AAE450 Spring 2009 Hydrogen Peroxide vs. Hydrazine Attitude Control Thrusters Brittany Waletzko Translunar/OTV Phase Week 5 Brittany Waletzko - ATT

AAE450 Spring 2009 The Scenario  Need thrusters to despin/desaturate reaction wheels during TLI  Thrusters could be useful for attitude control during lunar descent as well (~20Nm needed)  Propulsion considering using H 2 O 2 as oxidizer  use some for ATT Brittany Waletzko - ATT

AAE450 Spring 2009 Bottom-Line Figures Brittany Waletzko - ATT  Bottom line: Depending on final main engine selection, OTV phase ATT can accommodate with minimal project impact (level 3 changes) Future Work: Solidifying supporting hardware mass/power/cost figures, electrothermal hydrazine thruster options, other design alternatives  Valves make both hydrazine and hydrogen peroxide throttleable  Hydrazine less massive but significantly more expensive

AAE450 Spring 2009 Questions? Brittany Waletzko - ATT

AAE450 Spring 2009 Brittany Waletzko - ATT Backup Slides: Preliminary Electrothermal Hydrazine Thruster Research

AAE450 Spring 2009 Brittany Waletzko - ATT Size and Mass Comparison: N 2 H 4 and H 2 O 2

AAE450 Spring 2009 Primary References  Monopropellant Hydrazine Thrusters. Astrium Space Propulsion. 21 Jan  Rocket Research Corporation. "Final Report for Monopropellant Hydrazine Thruster System,"  Eric Wernimont, Ph.D. General Kinetics, Inc.: Huntington Beach, CA. Correspondence 7 Feb - 10 Feb  Astronautix. “Hydrazine”   “Electrothermal Hydrazine Data” Brittany Waletzko - ATT