AAE450 Spring 2009 Lander Phase: Hybrid Propulsion System Propulsion System Sizing and Inert Mass Analysis Hopper and Rover Designs for 10kg Payload Hopper Design of Arbitrary Payload (Dnepr) IMLLO – Injected Mass Lower Lunar Orbit Hydrogen Peroxide Decomposition Analysis Week 7 Presentation Thursday, Feb 26, 2009 Saad Tanvir Propulsion Group 1

AAE450 Spring 2009 Propulsion System Sizing and Inert Mass Analysis 10 kg Payload case Rover: t burn =207.3 sec, Thrust = 2000 N Propellant mass = 150 kg Propulsion System Inert mass = 42.4 kg Hopper : t burn =197.7 (Landing) + 86 (Hop) = sec, Thrust = 2000 N Propellant mass = 199 kg Propulsion System Inert mass = kg Saad Tanvir Propulsion Group 2

AAE450 Spring 2009 Saad Tanvir Propulsion Group Scaling Factor = IMLLO Dnepr/Wet Lander mass at LLO (10kg payload)= Hopper: t burn = sec, Thrust = 2000×6.245=12490 N Propellant mass = 1150 kg Propulsion System Inert mass = 169 kg Hydrogen Peroxide Decomposition Analysis For Aluminum Sealed Container Active Oxygen Loss from 90% H 2 O 2 for 2 years = 0.078% 1 = kg For Aluminum Vented Container Active Oxygen Loss from 90% H 2 O 2 for 1 year = 0.024% 1,2 = 0.04 kg Arbitrary Payload case (Dnepr) 3

AAE450 Spring 2009 Backup Slides: Rover Design – propulsion inert mass distribution – 10 kg Payload Saad Tanvir Propulsion Group 4

AAE450 Spring 2009 Saad Tanvir Propulsion Group Backup Slides: Hopper Design – propulsion inert mass distribution – 10 kg Payload 5

AAE450 Spring 2009 Saad Tanvir Propulsion Group Backup Slides: Hopper Design – propulsion inert mass distribution – Arbitrary Payload 6

AAE450 Spring 2009 Backup Slides: Pressurant System Analysis Saad Tanvir Propulsion Group 7

AAE450 Spring 2009 Backup Slides: Sizing Code Saad Tanvir Propulsion Group 8

AAE450 Spring 2009 Backup Slides: Sizing Code Continued … Saad Tanvir Propulsion Group 9

AAE450 Spring 2009 Backup Slide: Prop Inert mass variation with Thrust Saad Tanvir Propulsion Group 10

AAE450 Spring 2009 Backup Slides: H 2 O 2 Decomposition references 1 Ventura, M. C. (2005). Long Term Storability of Hydrogen Peroxide. AIAA - Joint Propulsion Conference, (41) 2 Ventura, M. C., Wernimont,, E., & Heister, S. (2007). Rocket Grade Hydrogen Peroxide (RGHP) for use in Propulsion and Power Devices - Historical Discussion of Hazards. AIAA - Joint Propulsion Conference, (43),. Saad Tanvir Propulsion Group 11