Mission data Mission Total mission duration d Crew

Mission data Mission Total mission duration [d] Crew size [-] Injection Δv [m/s] Destination capture Δv [m/s] Destination departure Δv [m/s] Lunar flyby 7 (3. 5/0/3. 5) 4 3200 20 (MCC) Lunar orbit 9 (3. 5/2/3. 5) 4 3200 835 + 20 (MCC) SE-L 2 visit 80 (35/10/35) 4 3200 400 + 50 (MCC) GEO visit 10. 5 (0. 25/10/0. 25) 4 2430 2100 (incl. 28. 5° plane change) 1470 NEO visit 138 (111/16/11) 3 3291 2193 1746

Science Payloads

Consumables data

Habitable volume LSAM crew module Orion crew module

Launch vehicle data Option Solid Rocket Boosters Core Stage LEO Payload [kg] Source 1 2 x 4 -Segment Solid Rocket Boosters 3 x SSME, Side. Mounted 72000 Presentation to the Augustine Committee 2 2 x 4 -Segment Solid Rocket Boosters 3 x SSME, Inline 74000 ESAS Report 3 2 x 5 -Segment Solid Rocket Boosters 4 x SSME, Inline 97000 ESAS Report

Launch vehicle shroud volume

Mission payloads Mission CEV Block II Upgraded CEV Block II LSAM crew compartment Additional consumables Science payload Total payload Lunar flyby 10797 kg - - - 1650 kg 12847 kg Lunar orbit 10797 kg - - - 1650 kg 12847 kg SE-L 2 visit - 11379 kg 2455 kg 1301 kg 4196 kg 19731 kg GEO visit - 11379 kg 2455 kg 0 kg 4196 kg 18430 kg NEO visit - 11379 kg 2455 kg 2175 kg 1476 kg 17685 kg

Centaur V 1 2 x [3 SSME + 2 x 4 -Segment SRB, Side-Mount] 2 x [3 SSME + 2 x 4 -Segment SRB, Inline] 1 x [4 SSME + 2 x 5 -Segment SRB, In-line] 2 x [4 SSME + 2 x 5 -Segment SRB, Inline] NE O GE Lu na r O Or bi t CEV SM + SE -L 2 CEV SM + Lu na r Fl 5 Centaur V 1 4 Centaur V 1 3 Centaur V 1 CEV SM + 2 Cent yb y aur V 1 CEV SM + 1 Centaur V 1 1 x [3 SSME + 2 x 4 -Segment SRB, Side-Mount] 1 x [3 SSME + 2 x 4 -Segment SRB, Inline] 1 x [4 SSME + 2 x 5 -Segment SRB, In-line]

Delta 4 Heavy US 2 x [3 SSME + 2 x 4 -Segment SRB, Side-Mount] 2 x [3 SSME + 2 x 4 -Segment SRB, Inline] 2 x [4 SSME + 2 x 5 -Segment SRB, Inline] NE O Lu na r GE O Or bi t CEV S M + 5 De CEV S M+4 D SE CEV SM + pper S tage Lu yb y eavy U pper S tage 3 Delta 4 H CEV SM + Fl eavy U elta 4 H -L 2 na r lta 4 H eavy Uppe r Stage 2 Delta 4 H eavy Uppe CEV SM + 1 Delta 4 He av r Stage y Upper Stage 1 x [3 SSME + 2 x 4 -Segment SRB, Side-Mount] 1 x [3 SSME + 2 x 4 -Segment SRB, Inline] 1 x [4 SSME + 2 x 5 -Segment SRB, In-line]

Numerical C 3 analysis 4 Ce nt au r. V 1 3 Ce s nt 1 C en 2 Ce au r. V st ag e 1 st ag e s tau nt r. V au r. V e tag 1 s 1 st ag e s

Lunar Flyby Mission Storyboard Earth’s moon Lunar flyby Lunar orbit Centaur V 1 stages discarded Trans-lunar coast Trans-Earth coast LEO Earth entry Launch 1 Earth landing Earth

Lunar Orbit Mission Storyboard Earth’s moon Lunar orbit Low lunar orbit capture Lunar orbit operations Science package discarded Low lunar orbit departure Centaur V 1 stages discarded Trans-lunar coast Trans-Earth coast LEO Earth entry Launch 1 Earth landing Earth

SE-L 2 Mission Storyboard Servicing payload left at the observation asset SE-L 2 operations SE-L 2 capture SE-L 2 departure SE-L 2 halo orbit Centaur V 1 stages discarded Trans-SE-L 2 coast Trans-Earth coast LEO Earth entry Launch 1 Earth landing Earth

SE-L 2 Earth departure

GEO Mission Storyboard GEO asset Capture stage discarded GEO operations Mission module and science payload discarded GEO capture GEO departure Centaur V 1 stages discarded Trans-GEO coast Trans-Earth coast LEO Launch 1 Earth entry Launch 2 Earth landing Earth

GEO Mission GEO insertion

NEO Mission Storyboard Capture stage discarded NEO exploration Mission module and science payload discarded NEO capture NEO vicinity NEO departure Consumables for trans. NEO coast discarded Trans-NEO coast Centaur V 1 stages discarded Trans-Earth coast LEO Launch 1 Earth entry Launch 2 Earth landing Earth

NEO Mission – NEO Insertion