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Aerospace 2017, 4(2), 30;

Multi-Mode Electric Actuator Dynamic Modelling for Missile Fin Control

Aeromechanical Systems Group, Centre for Defence Engineering, Cranfield University, Defence Academy of the United Kingdom, Shrivenham, Swindon SN6 8LA, UK
Author to whom correspondence should be addressed.
Academic Editor: Konstantinos Kontis
Received: 31 March 2017 / Revised: 7 June 2017 / Accepted: 8 June 2017 / Published: 14 June 2017
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Linear first/second order fin direct current (DC) actuator model approximations for missile applications are currently limited to angular position and angular velocity state variables. Furthermore, existing literature with detailed DC motor models is decoupled from the application of interest: tail controller missile lateral acceleration (LATAX) performance. This paper aims to integrate a generic DC fin actuator model with dual-mode feedforward and feedback control for tail-controlled missiles in conjunction with the autopilot system design. Moreover, the characteristics of the actuator torque information in relation to the aerodynamic fin loading for given missile trim velocities are also provided. The novelty of this paper is the integration of the missile LATAX autopilot states and actuator states including the motor torque, position and angular velocity. The advantage of such an approach is the parametric analysis and suitability of the fin actuator in relation to the missile lateral acceleration dynamic behaviour. View Full-Text
Keywords: actuator; aerodynamic load torque; feedforward; compensation; missile; position control actuator; aerodynamic load torque; feedforward; compensation; missile; position control

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Gurav, B.; Economou, J.; Saddington, A.; Knowles, K. Multi-Mode Electric Actuator Dynamic Modelling for Missile Fin Control. Aerospace 2017, 4, 30.

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