Two-body missile separation dynamics

摘要

The dynamics of the separation of a two-body missile has been investigated. This missile consists of an outer boost vehicle and an inner center body vehicle. Upon completion of the boost phase the two bodies separate as a result of differing aerodynamic loads applied to each body and the thrust from a sustainer motor contained within the center body. Through simulation, the separation event was evaluated for interaction between the two bodies as a function of flight-path-angle, interstage pressure, sustainer motor thrusting force, thrust misalignment angles, and radial clearance. The impact and friction forces created by any interaction were evaluated and their effects on the separation event were quantified. The flight characteristics of the center body after the separation event were also calculated for use in determination of the missile flight profile. Finally, recommendations are made regarding the design and performance conditions for the specific two-body missile addressed in this study.