Research On Gas Flow Regulation Technology Of Ducted Rockets

Combined the advantages of ramjet and rocket engine, ducted rocket is the bestengine choice for all kinds of future missiles. In the key technologies of thedevelopment of ducted rocket, the control of gas generator technology is the focus ofthe current national study. This paper focuses on the control of gas generator technologyof the ducted rocket, and the research work carried out based on it.Firstly, the composition of the gas flow regulating system and gas flow regulationprinciple was analyzed. The plunger spool-type gas flow regulating system is designed.Around the gas flow control system, the flow control valve layout and operatingprinciple was analyzed; The valve body materials and sealing materials was selected;The major components of the flow regulating valve was analyzed.Secondly, the dynamic response of the gas flow regulation system was studied. adynamic model based on the plunger spool-type was establishment, the dynamiccharacteristics of the gas flow regulation system was analyzed based on theoreticalanalysis and simulation analysis. The gas generator free volume, valve actuation speed,gas generator throat area, and other factors that affect the dynamic characteristics of thegas flow regulation system was analyzed.Then, the model of the gas flow control system was established, the designrequirement of the controller was proposed. The PID controller for gas flow Controlsystem was designed based on Classical control theory, the control of the system wassimulated and analyzed. For practical, the gas flow regulator complexity of the system,the impact of varying parameters on the system was analyzed.Finally, the variable flow ducted rocket model was established, the performancecomputing model of the variable flow ducted rocket was designed, and the engineperformance was calculated. In the gas generator nozzle throat area of the adjustmentprocess, the velocity characteristics and height characteristics of the variable flowducted rocket fuel ratio, thrust and specific impulse was analyzed.