Hybrid rocket propulsion systems for outer planet exploration missions

Abstract Outer planet exploration missions require significant propulsive capability, particularly to achieve orbit insertion. Missions to explore the moons of outer planets place even more demanding requirements on propulsion systems, since they involve multiple large Δ V maneuvers. Hybrid rockets present a favorable alternative to conventional propulsion systems for many of these missions. They typically enjoy higher specific impulse than solids, can be throttled, stopped/restarted, and have more flexibility in their packaging configuration. Hybrids are more compact and easier to throttle than liquids and have similar performance levels. In order to investigate the suitability of these propulsion systems for exploration missions, this paper presents novel hybrid motor designs for two interplanetary missions. Hybrid propulsion systems for missions to Europa and Uranus are presented and compared to conventional in-space propulsion systems. The hybrid motor design for each of these missions is optimized across a range of parameters, including propellant selection, O / F ratio, nozzle area ratio, and chamber pressure. Details of the design process are described in order to provide guidance for researchers wishing to evaluate hybrid rocket motor designs for other missions and applications.

[1]  Brian J. Cantwell,et al.  Hybrid Rocket Propulsion and In-Situ Propellant Production for Future Mars Missions , 2013 .

[2]  Brian J. Cantwell,et al.  Hybrid Propulsion for Solar System Exploration , 2011 .

[3]  D. R. Cruise,et al.  THEORETICAL Computations of Equilibrium Compositions, Thermodynamic Properties, and Performance Characteristics of Propellant Systems , 1979 .

[4]  M. Ravindran,et al.  Fuel Regression Rate in Hydroxyl-Terminated-Polybutadiene/ Gaseous-Oxygen Hybrid Rocket Motors , 2001 .

[5]  P. Penzo,et al.  Trajectory Design for a Europa Orbitter Mission: A Plethora of Astrodynamic Challenges , 1997 .

[6]  Eric W. Lemmon,et al.  Thermophysical Properties of Fluid Systems , 1998 .

[7]  Ronald W. Humble,et al.  Space Propulsion Analysis and Design , 1995 .

[8]  Elena Toson,et al.  Design and Optimization of Hybrid Propulsion Systems for In-Space Application , 2015 .

[9]  G. Zilliac,et al.  Hybrid Rocket Fuel Regression Rate Data and Modeling , 2006 .

[10]  M. Arif Karabeyoglu,et al.  Evaluation of the Homologous Series of Normal Alkanes as Hybrid Rocket Fuels , 2005 .

[11]  Ashley C. Karp,et al.  Hybrid propulsion in-situ resource utilization test facility results , 2015 .

[12]  Greg Zilliac,et al.  Continued Testing of the High Performance Hybrid Propulsion System for Small Satellites , 2015 .

[13]  Greg Zilliac,et al.  Nitrous Oxide Hybrid Rocket Motor Fuel Regression Rate Characterization , 2007 .

[14]  Greg Zilliac,et al.  Peregrine Hybrid Rocket Motor Development , 2014 .

[15]  Arif Karabeyoglu,et al.  A Two-Stage, Single Port Hybrid Propulsion System for a Mars Ascent Vehicle , 2010 .

[16]  Alfred C Wright.  USAF Propellant Handbooks. Nitric Acid/Nitrogen Tetroxide Oxidizers. Volume II. , 1977 .

[17]  Erik Seedhouse.  SpaceShipTwo: VSS Enterprise , 2015 .

[18]  Sarah Ramsey.  All Systems Go for NASA's Mission to Jupiter Moon Europa , 2015 .

[19]  R. Muzzy.  Applied hybrid combustion theory , 1972 .

[20]  C. J. Budney,et al.  MUSEings on Uranus: Exploration of the Ice-Giant , 2014 .

[21]  H. Seifert,et al.  Rocket Propulsion Elements , 1963 .

[22]  Brian Evans,et al.  Hybrid Rocket Investigations at Penn State University's High Pressure Combustion Laboratory: Overview and Recent Results , 2009 .

[23]  Barry Nakazono,et al.  Hybrid Propulsion In-Situ Resource Utilization Test Facility Development , 2014 .