Nonlinear Missile Autopilot Design Based on Angle of Attack Normal Form

Siguerdidjane, Houria; Devaud, Emmanuel

doi:10.1016/s0947-3580(00)70923-x

Cited by 9 publications

(4 citation statements)

References 13 publications

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“…Indeed, it is shown in [4] that the NMP phenomenon may be circumvented through the angle of attack normal form loop. In doing so, that makes possible the missile centre of mass tracking some desired trajectories and in addition the system meet the performance specifications.…”

Section: B Missile Nonlinear Dynamic Feedback Controllermentioning

confidence: 99%

“…The asymptotic output tracking based approach is becoming a quite interesting tool in the design of static or dynamic feedback control [16]. For the reader convenience, let us recall the calculations which lead to the commanded tail fin deflection dynamic feedback [4]. For sake of clarity, some arguments in equations have been omitted.…”

Section: B Missile Nonlinear Dynamic Feedback Controllermentioning

confidence: 99%

“…More recently, some approaches based on modern control theory have been proposed and a few lines of research investigated. Different approaches have been considered, and the main line of attack to the problem seems to be the feedback linearization, despite the difficulties which may occur when dealing with NMP systems [3], [4]. In order to overcome the NMP phenomenon, some authors proposed to drop from the missile model the terms which give rise to the NMP response.…”

Section: Introductionmentioning

confidence: 99%

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Nonsmooth optimization for nonlinear missile autopilot: Improvement under time domain constraints

Lassami

Font

Siguerdidjane

2006

2006 IEEE Conference on Computer Aided Control System Design, 2006 IEEE International Conference on Control Applications, 2006

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In this paper, a new parametric optimization approach to retune nonlinear controllers is proposed. It discusses the design of these controllers under temporal constraints. The formulated optimization problem is often complex; it involves nonsmooth design parameters and criteria. An efficient optimization algorithm based on the approximation of the epsilon subdifferential notion is presented. It only requires gradients which are computed using parametric sensitivity functions. The proposed approach is applied to tune a nonlinear missile autopilot. The purpose especially concerns how to appropriately apply our procedure in order to improve performance of a controlled nonlinear dynamic system. We show that the choice of the controller structure and parameters has a great effect on the validation of the temporal specifications. Simulation results are given to demonstrate the effectiveness of the proposed approach.

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Section: B Missile Nonlinear Dynamic Feedback Controllermentioning

confidence: 99%

Section: B Missile Nonlinear Dynamic Feedback Controllermentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Nonsmooth optimization for nonlinear missile autopilot: Improvement under time domain constraints

Lassami

Font

Siguerdidjane

2006

2006 IEEE Conference on Computer Aided Control System Design, 2006 IEEE International Conference on Control Applications, 2006

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“…The study described in this article can be seen as a continuation of the design result carried out by Siguerdidjane [11,12]. In reference [11], angle of attack is assumed as the known value, which is perfect, and applied the asymptotic output tracking control approach for angle of attack control. In this article, we introduce the estimator of angle of attack for application of real missile system and apply the different controller design method for inner loop control.…”

Section: Introductionmentioning

confidence: 99%

Missile acceleration controller design using proportional–integral and non-linear dynamic control design method

Kim

Tahk

2011

Proceedings of the Institution of Mechanical Engineers, Part G:

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In this article, a method to make the normal acceleration of medium angle of attack missile to track some desired trajectories is presented. The dynamics which describe a missile acceleration are known to be non-minimum phase, which makes it difficult to use a straightforward feedback linearization technique. This article aims at showing that this problem may be overcome by employing cascaded regulations in the non-linear area. First, inner loop controller by dynamical sliding mode control (SMC) method based on asymptotic output tracking is designed for angle of attack control which has a minimum phase characteristics. Also then, the problem that is addressed here is the completion of the global loop by designing an additional outer loop proportional–integral (PI) controller and angle of attack estimator. The performance and stability of proposed method are illustrated via computer simulations.

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