Performance Analysis of a Ducted Rocket Under Various Flight Conditions

A ducted rocket has superior maneuverability compared to an air-breathing engine and a higher terminal speed than a solid motor. A mathematical performance model for a ducted rocket is proposed based on its operating conditions. The physical model of concern includes the entire ducted rocket flow path, extending from the leading edge of the intake to the exhaust nozzle, which is validated with previous research results. Performance analysis is conducted by applying various flight conditions such as flight Mach number and altitude, angle of attack, roll angle, and air–fuel (AF) ratio. The stable flight envelope is presented by applying four operating limits such as AF ratio, choking conditions, pressure of gas generator, and inlet temperature. Finally, the sensitivity of design parameters on the performance of a ducted rocket is analyzed and discussed through the scatter plot method.