Performance Analysis of Axial-Injection, End-Burning Hybrid Rocket Propulsion System

Abstract

Although several investigations have been performed regarding the fundamental physics of axial-injection, end-burning hybrid rocket motors, investigations into the mission performance of a propulsion system based on this hybrid rocket motor configuration are limited. This Paper provides analysis of the performance characteristics of axial-injection, end-burning hybrid rocket motors based on the results from experimental tests in the literature. Notional propulsion systems were sized using the observed regression rates and characteristic velocities. These propulsion systems were then evaluated to determine the Delta-V that could be provided by an axial-injection, end-burning hybrid motor propulsion system using a plastic fuel and gaseous oxygen or nitrous oxide as the propellants. These Delta-V calculations were performed for different sizes of satellites. Finally, the calculated Delta-Vs were compared to those required for different maneuvers to evaluate the usefulness of axial-injection, end-burning hybrid rocket motors. Results from the analysis indicated that the provided specific impulse ranged from the mid-200 to -300 s depending on chamber pressure and expansion ratio, while the Delta-V values were in the several hundred meters/second range depending on the satellite mass. Overall, the Delta-V provided were sufficient for a variety of orbital maneuvers including altitude adjustments, orbit phasing, orbit maintenance, and deorbiting.