Conceptual design study performed at Johnson Space Center in summer 2006, in partial fulfillment of the requirements for the Master of Science in Space Studies at the International Space University.

1. Extensible Design of a Lunar Lander Robert Guinness & Arthur Guest International Space University 28 August 06

5. NASA and Constellation Program Organization Manages Agency-wide VSE Program Manage Agency-wide Programs Level 1 Level 2 Level 3 This office not yet “stood up.”

6. Advanced Projects Office and Lunar Lander Pre-Project Providing an “international perspective” on the lunar lander design ?

7. LLPS Requirements Crewed Sortie Mission

8. LLPS Requirements Crewed Outpost Mission ~180 days (south pole)

9. LLPS Requirements Cargo Outpost Mission

10. “Conceptual Design” Subset of the propulsion tradespace

16. The Truck Analogy Crew Cabin Generic Storage Fuel Engine Image of Mack Truck used with permission courtesy of Bob Young

26. Propulsion Trade 3268 kg 2888 kg Power-adjusted Total System Mass 0 kg ~30 kg Mass to produce Power for 99 days 0 W 78 W Power for Cryo-cooler 3268 kg 2858 kg System Mass Subtotal 2553 kg 1797 kg Total Usable Propellant 964 kg 257 kg Usable Fuel Mass 1590 kg 1540 kg Usable Oxidizer Mass 714 kg 1061 kg Inert Mass NTO/MMH LOX/LH2 Propulsion System Type

34. Sizing our Conceptual Design kg 53599.95 kg 45000.52 kg 45000.16 Launch Mass kg 20654.14 kg 2140.92 kg 564.07 Cargo-Launched kg 566.76 Inert Mass LLOCM kg 7041.09 Inert Mass SLOCM kg 5314.02 Inert Mass LSH kg 2182.53 kg 2153.80 Propellant kg 3284.94 kg 3277.66 Inert Mass LARS kg 2986.70 kg 2176.46 kg 1796.54 Propellant kg 5036.57 kg 4484.38 kg 4485.02 Inert Mass FDLS kg 21265.41 kg 20371.06 kg 23737.88 Propellant kg 3090.38 kg 3319.15 kg 3671.16 Inert Mass LCIDS Cargo Outpost Mission Crewed Outpost Mission Crewed Sortie Mission

38. Compliance with Requirements

39. Compliance with Desirements

42. BACK UP SLIDES

43. Ascent Stage Sensitivity

44. Propulsion Trade 3268 kg 2888 kg Power-adjusted Total System Mass 0 kg ~30 kg Mass to produce Power for 99 days 0 W 78 W Power for Cryo-cooler 3268 kg 2858 kg System Mass Subtotal 2553 kg 1797 kg Total Usable Propellant 964 kg 257 kg Usable Fuel Mass 1590 kg 1540 kg Usable Oxidizer Mass 714 kg 1061 kg Inert Mass NTO/MMH LOX/LH2 Propulsion System Type

45. Descent Trajectory Analysis

46. Important SORT Parameters 35571 lbm Optimization Variable OPTNAM Landed mass 379 s Control INDNAM(3) Time of start of vertical landing 279 s Control INDNAM(2) Time of first burn shutdown 25.0 km Control INDNAM(1) Initial altitude 2 m/s Constraint DEPNAM(2) Final descent rate 30 m Constraint DEPNAM(1) Final height above surface 9854 kg Input SWGT(3) Total Propellant Mass 3671 kg Input SWGT(2) Inert mass of jettisoned stage 15794 kg Input SWGT(1) Landed mass (inert mass plus ascent stage and cargo) Mass Statement 10 seconds Event criteria TPHASE CRITR (@ Event 115) Time of free-fall after stage jettison -179.9 degrees Input DALPHA Guidance angle of thrust vector 0.66667 Input XKCMD (@ Event 115) Throttle command setting for first burn segment 0.92 Input XKCMD (@ Event 100) Throttle command setting for first burn segment 32000 lbf Input LTHR01 Maximum Thrust of Engines 460 seconds Input LSI01 Specific Impulse of Engines Value Units Type Variable Name Parameter

47. Gravity Turn Steering

48. Descent Trajectory: Full and Close-up

49. Time Plots of Important Parameters

50. Time Plots of Important Propulsion Parameters

51. Time Plots of Important Propulsion Parameters

52. Extracurricular Activities