Author : Lini M.Thomas 1
Date of Publication :7th December 2015
Abstract: In a launch vehicle the Electro-Mechanical Actuation (EMA) system gimbals the rocket nozzle and provides accurate steering of the vehicle. The adequate amount of force or thrust at the gimbal point is obtained by the small rotation of the gimbal. The force generated from the EMA system stabilizes and steers the launch vehicle in the required direction in to overcome the wind-gust disturbances and balance the aerodynamic movements. The mathematical model of the linear actuator is considered for the servo system design. In this paper the servo design of the actuation system is carried out for the launch vehicle application. The servo system integrates actuators, sensors and embedded intelligent systems for control, optimization and supervision which aim in improving the performance of the system. Due to high reliability demands of such systems, accurate supervision and fault diagnosis concepts are of particular importance.
Reference :
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[1] Suchitra P, Priya C Kurian, and Rini Jones S B, “Optimal Controller based Servo System Design for the Thrust Vector Control of liquid propellant engine of three Stage Launch Vehicle”, International Conference on Magnetics, Machines & Drives (AICERA-2014 iCMMD).
[2] Baby Sebastian, Beena M Varghese, “Servo Design of Electromechanical Actuator based system for Launch Vehicle applications”, International Journal of Advanced Research in Electrical, Electronics and Instrumentation Engineering Vol. 2, Issue 5, May 2013.
[3] Ivana Todić, Marko Miloš, Mirko Pavišić, “Position and speed control of Electromechanical actuator for Aerospace applications”, Technical Gazette 20, 5(2013), 853-860.
[4] M. Jayakumar and Bijan B Das, “Fault Detection, Isolation And Reconfiguration In Presence Of Incipient Sensor Faults In An Electromechanical Flight Control Actuator System”, Vikram Sarabhai Space Centre, Indian Space Research Organization, Thiruvananthapuram, Kerala695022, IEEE conference 2013.