Orbit Selection for Space Based Interception of a Select ICBM Case

Abstract

In this paper, the orbit selection and configuration of the space-based exo-atmospheric kill vehicle (EKV) launch platforms are determined for three example launch sites. These include North Korea, China and Iran. The trajectories of the intercontinental ballistic missiles (ICBMs) are derived and the resulting trajectory parameters are used to determine the orbit necessary for a successful intercept. The parameters calculated include the inclination angle i, right ascension of the ascending node Q and the altitude r/sub a/ of the orbit. The calculations are based on the ICBM locations, capability of the space launch vehicle and the capabilities of the EKV. We show that for the launch locations given, a successful intercept requires 40 launch platforms in a circular orbit with altitude r/sub a/ = 1000 km, inclination angle i = 43.5 degrees and a right ascension angle of /spl Omega/ = 15.3 degrees.