Pulsed Laser Propulsion Experiments

Abstract

Pulsed thermal laser propulsion can become a very efficient, relatively near term technology for cheaply launching small satellites into LEO with payload masses on the order of 5 to 10 kg. In addition to flight demonstrations in the laboratory measurements of fundamental propulsion parameters in the atmospheric environment as well as at reduced pressures down to 1 mbar have been made for a parabolic thruster, called “Lightcraft”. The propulsion mode was either air breathing or with a plastic material as solid propellant. The results serve to model a typical launch of a nanosat type laser-propelled vehicle into LEO. A two-stage operation with an air-breathing mode in the denser atmosphere can solve the propellant consuming, drag dominated transition through the atmosphere. System requirements and estimated costs for establishing a commercial launch system will be discussed.