Small satellite solar thermal propulsion system design: An engineering model

Abstract

This paper presents an initial investigation into the design of a solar thermal propulsion concept for an increasingly important class of spacecrafts. Small satellites have been receiving renewed attention over the last decade. The proposed heat exchanger solar thermal propulsion concept attempts to move away from traditional solar thermal propulsion concepts. In this concept thermal energy in the form of heat is moved from the solar array to the propellant. Excess thermal energy is radiated into space. Initial thrust force and specific impulse values obtained by the use of established mathematical relations, produce numerical values that are not only comparable with the traditional solar thermal concept, but also with other small satellite propulsion types. A small satellite with an on-board propulsion system will expand the capability of small-satellites for the use in formation flying and station keeping. It will also provide a viable option for de-orbit at the end of mission life, thereby contributing to the effective removal of orbital spacecrafts once have completed their missions.