Test and Evaluation of a Fluidic Thruster for Roll Control of Air Breathing Missiles

摘要

A fluidic thruster designed for roll control of an air-breathing missile has been tested and evaluated. Since, for this particular application, the thruster receives its supply air from the engine air inlet duct, the thruster evaluation consisted of determining how efficiently the thruster diverts the high-energy air and exhausts it supersonically into the ambient atmosphere to generate the required roll control reaction forces. It is concluded that an array of four appropriately sized thrusters equally spaced about the diameter of a missile will develop adequate roll control torque for typical air-breathing missiles using a total of 1% of the engine air. (Author)