Space Based Missile Interceptor Sizing Methodology

The key to affording a constellation of space-based missiles is a minimum weight system incorporating advanced technologies in electronics and propulsion components. The recent development of a system sizing methodology along with the incorporation of advanced technologies has resulted in reducing acquisition and deployment costs. This system sizing methodology optimizes the interceptor weight for a desired burnout velocity that is anchored with 3-D CAD models based on heritage hardware. The propellant split between stages is iterated until a minimum interceptor weight is achieved. Inputs such as initial mass fraction, delta inert to delta propellant ratio, specific impulse, and burnout acceleration are used along with the delta velocity rocket equation to determine the number of missile stages, thruster size and optimum weight.