Flight Control Reconfiguration Based on Online Physical Model Identification and Nonlinear Dynamic Inversion

Lombaerts, Thomas; Chu, Ping; Mulder, J.A.

doi:10.1007/978-3-642-11690-2_13

Cited by 12 publications

(8 citation statements)

References 12 publications

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“…As described in Lombaerts et al [11], a post-failure safe flight envelope analysis suggests that a safe roll manoeuvre can only be achieved for demand values less than 20 • . However, it can be argued that based on the current controller implemented in the B747, the roll reference from the autopilot is limited for passenger comfort, and especially for LOC turning manoeuvres during the final stages of all ILS landings.…”

Section: A Ils Landingmentioning

confidence: 94%

Evaluation of a Sliding Mode Fault-Tolerant Controller for the El Al Incident

Alwi¹,

Edwards²,

Stroosma³

et al. 2010

Journal of Guidance, Control, and Dynamics

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This paper presents piloted flight simulator results associated with the EL-AL flight 1862 scenario using a model reference-based sliding mode control allocation scheme for fault tolerant control. The proposed controller design was carried out without any knowledge of the type of failure, and in the absence of any fault detection and isolation strategy. This is motivated by the fact that the flight crew were unaware of the loss of the right engines. For this reason, the control allocation scheme which is proposed uses (fixed) equal distribution of the control signals to all actuators (for both nominal situations and when a fault or failure occurs). The paper analyzes the scheme and determines the conditions under which closed-loop stability is retained. The results represent the successful real-time implementation of the proposed controller on the SIMONA motion flight simulator configured to represent a B747 aircraft. The evaluation results from the experienced pilots show that the proposed controller has the ability to position the aircraft for landing in both a nominal and the EL-AL failure scenario. It is also shown that actuator faults and failures which occured during the EL-AL incident can be handled directly without reconfiguring the controller.

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Section: A Ils Landingmentioning

confidence: 94%

Evaluation of a Sliding Mode Fault-Tolerant Controller for the El Al Incident

Alwi¹,

Edwards²,

Stroosma³

et al. 2010

Journal of Guidance, Control, and Dynamics

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show abstract

“…Conversely the vector g s (x) is associated with the secondary control surface (the stabilizer) [42] which will be used when faults/failures occur on the primary control Remark 1: Note that the term dCm dδe is assumed to be available either by online parameter estimation (e.g. [14]) or from a lookup table. In this paper the information is obtained from a lookup table based on [37].…”

Section: A Strict Feedback Formmentioning

confidence: 99%

“…Here the control allocation matrix is very bespoke and utilizes the specific aircraft equation of motion -especially the strict feedback form in (14).…”

Section: B Control Allocationmentioning

confidence: 99%

“…nonlinear dynamic inversion [10], backstepping [11], neural networks [12], sliding mode [13]). Some of these methods have attracted the attention of industry and have been further tested and evaluated in order to assess their potential for future applications and implementations on aircraft (see for example the European study on state-of-the-art FTC by the GARTEUR AG-16 group [14] and the recent ADDSAFE project [15]). However many of these proposed FTC schemes are based on linear plant representations and are therefore only valid in the vicinity of the designed trim point.…”

Section: Introductionmentioning

confidence: 99%

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Fault tolerant longitudinal aircraft control using non‐linear integral sliding mode

Alwi

Edwards

2014

IET Control Theory & Applications

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This paper proposes a novel nonlinear fault tolerant scheme for longitudinal control of an aircraft system, comprising an integral sliding mode control allocation scheme and a backstepping structure. In fault free conditions, the closed loop system is governed by the backstepping controller and the integral sliding mode control allocation scheme only influences the performance if faults/failures occur in the primary control surfaces. In this situation the allocation scheme redistributes the control signals to the secondary control surfaces and the scheme is able to tolerate total failures in the primary actuator. A backstepping scheme taken from the existing literature is designed for flight path angle tracking (based on the nonlinear equations of motion) and this is used as the underlying baseline controller in nominal conditions. The efficacy of the scheme is demonstrated using a high fidelity aircraft benchmark model. Excellent results are obtained in the presence of plant/model uncertainty in both fault-free and faulty conditions.

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“…al. 13,39,40 In contrast with current methods, the aerodynamic model structure selection procedure for multivariate simplex spline based models is rather straightforward.…”

Section: Aerodynamic Model Structure Selectionmentioning

confidence: 99%

A Multidimensional Spline-Based Global Nonlinear Aerodynamic Model for the Cessna Citation II

Visser

Mulder

Chu

2010

AIAA Atmospheric Flight Mechanics Conference

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A new method is proposed for the identification of global nonlinear models of aircraft non-dimensional force and moment coefficients. The method is based on a recent type of multivariate spline, the multivariate simplex spline, which can accurately approximate very large, scattered nonlinear datasets in any number of dimensions. The new identification method is used to identify a global nonlinear aerodynamic model of high dimensionality for the Cessna Citation II laboratory aircraft operated by the Delft University of Technology and the Netherlands National Aerospace Laboratory. The data used in the identification process consisted of millions of measurements and was accumulated during more than 250 flight test maneuvers with the laboratory aircraft. The resulting models for the aerodynamic force and moment coefficients are continuous analytical functions as they consist of sets of piecewise defined, multivariate polynomials. The identified models were validated using a subset of the flight data, with validation results showing a very close match between model and reality.

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Flight Control Reconfiguration Based on Online Physical Model Identification and Nonlinear Dynamic Inversion

Cited by 12 publications

References 12 publications

Evaluation of a Sliding Mode Fault-Tolerant Controller for the El Al Incident

Evaluation of a Sliding Mode Fault-Tolerant Controller for the El Al Incident

Fault tolerant longitudinal aircraft control using non‐linear integral sliding mode

A Multidimensional Spline-Based Global Nonlinear Aerodynamic Model for the Cessna Citation II

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