INTEGRATED CONTROLLER FOR DIVERT THRUSTER FLIGHT PROPULSION CONTROL SYSTEMS

摘要

Future generation missile calls for development o f fast response propulsion based control systems to achieve hit-to-kill miss distance against highly manoeuvrable targets covering high-enclo to exo-atmosphere regions.Control systems based on solid propulsion are developed connecting multiple pintle nozzles and control thrust vector is generated with distribution hot gasses in pitch/yaw directions.Differential distribution of hot gasses among multiple nozzles is complex due to time varying coupled non-linear chamber pressure dynamics with propellant combustion and nozzlesy flow phenomena and methods based on linear control may not ensure stability in wide operating conditions.There is need to develop "Unified Controller" based on non-linecir formulation to ensure control stability in wide operating conditions of various mission applications,with advanced features for new generation missiles to counter various futuristic targets,and achieve hit-to-kill capabilities following integrated approach in order to improve the total system performance.