Fault Tolerant Model Reference Adaptive Controller for Launch Vehicle Electromechanical Actuation System

In Small Satellite Launch Vehicle (SSLV), a Flex Nozzle Control (FNC) system, with the help of a linear actuator, is utilized to steer the launch vehicle. Electromechanical actuators (EMA) are usually preferred since they are easier to control and provides more safety. For the successful completion...

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Bibliographic Details
Published in2023 International Conference on Control, Communication and Computing (ICCC) pp. 1 - 6
Main Authors Farsana, Najma, Sebastian, Baby, Lal Priya, P. S., Kumar R, Hari
Format Conference Proceeding
LanguageEnglish
Published IEEE 19.05.2023
Subjects
Actuators
Adaptation models
Compensator
Control systems
EMA
Flexible printed circuits
FNC System
Friction
MIT Rule
MRAC
Simulation
Small satellites
Solid-Propellant Stage (SS2) regime
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Summary:In Small Satellite Launch Vehicle (SSLV), a Flex Nozzle Control (FNC) system, with the help of a linear actuator, is utilized to steer the launch vehicle. Electromechanical actuators (EMA) are usually preferred since they are easier to control and provides more safety. For the successful completion of a mission, control of EMA as well as the tolerance towards the failures are equally important. This paper proposes an algorithm to overcome the main issues faced by the system like parameter variations, disturbances and the failure of sensors. The controller used in this paper is Model Reference Adaptive Controller (MRAC), and the main advantage of the MRAC strategy is that it does not require the precise information about the fault location or amplitude. This paper also deals with the use of modified MIT rule for the design of MRAC. The efficacy of the proposed controller is verified through simulation results.
DOI:10.1109/ICCC57789.2023.10165637