Trajectory Simulations, Qualitative Analyses and Parametric Studies of a Laser-Launched Micro-Satellite Using OTIS

This paper will discuss Air Force Research Laboratory (AFRL) Propulsion Directorate’s theoretical and computational results regarding trajectory simulations, qualitative analyses and parametric studies of a 25‐cm focal diameter Laser Ramjet (X‐25LR) using Optimal Trajectories by Implicit Simulation (OTIS). OTIS has been used to produce an optimized trajectory simulation of a laser ramjet’s flight to Low Earth Orbit (LEO). The baseline case that has been simulated is a flight vehicle powered by a 1 MW, 10.6 μm, CO2, ground‐based laser (GBL) with an initial power capture of 82%. The fuel that is used during rocket flight is Delrin® doped with energetic additives to increase the coupling coefficient and thrust by a factor of five. Additionally, a nozzle extension was considered which increased performance by 40%. The flight trajectory was separated into three phases: 1) Air‐breathing ramjet flight to a specified altitude of ∼30 km and Mach number of ∼10; 2) Rocket powered flight into a trajectory with a fina...