mission data
DESCRIPTION
Mission data. Science Payloads. Consumables data. Habitable volume. LSAM crew module. Orion crew module. Launch vehicle data. Launch vehicle shroud volume. Mission payloads. Centaur V1. 2 x [3 SSME + 2 x 4-Segment SRB, Side-Mount]. 2 x [3 SSME + 2 x 4-Segment SRB, Inline]. - PowerPoint PPT PresentationTRANSCRIPT
Mission data
MissionTotal missionduration [d]
Crewsize [-]
InjectionΔv [m/s]
Destination capture
Δv [m/s]
Destinationdeparture
Δv [m/s]
Lunar flyby 7 (3.5/0/3.5) 4 3200 20 (MCC) 20 (MCC)
Lunar orbit 9 (3.5/2/3.5) 4 3200 835 + 20 (MCC) 835 + 20 (MCC)
SE-L2 visit 80 (35/10/35) 4 3200 400 + 50 (MCC) 400 + 50 (MCC)
GEO visit 10.5 (0.25/10/0.25) 4 24302100 (incl. 28.5° plane change)
1470
NEO visit 138 (111/16/11) 3 3291 2193 1746
Science Payloads
Consumables data
Habitable volume
Orioncrew module
LSAMcrew module
Launch vehicle data
Option Solid Rocket Boosters Core Stage LEO Payload [kg] Source
12 x 4-Segment Solid
Rocket Boosters3 x SSME, Side-
Mounted72000
Presentation to the Augustine Committee
22 x 4-Segment Solid
Rocket Boosters3 x SSME, Inline 74000 ESAS Report
32 x 5-Segment Solid
Rocket Boosters4 x SSME, Inline 97000 ESAS Report
Launch vehicle shroud volume
Mission payloads
Mission CEV Block IIUpgraded
CEV Block IILSAM crew
compartmentAdditional
consumablesScience payload
Total payload
Lunar flyby 10797 kg - - - 1650 kg 12847 kg
Lunar orbit 10797 kg - - - 1650 kg 12847 kg
SE-L2 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 V1
CEV SM + 1 Centaur V1
CEV SM + 2 Centaur V1
CEV SM + 3 Centaur V1
CEV SM + 4 Centaur V1
CEV SM + 5 Centaur V1
2 x [3 SSME +2 x 4-Segment SRB,
Inline]
2 x [4 SSME +2 x 5-Segment SRB,
Inline]
2 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]
1 x [3 SSME +2 x 4-Segment SRB,
Side-Mount]
Lunar Orbit
SE-L2
Lunar Flyby
GEO
NEO
1 x [4 SSME +2 x 5-Segment SRB,
In-line]
Delta 4 Heavy US
CEV SM + 1 Delta 4 Heavy Upper Stage
CEV SM + 2 Delta 4 Heavy Upper Stage
CEV SM + 3 Delta 4 Heavy Upper Stage
CEV SM + 4 Delta 4 Heavy Upper Stage
CEV SM + 5 Delta 4 Heavy Upper Stage
Lunar Orbit
SE-L2
Lunar Flyby
GEO
NEO
1 x [3 SSME +2 x 4-Segment SRB,
Inline]
2 x [4 SSME +2 x 5-Segment SRB,
Inline]
1 x [3 SSME +2 x 4-Segment SRB,
Side-Mount]
1 x [4 SSME +2 x 5-Segment SRB,
In-line]
2 x [3 SSME +2 x 4-Segment SRB,
Inline]
2 x [3 SSME +2 x 4-Segment SRB,
Side-Mount]
Numerical C3 analysis
4 Centaur V1 stages3 Centaur V1 stages
2 Centaur V1 stages
1 Centaur V
1 stage
Lunar Flyby Mission Storyboard
Earth
Lunarorbit
LEO
Earth’smoon
Centaur V1 stages discarded
Launch 1
Trans-lunar coast Trans-Earth coast
Earth entry
Earth landing
Lunar flyby
Lunar Orbit Mission Storyboard
Earth
Lunarorbit
LEO
Earth’smoon
Centaur V1 stages discarded
Launch 1
Trans-lunar coast Trans-Earth coast
Earth entry
Earth landing
Lunar orbit operations
Science package discarded
Low lunar orbit capture Low lunar orbit departure
SE-L2 Mission Storyboard
Earth
SE-L2halo orbit
LEO
SE-L2asset
Centaur V1 stages discarded
Launch 1
Trans-SE-L2 coast Trans-Earth coast
SE-L2 captureSE-L2 departure
SE-L2operations
Earth entry
Earth landing
Servicing payload left atthe observation asset
SE-L2 Earth departure
GEO Mission Storyboard
Earth
GEO
LEO
Centaur V1 stages discarded
Launch 1 Launch 2
Trans-GEO coast Trans-Earth coast
GEO capture
GEO departure
GEO operations
Earth entry
Earth landing
GEOasset
Mission module and sciencepayload discarded
Capture stage discarded
GEO Mission GEO insertion
NEO Mission Storyboard
Earth
NEOvicinity
LEO
NEO
Centaur V1 stages discarded
Launch 1 Launch 2
Trans-NEO coast Trans-Earth coast
NEO capture
NEO departure
NEO exploration
Earth entry
Earth landing
Capture stage discarded
Mission module and sciencepayload discarded
Consumables for trans-NEO coast discarded
NEO Mission – NEO Insertion