Abstract
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.
Highlights
Previous research has mainly focused on the system performance by comparing the commanded and the actual deflection of the missile fin
This paper aims to integrate a direct-drive actuator with the missile fin dual feedforward/feedback model and relate this to the missile airframe state variables
This paper aims to demonstrate the effectiveness of numerical simulation for missile actuator systems in relation to the autopilot control design
Summary
Previous research has mainly focused on the system performance by comparing the commanded and the actual deflection of the missile fin (angular position). There is a simplified assumption that the actuator supplies instantly the required load torque to the fin to hold it in its position under the given aerodynamic flow conditions. In this paper, the missile fin is driven from a direct-drive actuator without a gearbox. The holding torque at different fin angular positions must be supplied from the actuator alone. The load torque cannot be provided instantaneously from the actuator and the current is modelled to allow a better understanding of the missile lateral acceleration (LATAX) characteristics in relation to the fin actuator electrical characteristics. This paper aims to integrate a direct-drive actuator with the missile fin dual feedforward/feedback model and relate this to the missile airframe state variables
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