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Week 7 Presentation Thursday, Feb 26, 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

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Week 7 Presentation Thursday, Feb 26, 2009

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

  2. Propulsion System Sizing and Inert Mass Analysis Saad Tanvir Propulsion Group 10 kg Payload case Rover: tburn=207.3 sec, Thrust = 2000 N Propellant mass = 150 kg Propulsion System Inert mass = 42.4 kg Hopper:tburn=197.7 (Landing) + 86 (Hop) =283.7 sec, Thrust = 2000 N Propellant mass = 199 kg Propulsion System Inert mass = 49.81 kg 2

  3. Arbitrary Payload case (Dnepr) • Hydrogen Peroxide Decomposition Analysis • For Aluminum Sealed Container • Active Oxygen Loss from 90% H2O2 for 2 years = 0.078%1 = 0.125 kg • For Aluminum Vented Container • Active Oxygen Loss from 90% H2O2for 1 year = 0.024%1,2 = 0.04 kg Saad Tanvir Propulsion Group Scaling Factor = IMLLO Dnepr/Wet Lander mass at LLO (10kg payload)= 6.245 Hopper:tburn= 283.7 sec, Thrust = 2000×6.245=12490 N Propellant mass = 1150 kg Propulsion System Inert mass = 169 kg 3

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

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

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

  7. Backup Slides: Pressurant System Analysis Saad Tanvir Propulsion Group 7

  8. Backup Slides: Sizing Code Saad Tanvir Propulsion Group 8

  9. Backup Slides: Sizing Code Continued … Saad Tanvir Propulsion Group 9

  10. Backup Slide: Prop Inert mass variation with Thrust Saad Tanvir Propulsion Group 10

  11. Backup Slides: H2O2 Decomposition references Saad Tanvir Propulsion Group 1Ventura, M. C. (2005). Long Term Storability of Hydrogen Peroxide. AIAA - Joint Propulsion Conference, (41) 2Ventura, 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), . 11

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