Cost-effective mission design for a small solar probe

Abstract

The Small Solar Probe Mission is designed to characterize the Solar Corona as close as three solar radii above the sun's surface. Until 1992 studies generated concepts with large spacecraft launched on large launch vehicles and requiring nearly a decade to reach their initial perihelion. In 1992 JPL responded to emerging fiscal constraints by proposing a Small Solar Probe. The payload was reduced in scope while yet retaining the primary objectives of this exploratory mission. The mission design uses a Delta launch vehicle and a direct trajectory to Jupiter where a gravity assist places the spacecraft on a polar trajectory about the Sun; This paper describes the mission and the designs derived from it in the context of a cost effective concept. Design choices made are directly related to cost implications.