Diederick Joosten

Bio: Diederick Joosten is an academic researcher from Delft University of Technology. The author has contributed to research in topics: Control reconfiguration & Model predictive control. The author has an hindex of 12, co-authored 17 publications receiving 500 citations.

Nonlinear Reconfiguring Flight Control Based on Online Physical Model Identification

Abstract: This paper presents a study on fault tolerant flight control of a benchmark aircraft model. Reconfiguring control is implemented by making use of adaptive nonlinear dynamic inversion for manual and autopilot control. The weakness of classical nonlinear dynamic inversion, its sensitivity to modeling errors, is circumvented here by making use of a real-time identified physical model of the damaged aircraft. With help of the Boeing 747 benchmark simulation model, including the realistic component as well as the structural failure modes, it is possible to analyze the damage accommodation capabilities of the considered approach. In failure conditions, the damaged aircraft model is identified by the so-called two-step method in real time and this model is applied subsequently to the model-based adaptive nonlinear dynamic inversion routine in a modular structure, which allows flight control reconfigurations online. After discussing the modular adaptive controller setup, reconfiguration test results are shown for damaged aircraft models using a desktop computer as well as the moving base Simulation, Motion, and Navigation Research Flight Simulator of Delft University. These results indicate satisfactory failure handling capabilities of this fault tolerant control setup, for component as well as structural failures.

Online Aerodynamic Model Structure Selection and Parameter Estimation for Fault Tolerant Control

Abstract: This paper describes a new recursive algorithm for the approximation of time varying nonlinear aerodynamic models by means of a joint adaptive selection of the model structure and parameter estimation. This procedure is called Adaptive Recursive Orthogonal Least Squares (AROLS), and is an extension and modification of the classical Recursive Orthogonal Least Squares (ROLS). This algorithm is considered to be particularly useful for indirect fault tolerant flight control, making use of model based adaptive control routines. After the failure, a completely new aerodynamic model can be elaborated recursively with respect to structure as well as parameter values. The performance of the identification algorithm is demonstrated on some simulation data sets.

A Simulation Benchmark for Integrated Fault Tolerant Flight Control Evaluation

Abstract: This paper presents a description of a large transp ort aircraft simulation benchmark that includes a suitable set of assessment criteria , for the integrated evaluation of fault tolerant flight control systems (FTFC). These syste ms consist of a combination of novel fault detection, isolation (FDI) and reconfigurable contr ol schemes. In 2004, a research group on Fault Tolerant Control, comprising a collaboration of nine European partners from industry, universities and research institutions, w as established within the framework of the Group for Aeronautical Research and Technology in Europe (GARTEUR) co-operation program. The aim of the research group, Flight Mechanics Action Group FM-AG(16), is to demonstrate the capability and viability of modern FTFC schemes when applied to a realistic, nonlinear design problem and to assess t heir capability to improve aircraft survivability. The test scenarios that are an integ ral part of the benchmark were selected to provide challenging assessment criteria to evaluate the effectiveness and potential of the FTFC methods being investigated. The application of fault reconstruction and modelling techniques based on (accident) flight data, as desc ribed in this paper, has resulted in high fidelity non-linear aircraft and fault models for t he design and evaluation of modern FTFC methods.

Piloted Simulator Evaluation Results of New Fault-Tolerant Flight Control Algorithm

Abstract: A high fidelity aircraft simulation model, reconstructed using the Digital Flight Data Recorder (DFDR) of the 1992 Amsterdam Bijlmermeer aircraft accident (Flight 1862), has been used to evaluate a new Fault-Tolerant Flight Control Algorithm in an online piloted evaluation. This paper focuses on the piloted simulator evaluation results. Reconfiguring control is implemented by making use of Adaptive Nonlinear Dynamic Inversion (ANDI) for manual fly by wire control. After discussing the modular adaptive controller setup, the experiment is described for a piloted simulator evaluation of this innovative reconfigurable control algorithm applied to a damaged civil transport aircraft. The evaluation scenario, measurements and experimental design, as well as the real-time implementation are described. Finally, reconfiguration test results are shown for damaged aircraft models including component as well as structural failures. The evaluation shows that the FTFC algorithm is able to restore conventional control strategies after the aircraft configuration has changed dramatically due to these severe failures. The algorithm supports the pilot after a failure by lowering workload and allowing a safe return to the airport. For most failures, the handling qualities are shown to degrade less with a failure than the baseline classical control system does.

Real Time Damaged Aircraft Model Identification for Reconfiguring Flight Control

Abstract: This paper presents a study on the real time identification process of a damaged aircraft model. This is part of a Delft University research project which investigates the possibilities of adaptive control methods for recovering damaged aircraft operating in failure conditions. With help of a Boeing 747 simulation model supplied by the Dutch Aerospace Laboratory, including realistic failure modes with additive as well as parametric failures, it is possible to analyse the considered method’s capabilities to identify these types of damage. The types of failures included in the simulation model describe also asymmetric damage, resulting in a situation where it is impossible to base the damaged aircraft model upon the concept of decoupled longitudinal and lateral motions. The considered identification method in this study is the so-called two step method, which has been continuously under development at Delft University of Technology over the last 20 years. The two consecutive steps of this method, which are its important cornerstones, are presented: Aircraft State Estimation (ASE) and Aerodynamic Model Identification (AMI). Also two important validation tests of this method are illustrated. Furthermore, modified stepwise regression (MSWR) is introduced as a model structure development tool. Thereafter, as an application, some preliminary identification results are shown for damaged aircraft models. Future work will include further investigations on the capabilities and eventual modifications on the current status of these methods, as well as the implementation of this resulting real time damaged aircraft model in an adaptive control strategy.

Subset Selection in Regression

Abstract: 8. Subset Selection in Regression (Monographs on Statistics and Applied Probability, no. 40). By A. J. Miller. ISBN 0 412 35380 6. Chapman and Hall, London, 1990. 240 pp. £25.00.

Velocity-Free Fault-Tolerant and Uncertainty Attenuation Control for a Class of Nonlinear Systems

Abstract: This paper addresses a difficult problem of velocity-free uncertain attenuation control for a class of nonlinear systems with external disturbance and multiple actuator faults. With only the output measurement available for feedback, a sliding-mode observer (SMO) is proposed to reconstruct the full states. The reconstructed signal can approximate the true value to any accuracy. An adaptive version of the observer is further presented to handle a class of structured uncertainties in the system. Together with the system output feedback, the reconstructed state is used to synthesize a velocity-free controller. All states in the closed-loop system are guaranteed to be uniformly ultimately bounded (UUB). System uncertainty and external disturbances are attenuated. Actuator fault is accommodated. An example with application the approach to satellite attitude stabilization maneuver is presented to verify the effectiveness of the proposed scheme.