Next Article in Journal
Nonlinear Model Predictive Control for Unmanned Aerial Vehicles
Previous Article in Journal
An Efficiently Parallelized High-Order Aeroacoustics Solver Using a Characteristic-Based Multi-Block Interface Treatment and Optimized Compact Finite Differencing
Article Menu

Export Article

Open AccessArticle
Aerospace 2017, 4(2), 30; doi:10.3390/aerospace4020030

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
View Full-Text   |   Download PDF [6664 KB, uploaded 14 June 2017]   |  

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. View Full-Text
Keywords: actuator; aerodynamic load torque; feedforward; compensation; missile; position control actuator; aerodynamic load torque; feedforward; compensation; missile; position control
Figures

Figure 1

This is an open access article distributed under the Creative Commons Attribution License which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited. (CC BY 4.0).

Scifeed alert for new publications

Never miss any articles matching your research from any publisher
  • Get alerts for new papers matching your research
  • Find out the new papers from selected authors
  • Updated daily for 49'000+ journals and 6000+ publishers
  • Define your Scifeed now

SciFeed Share & Cite This Article

MDPI and ACS Style

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

Show more citation formats Show less citations formats

Note that from the first issue of 2016, MDPI journals use article numbers instead of page numbers. See further details here.

Related Articles

Article Metrics

Article Access Statistics

1

Comments

[Return to top]
Aerospace EISSN 2226-4310 Published by MDPI AG, Basel, Switzerland RSS E-Mail Table of Contents Alert
Back to Top