Robust gain-scheduled autopilot design with anti-windup compensation for a guided projectile

This article deals with the control design of a dual-spin projectile concept, characterized by highly nonlinear parameter-dependent and coupled dynamics, and subject to uncertainties and actuator saturations. An open-loop nonlinear model stemming from flight mechanics is first developed. It is subse...

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Vydané v:CEAS aeronautical journal Ročník 14; číslo 3; s. 765 - 786
Hlavní autori: Thai, Sovanna, Theodoulis, Spilios, Roos, Clément, Biannic, Jean-Marc
Médium: Journal Article
Jazyk:English
Vydavateľské údaje: Vienna Springer Vienna 01.07.2023
Springer Nature B.V
Springer
Predmet:
Actuators
Aerospace Technology and Astronautics
Antiwindup compensators
Automatic pilots
Engineering
Engineering Sciences
Flight
Flight mechanics
H-infinity control
Nonlinear systems
Nonlinearity
Original Paper
Parameters
Physics
Pitch (inclination)
Projectiles
Rolling motion
Uncertainty
Yaw
Guided projectiles
Gain scheduling
Robustness analysis
Anti-windup
ANTI-WINDUP DESIGN
synthèse anti-windup
mu-analyse
commande robuste
MU-ANALYSIS
GUIDED PROJECTILE
IQC
projectile guidé
ROBUST CONTROL
ISSN:1869-5582, 1869-5590
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Popis
Shrnutí:This article deals with the control design of a dual-spin projectile concept, characterized by highly nonlinear parameter-dependent and coupled dynamics, and subject to uncertainties and actuator saturations. An open-loop nonlinear model stemming from flight mechanics is first developed. It is subsequently linearized and decomposed into a linear parameter-varying system for the roll channel, and a quasi-linear parameter-varying system for the pitch/yaw channels. The obtained models are then used to design gain-scheduled H ∞ baseline autopilots, which do not take the saturations into account. As a major contribution of this paper, the saturation nonlinearities are addressed in a second step through anti-windup augmentation. Three anti-windup schemes are proposed, which are evaluated and compared through time-domain simulations and integral quadratic constraints analysis. Finally, complete guided flight scenarios involving a wind disturbance, perturbed launch conditions, or aerodynamic uncertainties, are analyzed by means of nonlinear Monte Carlo simulations to evaluate the improvements brought by the proposed anti-windup compensators.
Bibliografia:ObjectType-Article-1
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content type line 14
ISSN:1869-5582
1869-5590
DOI:10.1007/s13272-023-00668-9