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Data from NASA Apollo 11 Press Kit Shows spacecraft weight delivered to LEO (Low Earth Orbit)

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.)

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Data from NASA Apollo 11 Press Kit Shows spacecraft weight delivered to LEO (Low Earth Orbit)

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  1. 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. Trans Lunar Injection Summary • Total vehicle weight in LEO = 296,379 pounds • Total propellant weight = 157,010 pounds • Stage 3 engine - one J-2 using Lox/LH2 • 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)

  3. Trans Lunar Injection Summary • 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/NTO4), deliver lower performance • Isp LH2 = 450 Isp MMH = 338 • MMH/NTO4 can be stored for longer periods • Used for CSM & LEM engines • For MMH engines, 10,000 lbs LEO puts 1125 lbs in LLO

  4. 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

  5. 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

  6. 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 !!!!

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