Robust gain-scheduled autopilot design for spin-stabilized projectiles with a course-correction fuze

This article explores the design of a pitch/yaw axis load factor autopilot for a class of 155-mm spin-stabilized ammunition which incorporates a novel nose-positioned course correction fuze system used for trajectory correction. The projectile full nonlinear model is discussed and a procedure for ob...

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Bibliographic Details
Published in:Aerospace science and technology Vol. 42; pp. 477 - 489
Main Authors: Theodoulis, Spilios, Sève, Florian, Wernert, Philippe
Format: Journal Article
Language:English
Published: Elsevier Masson SAS 01.04.2015
Elsevier
Subjects:
Actuators
Automatic
Automatic pilots
Autopilot design
Design engineering
Engineering Sciences
Flight mechanics
Gain-scheduling
Guided projectiles
Loads (forces)
LPV systems
Nonlinearity
Projectiles
Robust control
Stability
Trajectories
Robust control
Autopilot design
LPV systems
Guided projectiles
Gain-scheduling
Flight mechanics
ISSN:1270-9638, 1626-3219
Online Access:Get full text
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Summary:This article explores the design of a pitch/yaw axis load factor autopilot for a class of 155-mm spin-stabilized ammunition which incorporates a novel nose-positioned course correction fuze system used for trajectory correction. The projectile full nonlinear model is discussed and a procedure for obtaining the system q-LPV model necessary for control synthesis is exposed. Important properties relevant to axis cross-coupling, internal modes and stability properties specific to this kind of system are also highlighted. A comparison of full- and reduced-order mixed-sensitivity H∞ linear compensators with an additional model following constraint for the design of the projectile autopilot is presented. Robust stability with respect to aerodynamic and actuator/sensor modeling uncertainties is verified via standard μ-analysis tools throughout the projectile flight envelope. Nonlinear 7-DoF trajectory simulation results are finally presented for a single or dual control surface actuator configuration.
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ISSN:1270-9638
1626-3219
DOI:10.1016/j.ast.2014.12.027