Nonlinear missile autopilot design based on angle of attack normal form

DOI10.1016/S0947-3580(00)70923-XzbMath1293.93557OpenAlexW2019115295MaRDI QIDQ397606

Emmanuel Devaud, Houria B. Siguerdidjane

Publication date: 12 August 2014

Published in: European Journal of Control (Search for Journal in Brave)

Full work available at URL: https://doi.org/10.1016/s0947-3580(00)70923-x

zbMATH Keywords

trackingnonlinear systemnon-minimum phasemissile autopilot

Mathematics Subject Classification ID

Nonlinear systems in control theory (93C10) Automated systems (robots, etc.) in control theory (93C85) Linearizations (93B18)

Related Items (1)

A missile autopilot based on feedback linearization

Cites Work

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• Nonlinear control systems: An introduction
• Nonlinear control design for slightly non-minimum phase systems: Application to V/STOL aircraft
• Asymptotic output stabilization for nonlinear systems via dynamical variable-struc-ture feedback control
• Missile Autopilot Design Using a New Linear Time-Varying Control Technique
• Approximate output tracking for nonlinear non‐minimum phase systems with an application to flight control
• Bounded tracking for non-minimum phase nonlinear systems with fast zero dynamics
• Tracking nonlinear non-minimum phase systems using sliding control
• Stable inversion of nonlinear non-minimum phase systems
• Nonlinear inversion-based output tracking
• A dynamical variable structure control strategy in asymptotic output tracking problems
• Flight control design using robust dynamic inversion and time-scale separation

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