Numerical investigation of aerodynamic characteristics of dual missiles in close-range flight

Abstract

The interaction of aerodynamic characteristics between missiles should be taken into account during the flight of multiple missiles. This study employs the standard k-ε turbulence model to analyze the flight dynamics of missiles operating under various motion regimes, specifically examining the aerodynamic characteristics of dual missiles influenced by variations in angle of attack and angle of sideslip while in a relatively stationary flight configuration. Utilizing an orthogonal experimental design, a total of 25 numerical simulation cases were developed to systematically assess the safety of dual missile operations, with the differential lift coefficient and pitching moment coefficient between the missiles being designated as critical safety indices. The findings indicate that the interactions resulting from variations in angle of attack predominantly affect the missile body, whereas the influences associated with angle of sideslip are primarily manifested in the missile wings. Furthermore, statistical analyses including range analysis and ANOVA reveal the hierarchy of factors impacting the difference in lift and pitching moment:Mach number > angle of sideslip > angle of attack, and the effect of Mach number is much larger than that of angle of sideslip and the angle of attack. Notably, the data suggest enhanced flight safety for the missiles at a Mach number of 0.9. Additionally, it is observed that as the relative velocity between dual missiles increases, the spatial separation at which notable aerodynamic interactions occur also expands progressively.