David Heck Advanced Manufacturing Research & Development Boeing – Phantom Works, St. Louis, Mo

2. SEND IT TO THE MOON David Heck Advanced Manufacturing Research & Development Boeing – Phantom Works, St. Louis, Mo

3. Space Shuttle Return to Flight • July 2005 Discover • Returned with 13 tons of ISS trash • 26,000 pounds total • old equipment, packaging, wiring • waste water, human waste, etc

4. Returned with 13 tons of ISS trash (2 years worth) • 26,000 pounds total • old equipment, packaging, wiring • waste water, human waste, etc • Paid lots of $$ to get it to orbit • Paying more to bring it home

8. Shower Head Vacuum Hose

9. Vacuum Hose Sit here Footrest

10. Need Carbon & Nitrogen

11. Space Station Waste Estimate (5) 589 (5) 231

12. 3558 g/CM-d TOTAL • 1918 g Human Waste = 54% • 423 g bio-degradable • Total degradable = 66% (5) 589 (5) 231 In-Situ Resource Utilization (ISRU)

13. 26,000 pounds total of trash • old equipment, packaging, wiring • waste water, human waste, etc • Based on typical ISS output, • 54% human waste • 66% bio-related • Actual composition: • 14,410 lbs. human waste • 1,600 lbs. other bio-degradable

14. Why is this important ? • Launch costs are prohibitive • Delta IV Medium – • $130 million puts 25,000 pounds in LEO • about $5000 per pound to LEO • Can land 4400 pounds on Lunar surface • $30,000 per pound to Lunar surface

16. Why In-Situ ? • 6 ounce can of Wasabi Peas - • 12 bottle of ketchup - • Not having to ship EVERYTHING • up from the Earth - $11,250 $22,500 PRICELESS

17. Living off the land In-Situ Resource Utilization (ISRU)

19. Lunar Landings, circa 1970 • 6 Apollo • 3 Luna • 840 lbs. • Wash U. regional node for analysis 11

20. 4.5 % Titanium 6 % 5.5 % 40 % 14 % 19 %

21. 40% oxygen – rocket oxidizer, O2 • 19 % silicon – glass & ceramics • 14% iron - iron & steel products – construction • 6% Titanium - high temperature & spacecraft • 5.5% Aluminum – light weight spacecraft parts • 4.5%Magnesium – light weight parts, alloy element • Others: Chrome, Manganese, Sulphur, Potassium, Carbon (00.014%) • 850 pounds from 6 sites. What else could we find ?

22. Composition of Lunar Samples

23. Composition of Lunar Samples

24. Lunar Industry • Mining • Robotic Sweeper – 2 foot wide, 1 inch regolith depth • Moving at 1 mile per hour • (5280 ft per hour = 1.5 ft per sec) • Gathers 880 ft3 PER HOUR • = 10 ft x 10 ft x 8.8 feet high • @13% Iron, 25% utilization yields 28 ft3 of IRON • = 42 - 4 ft X 4 ft X 1 inch sheets PER HOUR ! ADD Carbon = STEEL

25. Lunar Industry • Ground transport • lunar bus, carts, miners, rovers • Maglev trains & tracks • Mass driver launchers • Structures • blast deflectors, reflectors, antennas, sun shades • tanks, towers, rails/tracks • habitats, work areas • power transmission • Systems • Gas & fluid processing equipment & machines • Waste processing & recycling • Power generation & transmission

26. Spherical Tanks “Stick” Reflectors

27. Lunar Industry

28. How do we get it there ? • Three main steps • Push into Trans-Lunar Injection trajectory • Brake into Lunar orbit (LOI) • De-orbit & land on the Moon • Requires lots of Fuel

29. How do we get it there ? • Easy Way - • Upper Stage Chemical Rocket booster • Traditional rocket powered Lander • Lots of mass to push to Moon • Requires lots of Fuel • How Much ??

30. Lessons from Apollo* • Data from NASA Apollo 11 Press Kit • Shows spacecraft weight delivered to LEO • (Low Earth Orbit) • Shows weights for each portion of Apollo 11 • Command & Service Module • L.E.M. (Descent and Ascent stages) • Various sub-systems (water, ECS package, etc.) • Propellant weights for each stage, engine specs • Allows calculation of “Parametric” values

31. Lessons from Apollo*

32. Lessons from Apollo*

33. Lessons from Apollo*

34. Lessons from Apollo* Trans Lunar Injection Summary • For every 10,000 lbs in LEO, Apollo puts 3300 lbs in TLI • Requires LOX/LH2 J-2 class engines • Payload Ratio is .33 • Delta II (7925H-10L) can place 10,120 lbs in LEO • Current MB-60 engine is higher performance than J-2 • Isp = 467 versus Isp = 420 for J-2 • Required propellant = 10,120*.666*(420/467) = 6019 lbs • Payload to LLO = 10,120-6019 = 4101 lbs (extra 761#) • Delta IV (5,4) can place 25,300 lbs in LEO • Propellant = 15,048 lbs • Payload to TLI = 10,252 lbs • Payload Ratio is .33

35. Lessons from Apollo* • Lunar Orbit Insertion • Apollo Summary • Command Service Module/LEM weight at TLI = 100,369 • LOI Propellant used = 12,011 lbs MMH/NTO • Apollo Isp = 318 versus Isp = 338 for RS-72 • Fuel fraction = .112 ……. Payload fraction = .887 • Delta II (TLI = 4101 lbs) payload to LLO = 3,639 lbs • Delta IV (5,4)(TLI = 10,252) payload to LLO = 9,099 lbs • Payload Ratio is . 887

36. Lessons from Apollo* • Lunar LANDING • Apollo Summary • LEM weight 33,205 (Apollo 11) • Descent Propellant used = 18,100 lbs MMH/NTO • Payload to Lunar Surface = 14,501 lbs …. • Apollo Isp = 318 versus Isp = 338 for RS-72 • Apply to LEM weights, current fractions are … • Fuel fraction = .513 ……. Payload fraction = .487 • Delta II (LLO = 3639 lbs) payload to Lunar Surface = 1,772 lbs • Delta IV (LLO = 9,099) payload to Lunar Surface = 4431 lbs !!!! • Payload fraction = .487

37. Lessons from Apollo* • Summary of TLI, LOI, LL • TLI fraction = .33 LOI fraction = .887 • L Landing = .487 • Delta IV (5,4) puts 25,300 lbs in LEO • Lands 4431 pounds on the surface = 17% Payload • For our 8,800 pounds of … schtuff, we need 52,000 pounds of fuel • @ $5,000 per pound, cost = $258,000,000

38. Other Ideas • Mars Rover Landing Bag • Ion Propulsion • ISP = 8,000 vs. 460 for LH2 • Fuel weight now 4,000 lbs • Cost is $20,000,000

39. IS THIS REALLY GOING TO HAPPEN ? US South Pole Research Station University of Arizona Controlled Environment Ag. Center http://ag.arizona.edu/ceac/CEACresearch/International/004.htm

40. University of Arizona Controlled Environment Ag. Center

41. University of Arizona Controlled Environment Ag. Center Mars Simulation Development Unit http://ag.arizona.edu/ceac/CEACresearch/International/004.htm