1. 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

2. Lessons from Apollo *

5. Total vehicle weight in LEO = 296,379 pounds Total propellant weight = 157,010 pounds Stage 3 engine - one J-2 using Lox/LH 2 Command/Service Module weight = 67,164 pounds Lunar Excursion Module weight= 33,205 pounds Total Weight delivered to Low Lunar Orbit = 100,369 pounds Lunar Orbit Weight Fraction =.33 So, for every 10,000 lbs in LEO, Saturn put 3300 lbs in LLO (using LOX/LH2 J-2 class engines) Trans Lunar Injection Summary

6. Lessons from Apollo * For every 10,000 lbs in LEO, we can put 3300 lbs in LLO Requires LOX/LH2 J-2 class engines Limited amount of time from launch to TLI burn Not generally used for shuttle-based upper stages Good for un-manned launches, like Delta’s II thru IV Other propellants (MMH/NTO 4 ), deliver lower performance Isp LH2 = 450 Isp MMH = 338 MMH/NTO 4 can be stored for longer periods Used for CSM & LEM engines For MMH engines, 10,000 lbs LEO puts 1125 lbs in LLO Trans Lunar Injection Summary

7. Lessons from Apollo * Current Launchers Improvements 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#) Good for launching cargo, supplies, etc. Delta IV (5,4) can place 25,300 lbs in LEO Propellant = 15,048 lbs Payload to TLI = 10,252 lbs

8. 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

9. 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 (5,4) (LLO = 9,099) payload to LLO = 4431 lbs !!!!