Research on forebody active disturbed flow characteristics of slender body in supersonic field

Abstract

Instantaneous turn rate plays an extremely important role in the generic missile configuration with an appropriate angle of attack in supersonic air flows. Under these special supersonic flow conditions, the dominant aerodynamic coefficient of the generic missile, which was simplified to a slender baseline geometry with a blunt-cone nose, was the side force coefficient. Active disturbed flow control technology on a supersonic missile body referred to the design of micro-flow effectors and controlled the flow around the missile by actively regulating the height of the micro-flow effectors around the missile surface, which allows for active control of the missile flight attitude. This paper used the small perturbation assumptions to calculate the side force model affected by the flow effectors and used Ansys Fluent® to analyze the separated vortex around the slender body, as well as the effects of regularity of the parameters for the micro-flow effector to the side force coefficient. In this paper, we also developed methods to analyze the supersonic complex air flow zones and analyzed the air flows around the body and the side force coefficient of the slender body by changing the parameters of the micro-flow effector structure, air flow field conditions and body structural parameters. The projects concluded that the simulation analysis method and analysis of the results can be used to guide active disturbed flow control systems and actuation device designs for compact and lightweight missiles to provide the necessary reference basis.