Simulations of a Missile with Liquid Payload under Launch Conditions

摘要

A numerical simulation of the flow of a liquid in the annular region between two coaxial circular cylinders was performed. This simulation corresponds to the actual behavior of a missile with a liquid payload during its launch phase. The simulation was performed in two parts. The first part was to determine if the payload liquid, which comprised both Newtonian and non-Newtonian fluids, would achieve full spin up relative to the missile during launch. During the second part, the despin moments acting on the spinning and nutating missile with a fully spun up liquid payload were determined from the steady-state Navier-Stokes equations relative to an aeroballistic reference frame. The simulations were performed with a finite element software package FIDAP. The majority of the computations were done on an HP9000 minicomputer; some were done on a Microvax workstation.