1 / 11

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

baxter
Télécharger la présentation

Week 7 Presentation Thursday, Feb 26, 2009

An Image/Link below is provided (as is) to download presentation Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author. Content is provided to you AS IS for your information and personal use only. Download presentation by click this link. While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server. During download, if you can't get a presentation, the file might be deleted by the publisher.

E N D

Presentation Transcript


  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

More Related