Aircraft Fault Detection, Isolation and Reconfiguration in the Presence of Measurement Errors

Ganguli, Subhabrata; Papageorgiou, George

doi:10.2514/6.2006-6551

Cited by 10 publications

(3 citation statements)

References 3 publications

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“…As such, it is also a popular control method for reconfiguring control. [12][13][14][15][16][17][18] The controller as presented in this paper builds further on previous work done at the German Aerospace Center DLR, but includes switches which allow careless switching between manual and autopilot control, as well as between rate control attitude hold (RCAH) and pure rate control. In previous manual flight control research, 17 it was observed that a rate control attitude hold setup is desirable for manual control from the perspective of handling qualities.…”

Section: Introductionmentioning

confidence: 95%

Design and flight testing of manual nonlinear flight control laws

Lombaerts

Looye

2011

AIAA Guidance, Navigation, and Control Conference

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This paper describes the design of a manual flight controller, based upon nonlinear model-based control laws. These control laws include the previously developed concept of Pseudo Control Hedging (PCH). This PCH algorithm adapts the reference model for the system output in case of unachievable commands due to control input saturation. This control algorithm has been applied in the body angular rate control loops of a high fidelity simulation model of the VFW-614 ATTAS (Advanced Technologies Testing Aircraft System) laboratory aircraft, where its beneficial influence has been illustrated. Test flights have been performed with ATTAS to evaluate the flight control technique in a relevant environment. Nomenclaturegain L; M ; N combined aerodynamic and thrust moment around the body X/Y/Z axis [Nm] N 1 fan speed [s -1 ] OS overshoot [rad] S wing area [m 2 ] V airspeed [m/s] b wingspan [m] c mean aerodynamic chord [m] g gravity constant [m/s 2 ] n x ; n y ; n z load factor along body X/Y/Z axis [-] p; q; r roll, pitch and yaw rate around the body X/Y/Z axis [rad/s] u input u b ; v b ; w b airspeed velocity components along body X/Y/Z axis [m/s] u e ; v e ; w e airspeed velocity components along earth fixed X/Y/Z axis [m/s] x; y; z position coordinates along X/Y/Z axis [m] (reference frame varies) x state vector Subscript 0 constant term A with respect to aerodynamic reference frame bwith respect to body fixed reference frame e with respect to earth fixed reference frame k with respect to kinematic reference frame a; e; r aileron, elevator and rudder c; comm commanded * Researcher,

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Section: Introductionmentioning

confidence: 95%

Design and flight testing of manual nonlinear flight control laws

Lombaerts

Looye

2011

AIAA Guidance, Navigation, and Control Conference

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“…The Fault Detection and Isolation (FDI) represents a relevant and critical theme in many sectors such as surgery [ 4 ], automotive [ 5 ], electrical engineering [ 6 ], wind turbines [ 7 ] and aerospace engineering [ 8 , 9 , 10 , 11 , 12 , 13 , 14 , 15 , 16 , 17 , 18 ]. Although aircraft subsystems are designed with sufficient levels of redundancy to tolerate both hardware and software faults, FDI algorithms are suitable to monitor the aircraft safety and assess the eventual presence of anomalies, [ 19 , 20 , 21 , 22 , 23 ].…”

Section: Introductionmentioning

confidence: 99%

“…With the goals of reducing the complexity of the FDI system, to increase its modularity and to make it distributable, the designers try to minimize the estimator dimensions. The literature presents some remarkable works dealing with the detection and the isolation of faults affecting aircraft air data such as [ 1 , 2 , 3 , 10 , 13 , 17 , 20 , 21 , 35 ] in which the detection filters are base on full order unknown input re-constructors. At the opposite, this paper focuses on the reduction of dimensions of the unisolable fault set and, thanks to the innovative combined use of the SP and the NLGA, allows for the isolation of the angle of attack faults, otherwise not possible, by means of reduced order detection filters.…”

Section: Introductionmentioning

confidence: 99%

Avionic Air Data Sensors Fault Detection and Isolation by means of Singular Perturbation and Geometric Approach

Castaldi

Mimmo

Simani

2017

Sensors

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Singular Perturbations represent an advantageous theory to deal with systems characterized by a two-time scale separation, such as the longitudinal dynamics of aircraft which are called phugoid and short period. In this work, the combination of the NonLinear Geometric Approach and the Singular Perturbations leads to an innovative Fault Detection and Isolation system dedicated to the isolation of faults affecting the air data system of a general aviation aircraft. The isolation capabilities, obtained by means of the approach proposed in this work, allow for the solution of a fault isolation problem otherwise not solvable by means of standard geometric techniques. Extensive Monte-Carlo simulations, exploiting a high fidelity aircraft simulator, show the effectiveness of the proposed Fault Detection and Isolation system.

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