Model Predictive Control in Aerospace Systems: Current State and Opportunities

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Aircraft Fault-Tolerant Trajectory Control Using Incremental Nonlinear Dynamic Inversion

This paper presents a fault-tolerant aircraft control (FTAC) scheme against actuator faults. First, the upper bounds of the norms of the unknown functions are introduced, which contain actuator faults and model uncertainties. Subsequently, self-constructing fuzzy neural networks (SCFNNs) with adaptive laws are capable of obtaining the bounds. The bound estimation can reduce the computational burden with a lower amount of rules and weights, rather than the dynamic matrix approximation. Moreover, with the aid of SCFNNs, a multivariable sliding mode control (SMC) is developed to guarantee the finite-time stability of the handicapped aircraft. As compared to the existing intelligent FTAC techniques, the proposed method has twofold merits: fault accommodation can be promptly accomplished and decoupled difficulties can be overcome. Finally, simulation results from the nonlinear longitudinal Boeing 747 aircraft model illustrate the capability of the presented FTAC scheme.

/pdf/fault-tolerant-aircraft-control-based-on-self-constructing-zepvauirj4.pdf

Fault-Tolerant Aircraft Control Based on Self-Constructing Fuzzy Neural Networks and Multivariable SMC Under Actuator Faults

A resilient control system is expected to have the capacity to restore the desired system stability and tracking performance in the presence of uncertain system faults such as actuator failures. While redundant actuators are used for actuator failure accommodation, uncertain actuator failures, whose failure time, pattern, and values may be unknown, can bring new challenges to feedback control design as such uncertain failures can introduce large structural, parametric, and actuation uncertainties. Two technical issues are associated with using redundant actuators: how redundant actuators should be coordinated for effective failure compensation control, and how a feedback control law should be adaptively designed to compensate uncertain actuator failures. In this paper, we present a tutorial on direct adaptive failure compensation-based solutions to these issues for different types of control systems: state tracking using state feedback, output tracking using state feedback or output feedback, for linear, ...

Direct adaptive actuator failure compensation control: a tutorial

Adaptive disturbance observer‐based finite‐time continuous fault‐tolerant control for reentry RLV

Flight testing of a rate saturation compensation scheme on the ATTAS aircraft

This work presents a novel method of fault-tolerant model predictive control where the response of a reference closed-loop model is followed even in the presence of an actuator fault. This architecture is capable of redistributing the control efforts among healthy actuators in a stable manner, respecting their limitations. Also, a constrained guidance system that works in conjunction with the inner-loop fault-tolerant controller is proposed. The guidance law considers the calculated limitations of the inner-loop control system as input constraints in order to smooth the transition between two consecutive navigation legs defined by waypoints. A trajectory-tracking system composed of the constrained guidance and the fault-tolerant model predictive controller is demonstrated through numerical simulations and experimental results on an experimental midsize transport aircraft, showing adequate performance.

Fault-Tolerant Model Predictive Control with Flight-Test Results

This work presents a fault-tolerant flight control system using model predictive control (MPC). The proposed technique, named feasible target-tracking MPC, filters the reference demand to guarantee feasibility of the constrained optimization. This architecture is also capable of redistributing, in a stable manner, the control efforts among healthy actuators, respecting their limitations. A trajectory tracking system based on the proposed fault-tolerant model predictive controller is demonstrated using the ground simulator of the VFW-614 ATTAS (Advanced Technologies Testing Aircraft System), showing feasibility and adequate performance.

http://www.cta-dlr2009.ita.br/Proceedings/PDF/58838.pdf

Dirk Leißling

Papers

Flight testing of a rate saturation compensation scheme on the ATTAS aircraft

Fault-Tolerant Model Predictive Control with Flight-Test Results

Fault-Tolerant Flight Control System using Model Predictive Control

Fault-Tolerant Model Predictive Control with Flight-Test Results