Linear Paramater-Varying Detection Filter Design for a Boeing 747-100/200 Aircraft

Szászi, István; Marcos, Andrés; Balas, Gary J.; Bokor, József

doi:10.2514/1.6689

Cited by 72 publications

(59 citation statements)

References 21 publications

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“…The nonlinear longitudinal dynamics are documented in Refs. [21], [22]. In this paper, the flight envelope for the longitudinal dynamics is defined as α ∈ [−2 10](deg) and V ∈ [100 250] (m/sec) at an altitude of 7000 m. Aerodynamic coefficients and their derivatives are fit into a polynomial function form such that…”

Section: B Longitudinal Dynamics Of a Transport Aircraftmentioning

confidence: 99%

Robust Gain-Scheduled Fault Tolerant Control For A Transport Aircraft

Shin

Gregory

2007

2007 IEEE International Conference on Control Applications

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Abstract-This paper presents an application of robust gainscheduled control concepts using a linear parameter-varying (LPV) control synthesis method to design fault tolerant controllers for a civil transport aircraft. To apply the robust LPV control synthesis method, the nonlinear dynamics must be represented by an LPV model, which is developed using the function substitution method over the entire flight envelope. The developed LPV model associated with the aerodynamic coefficient uncertainties represents nonlinear dynamics including those outside the equilibrium manifold. Passive and active fault tolerant controllers (FTC) are designed for the longitudinal dynamics of the Boeing 747-100/200 aircraft in the presence of elevator failure. Both FTC laws are evaluated in the full nonlinear aircraft simulation in the presence of the elevator fault and the results are compared to show "pros" and "cons" of each control law.

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Section: B Longitudinal Dynamics Of a Transport Aircraftmentioning

confidence: 99%

Robust Gain-Scheduled Fault Tolerant Control For A Transport Aircraft

Shin

Gregory

2007

2007 IEEE International Conference on Control Applications

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“…There has been significant research in these areas in the last decade in order to exploit the convenience of extending LTI design methods to achieve performance and stability guarantees. A significant portion of this research has been directed towards FDI (see for examples [7], [9], [10], [11], [21], [22], [34], [41], [37]). …”

Section: Introductionmentioning

confidence: 99%

Robust fault reconstruction for linear parameter varying systems using sliding mode observers

Alwi

Edwards

2013

Intl J Robust & Nonlinear

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This paper presents a robust FDI scheme using a sliding mode observer based on an LPV system, with fault reconstruction capability. Both actuator and sensor fault reconstruction schemes are considered which possess robustness against a certain class of uncertainty and corrupted measurements. For actuator fault reconstruction, the input distribution matrix (associated with the actuators being monitored) is factorized into fixed and varying components. LMIs are used to design the key observer parameters in order to minimize the effect of uncertainty and measurement corruption on the fault reconstruction signal. The faults are reconstructed using the output error injection signal associated with the nonlinear term of the sliding mode observer. For sensor fault reconstruction, the idea is to re-formulate the problem into an actuator fault reconstruction scenario so that the same design procedure can be applied. This is achieved by augmenting the original system with the filtered sensors being monitored. Simulations using a full nonlinear model of a large transport aircraft are presented, and show good fault reconstruction performance.

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“…[13], the IFTC system of the aircraft is designed, which includes a fault tolerant control (FTC) law and fault detection and isolation (FDI) filters. In Ref.…”

Section: Introductionmentioning

confidence: 99%

“…In Ref. [13], the FTC law is designed as a H ∞ control law to minimize command tracking errors under actuator fault occurrence and the FDI filter is designed based on an affine LPV model of the Boeing 747 aircraft to generate residual signals using the geometric approach [14]. Since the FDI filter is designed based on the open-loop dynamics, the closed-loop evaluation is required before implementing it.…”

Section: Introductionmentioning

confidence: 99%

“…Since the FDI filter is designed based on the open-loop dynamics, the closed-loop evaluation is required before implementing it. For the closed-loop evaluation over the entire flight envelope, an LFT model from the nonlinear dynamics model of the Boeing 747-100/200 aircraft [13] is developed in this paper. The variation of the nonlinear aircraft dynamics over the flight envelope are captured by the LFT model with the ∆ block, which contains key parameters such as angle of attack and velocity.…”

Section: Introductionmentioning

confidence: 99%

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Closed-Loop Evaluation of An Integrated Failure Identification and Fault Tolerant Control System for A Transport Aircraft

Shin

Belcastro

Khong

2006

AIAA Guidance, Navigation, and Control Conference and Exhibit

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Formal robustness analysis of aircraft control upset prevention and recovery systems could play an important role in their validation and ultimate certification. Such systems developed for failure detection, identification, and reconfiguration, as well as upset recovery, need to be evaluated over broad regions of the flight envelope or under extreme flight conditions, and should include various sources of uncertainty. To apply formal robustness analysis, formulation of linear fractional transformation (LFT) models of complex parameter-dependent systems is required, which represent system uncertainty due to parameter uncertainty and actuator faults. This paper describes a detailed LFT model formulation procedure from the nonlinear model of a transport aircraft by using a preliminary LFT modeling software tool developed at the NASA Langley Research Center, which utilizes a matrix-based computational approach. The closed-loop system is evaluated over the entire flight envelope based on the generated LFT model which can cover nonlinear dynamics. The robustness analysis results of the closed-loop fault tolerant control system of a transport aircraft are presented. A reliable flight envelope (safe flight regime) is also calculated from the robust performance analysis results, over which the closed-loop system can achieve the desired performance of command tracking and failure detection. * Senior Staff Scientist, Robust and Adaptive Control, AIAA Member, email:shinjy@nianet.org.† Senior Researcher, Dynamic Systems and Control Branch, AIAA Member. ‡ Researcher, Dynamic Systems and Control Branch, AIAA Member.

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Linear Paramater-Varying Detection Filter Design for a Boeing 747-100/200 Aircraft

Cited by 72 publications

References 21 publications

Robust Gain-Scheduled Fault Tolerant Control For A Transport Aircraft

Robust Gain-Scheduled Fault Tolerant Control For A Transport Aircraft

Robust fault reconstruction for linear parameter varying systems using sliding mode observers

Closed-Loop Evaluation of An Integrated Failure Identification and Fault Tolerant Control System for A Transport Aircraft

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