimisation and nonlinear simulation are used to search for the wor...
Flight Control Systems are often designed in linearization points over a flight envelope and it must...
tigated the potential of a number of advanced analysis techniques for use in the clearance of flight...
AbstractThe main goal of flight clearance is to use the structured singular value (μ) analysis of th...
[Abstract] Due to the continuously increasing design requirements on modern aircraft the robustness ...
To validate the robust stability of the flight control system of hypersonic flight vehicle, which su...
This paper describes flight control law validation issues raised at NASA Dryden, and recasts these p...
The objective of the research was to identify and evaluate promising mathematical techniques for re-...
This article presents a new paradigm for robust flutter modeling and analysis of high-order uncertai...
The flight control law clearance problem can be formulated as a robustness analysis problem, where ...
peer-reviewedThe paper introduces a new approach for the computation of a lower bound on the struct...
This thesis describes the development and application of optimisation-based methods for worst-case a...
Results for stability analysis of the nonlinear rigid aircraft model and comfort and loads analysis ...
This chapter presents results obtained by applying the Lyapunov-based robustness analysis techniques...
In this work, a successive robust flutter prediction technique is developed by coupling nominal anal...
Abstract: In this paper, global optimisation and nonlinear simulation are used to search for the wor...
Flight Control Systems are often designed in linearization points over a flight envelope and it must...
tigated the potential of a number of advanced analysis techniques for use in the clearance of flight...
AbstractThe main goal of flight clearance is to use the structured singular value (μ) analysis of th...
[Abstract] Due to the continuously increasing design requirements on modern aircraft the robustness ...
To validate the robust stability of the flight control system of hypersonic flight vehicle, which su...
This paper describes flight control law validation issues raised at NASA Dryden, and recasts these p...
The objective of the research was to identify and evaluate promising mathematical techniques for re-...
This article presents a new paradigm for robust flutter modeling and analysis of high-order uncertai...
The flight control law clearance problem can be formulated as a robustness analysis problem, where ...
peer-reviewedThe paper introduces a new approach for the computation of a lower bound on the struct...
This thesis describes the development and application of optimisation-based methods for worst-case a...
Results for stability analysis of the nonlinear rigid aircraft model and comfort and loads analysis ...
This chapter presents results obtained by applying the Lyapunov-based robustness analysis techniques...
In this work, a successive robust flutter prediction technique is developed by coupling nominal anal...
Abstract: In this paper, global optimisation and nonlinear simulation are used to search for the wor...
Flight Control Systems are often designed in linearization points over a flight envelope and it must...