A backstepping design for flight path angle control

Härkegård, Ola; Glad, S.T.

doi:10.1109/cdc.2000.912259

Cited by 60 publications

(68 citation statements)

References 3 publications

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“…where α 0 is the angle of attack at a steady state condition [34]. According to [34], the gains κ 1 , κ 2 , κ 3 must be chosen to satisfy…”

Section: A Nominal Back-stepping Control Lawmentioning

confidence: 99%

“…Compared with the existing schemes designed from linear models, the underlying nonlinear backstepping controller has guaranteed levels of stability and performance for a wide range of flight conditions. Furthermore, the backstepping design from [11], [34] has a simple structure and does not require exact detailed knowledge of the aircraft dynamics (e.g. the coefficient of forces and moments).…”

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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“…where α 0 is the angle of attack at a steady state condition [34]. According to [34], the gains κ 1 , κ 2 , κ 3 must be chosen to satisfy…”

Section: A Nominal Back-stepping Control Lawmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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

Alwi

Edwards

2014

IET Control Theory & Applications

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“…An additional advantage is that the controller relies on less precise model information: the designer does not need to know the size of a stabilizing nonlinearity. In [75,77,78] this notion is used to design a robust nonlinear controller for a fighter aircraft model. Other examples of backstepping control designs where the cancellation of useful nonlinearities is avoided can be found in [116,118].…”

Section: Introductionmentioning

confidence: 99%

Adaptive Backstepping Flight Control for Modern Fighter Aircraft

Sonneveldt¹

2011

Advances in Flight Control Systems

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“…Also, any control methodology proposed for transportation aircraft should enable people to safely fly without requiring increased workload from the pilots. In this context, nonlinear adaptive control could be a promising way to design improved solutions to this problem since these techniques try to compensate for modeling inaccuracies and external disturbances; this is why many studies [1], [2], [4], [5], [6], [7], [8], [9], [10], [11]- [12] have been performed in this field.…”

Section: Introductionmentioning

confidence: 99%