超声速多轴无源流体推力矢量喷管控制特性研究OA

Fluidic thrust vectoring control technology has emerged as a critical solution for aircraft attitude control,demonstrating exceptional potential in propulsion-integrated design and flight performance enhancement.Existing supersonic passive ejector-type fluidic thrust vectoring nozzles predominantly employ 2D configurations,and thus are limited to single-axis pitch control.This study designed a multi-axis passive fluidic thrust vectoring nozzle,which feature a divergent section structure with eight circumferentially arranged secondary flow injection channels to achieve multi-axis thrust vectoring control.Through synchronized schlieren visualization and total pressure measurements,the shock wave structures and thrust vectoring characteristics were systematically investigated under diverse control modes.Experimental results demonstrate that at a nozzle pressure ratio(NPR)of 4.0,thrust vectoring control can be achieved in all 16 circumferential directions by selectively opening and closing secondary flow channels;As the number of closed secondary flow channels increases,the flow vectoring angle gradually increases.The maximum flow vectoring angle in the direction of primary control is 6°,and the linearity is 77.85％;the maximum flow vectoring angle in the direction of secondary control is 5°,and the linearity reaches 96％.