A Robust Adaptive Nonlinear Control Approach to Missile Autopilot Design

Kim, Seunghwan; Song, Chanho

doi:10.1016/s1474-6670(17)41057-3

Cited by 11 publications

(16 citation statements)

References 2 publications

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“…A second order nonlinear model of a generic surface-to-air missile has been obtained from [109]. The model is nonlinear, but not overly complex.…”

Section: Example: Longitudinal Missile Controlmentioning

confidence: 99%

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Adaptive Backstepping Flight Control for Modern Fighter Aircraft

Sonneveldt¹

2011

Advances in Flight Control Systems

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“…A second order nonlinear model of a generic surface-to-air missile has been obtained from [109]. The model is nonlinear, but not overly complex.…”

Section: Example: Longitudinal Missile Controlmentioning

confidence: 99%

“…There is plenty of literature available on adaptive backstepping designs for the control of aircraft and missiles; see e.g. [58,61,76,109,176,183]. However, most of these designs consider control of the aerodynamic angles µ, α and β or the angular rates.…”

Section: 3mentioning

confidence: 99%

Adaptive Backstepping Flight Control for Modern Fighter Aircraft

Sonneveldt¹

2011

Advances in Flight Control Systems

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“…Flight control has long been a privileged applicative field for robust and gain-scheduling control, see, eg, previous works [1][2][3][4][5][6] and more recently, for fault-tolerant and adaptive control. [7][8][9][10][11][12][13][14][15][16][17][18][19][20][21][22] Noting that strong links exist between all these fields. Indeed, robust and adaptive control can be seen as competing/complementary techniques for solving the same problem of controlling an uncertain plant.…”

Section: Introductionmentioning

confidence: 99%

“…24 Nevertheless, a physical aerodynamic state-space model is available for an aircraft (A/C), and state-space methods are typically used to design robust or gain-scheduled flight control laws so that adaptive flight controllers are usually designed using state-space methods, see, eg, previous works. 8,[10][11][12][13][14][15][16][18][19][20][21][22] Generally speaking, 2 main problems need to be solved in adaptive control, namely, to obtain a priori guaranteed stability and performance properties of the adaptive closed loop and to decrease the online computational time and complexity. In the context of indirect adaptive control, following the works of Ferreres and Antoinette, 25,26 a solution based on robust and gain-scheduled control tools is to design off-line a gain-scheduled controller, depending on the plant parameters to be estimated, to avoid the complexity of implementing a control design algorithm online.…”

Section: Introductionmentioning

confidence: 99%

Adaptive LFT control of a civil aircraft with online frequency‐domain parameter estimation

Ferreres

Hardier²

2017

Intl J Robust & Nonlinear

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Summary This paper describes the application of an indirect linear fractional transformation (LFT)–based state‐space adaptive control scheme to a transport aircraft, within the context of the European project REconfiguration of CONtrol in Flight for Integral Global Upset REcovery. The principle of the scheme is to design and validate off‐line a gain‐scheduled controller, depending on the plant parameters to be estimated, and to combine it online with a model estimator, so as to minimize the onboard computational time and complexity. A modal approach, very classical for the design of a flight control law, is used to directly synthesize the static output feedback LFT controller, depending on the control and stability derivatives, ie, the parameters of the linearized aerodynamic state‐space model to be estimated. Since the gain‐scheduled LFT controller online depends on the parameter estimates instead of the true values, its robustness to transient and asymptotic estimation errors needs to be assessed using μ and integral quadratic constraint analysis techniques. A primary concern being an online implementation, a fully recursive frequency‐domain estimation technique is proposed, with a low online computational burden and the capability to track time‐varying parameters. Full nonlinear simulations along a trajectory validate the good performance properties of the combined estimator and gain‐scheduled flight controller. To some extent, minimal guaranteed stability and performance properties of the adaptive scheme can be ensured by switching to a robust controller when the parameter estimates are not reliable enough, thus bypassing the Certainty Equivalence Principle.

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“…In [8], the authors designed a new robust autopilot based on predictive functional control (PFC) to deal with the high nonlinearity of agile missiles while considering the control constraints. A new backstepping autopilot, which guarantees the uniform ultimate boundness, has also been proposed [9]. In [10], the extended observer is utilized to increase the robustness of the input-output linearization adaptive output feedback control http://ijass.org [11,12] adaptive control is that it allows fast adaptation without losing robustness.…”

Section: Introductionmentioning

confidence: 99%

Missile two-loop acceleration autopilot design based on 𝓛₁adaptive output feedback control

He¹,

Lin²

2014

International Journal of Aeronautical and Space Sciences

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This article documents the design of a novel two-loop acceleration autopilot based on 1 L adaptive output feedback control for tail-controlled missiles. The inner loop is an adaptive angle-of-attack tracking loop and the outer loop is the traditional PI controller for error compensation. A systematic low-pass filter design procedure is provided for minimum phase system and is applied to the inner loop design while the parameters of the outer loop are obtained from the multi-objective optimization problem. The effectiveness of the proposed autopilot is verified through numerical simulations under various conditions. Key words: 1 L adaptive output feedback control, Autopilot, low-pass filter IntroductionDue to the wide parameter variation and stringent performance requirements, missile autopilot design is a challenging task. The traditional method of guaranteeing stability in the presence of aerodynamic parameter variation or uncertainty is the gain scheduling control strategy. Modern air-to- IntroductionDue to the wide parameter variation and stringent performance requirements, missile autopilot design is a challenging task. The traditional method of guaranteeing stability in the presence of aerodynamic parameter variation or uncertainty is the gain scheduling control strategy. Modern air-to- adaptive output feedback control for tail-controlled missiles. The inner loop is an adaptive angle-of-attack tracking loop and the outer loop is the traditional PI controller for error compensation. A systematic low-pass filter design procedure is provided for minimum phase system and is applied to the inner loop design while the parameters of the outer loop are obtained from the multi-objective optimization problem. The effectiveness of the proposed autopilot is verified through numerical simulations under various conditions. adaptive output feedback control, Autopilot, low-pass filter

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A Robust Adaptive Nonlinear Control Approach to Missile Autopilot Design

Cited by 11 publications

References 2 publications

Adaptive Backstepping Flight Control for Modern Fighter Aircraft

Adaptive Backstepping Flight Control for Modern Fighter Aircraft

Adaptive LFT control of a civil aircraft with online frequency‐domain parameter estimation

Missile two-loop acceleration autopilot design based on 𝓛₁adaptive output feedback control

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A Robust Adaptive Nonlinear Control Approach to Missile Autopilot Design

Cited by 11 publications

References 2 publications

Adaptive Backstepping Flight Control for Modern Fighter Aircraft

Adaptive Backstepping Flight Control for Modern Fighter Aircraft

Adaptive LFT control of a civil aircraft with online frequency‐domain parameter estimation

Missile two-loop acceleration autopilot design based on 𝓛1adaptive output feedback control

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Product

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Missile two-loop acceleration autopilot design based on 𝓛₁adaptive output feedback control