Session
Technical Session XIII: Poster Session
Abstract
This paper deals with the propulsion and trajectory issues of creating a small satellite constellation around the Sun. The possible uses for such a constellation, including stereoscopic imaging of the Sun and gamma ray burst localization, are briefly discussed. The focus of the paper is then narrowed to a range of orbits and payload masses. Spread rate, the most important parameter for creating a sun orbiting constellation, is explained and defined. Next, it is shown that impulsive chemical propulsion is better than low thrust electric propulsion for this mission class. Finally, a full discussion of the propulsion and trajectory options available is presented. Among the topics discussed are: launch options, including dedicated launch vehicles and secondary payload slots, propulsion architecture options, including concentrating the propulsion into a single bus and distributing the propulsion among the satellites; and propulsion systems options including solid, monopropellant, and bipropellant propulsion. Performance calculations are given for each option over a wide range of parameters. It is concluded that the best dedicated launch vehicle options are bus monopropellant propulsion, and distributed solid propulsion. It is also concluded that secondary payload slots offer a very low cost alternative to dedicated launch vehicles for payload masses up to 55 kg.
Creating Small Satellite Constellations Around the Sun
This paper deals with the propulsion and trajectory issues of creating a small satellite constellation around the Sun. The possible uses for such a constellation, including stereoscopic imaging of the Sun and gamma ray burst localization, are briefly discussed. The focus of the paper is then narrowed to a range of orbits and payload masses. Spread rate, the most important parameter for creating a sun orbiting constellation, is explained and defined. Next, it is shown that impulsive chemical propulsion is better than low thrust electric propulsion for this mission class. Finally, a full discussion of the propulsion and trajectory options available is presented. Among the topics discussed are: launch options, including dedicated launch vehicles and secondary payload slots, propulsion architecture options, including concentrating the propulsion into a single bus and distributing the propulsion among the satellites; and propulsion systems options including solid, monopropellant, and bipropellant propulsion. Performance calculations are given for each option over a wide range of parameters. It is concluded that the best dedicated launch vehicle options are bus monopropellant propulsion, and distributed solid propulsion. It is also concluded that secondary payload slots offer a very low cost alternative to dedicated launch vehicles for payload masses up to 55 kg.
