Inserted Type Solid Rocket Booster Separation from an Air Breathing Engine Vehicle

This paper proposes an effective numerical methodology to analyze the mechanism of the separation of an inserted type of solid rocket booster from a supersonic air breathing engine vehicle having a conical intake. Unlike the previous computational fluid dynamic (CFD) approach, present work constructs a compacted model capable to reduce the computational time definitely. The dynamics of vehicle including relative booster motion and separation are successfully derived by the multi-body dynamic approach, Kane’s method. Aerodynamic forces along the different relative positions of booster are calculated by DATCOM software and the internal pressure force inside booster channel which mainly determines the magnitude of separation force acting on the effective frontal area of booster is calculated by considering supersonic intake flow with Taylor-MacColl equation. The Mach number, AoA (Angle of attack), pitch angle variation and the booster separation time are investigated as results with booster remnant forces and various initial pitch angles.