Synthesizing Spacecraft Orbits with High Inclinations Using Venusian Gravity Assists

Abstract

An adaptive, semi-analytical, and geometrically clear method for synthesis of sequences of Venusian gravity-assist maneuvers setting the desired inclination of a spacecraft orbit is proposed. The geometric constraint on the maximum possible inclination of a spacecraft orbit, which depends on the asymptotic spacecraft velocity relative to Venus, and the dynamic constraint (arising when a gravity-assist maneuver is performed) on the angle of rotation of the vector of asymptotic velocity relative to Venus are considered simultaneously.