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Falcon 9 Heavy › To carry crew capsule and propellant required to rendezvous with transit vehicle Image Credit: http://www.spacex.com/assets/img/20110405-falcon-heavy.jpg Payload Mass [t] Cost Per Launch Cost per kg of payload 53.0$125 Million$2358.49 Falcon XX To carry Cargo Vehicles into LEO To carry crew vehicle components to be assembled in LEO Payload Mass [t] Cost Per Launch Cost per kg of payload 150.0$300 Million$2000
![ Falcon 9 Heavy › To carry crew capsule and propellant required to rendezvous with transit vehicle Image Credit: Payload Mass [t] Cost Per Launch Cost per kg of payload 53.0$125 Million$ Falcon XX To carry Cargo Vehicles into LEO To carry crew vehicle components to be assembled in LEO Payload Mass [t] Cost Per Launch Cost per kg of payload 150.0$300 Million$2000](http://images.slideplayer.com./13/4129701/slides/slide_2.jpg " Falcon 9 Heavy › To carry crew capsule and propellant required to rendezvous with transit vehicle Image Credit: Payload Mass [t] Cost Per Launch Cost per kg of payload 53.0$125 Million$ Falcon XX To carry Cargo Vehicles into LEO To carry crew vehicle components to be assembled in LEO Payload Mass [t] Cost Per Launch Cost per kg of payload 150.0$300 Million$2000")
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Circular Spiral Out › Constant thrust ParameterValue TOF [days]350 M o [t]*113 M p [t]15 M f [t]98 *M o – mass at LEO (350 km)
![ Circular Spiral Out › Constant thrust ParameterValue TOF [days]350 M o [t]*113 M p [t]15 M f [t]98 *M o – mass at LEO (350 km)](http://images.slideplayer.com./13/4129701/slides/slide_3.jpg " Circular Spiral Out › Constant thrust ParameterValue TOF [days]350 M o [t]*113 M p [t]15 M f [t]98 *M o – mass at LEO (350 km)")
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Various departure dates starting in 2022 › Multiple cargo missions per departure date › 21 Total Cargo Missions ParameterValue TOF [days]316 M o [t]*98 M p [t]12 M f [t] t 87 *M o – Earth Departure Mass t M f – Mars Arrival Mass
![ Various departure dates starting in 2022 › Multiple cargo missions per departure date › 21 Total Cargo Missions ParameterValue TOF [days]316 M o [t]*98 M p [t]12 M f [t] t 87 *M o – Earth Departure Mass t M f – Mars Arrival Mass](http://images.slideplayer.com./13/4129701/slides/slide_4.jpg " Various departure dates starting in 2022 › Multiple cargo missions per departure date › 21 Total Cargo Missions ParameterValue TOF [days]316 M o [t]*98 M p [t]12 M f [t] t 87 *M o – Earth Departure Mass t M f – Mars Arrival Mass")
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Momf1Mp1Mp2MpMa [t]Vinffilename 33432.8029277.004155.802208.506364.3027068.502.91cargocom 113140.0098366.3014773.7013366.3028140.0085000.003.70cargof 126488.50109910.7016577.8012910.7029488.5097000.003.61cargoa1b 117894.50102478.8015415.7012478.8027894.5090000.003.32cargo1c 107923.4093853.5014069.9011853.5025923.4082000.003.13cargo2b 110522.7096102.2014420.5011102.2025522.7085000.003.58cargo3b 119958.90104264.3015694.6011264.3026958.9093000.003.54cargo4b 116882.60101603.6015279.0010603.6025882.6091000.003.13cargo5b 124791.40108443.3016348.1012443.3028791.4096000.002.41cargo6b 107499.0093486.3014012.7011486.3025499.0082000.003.15cargo7b 85627.0074554.5011072.5010554.5021627.0064000.003.64cargo8b 113072.8098306.3514766.4511806.3526572.8086500.003.32 113.0798.3114.7711.8126.5786.50
![Momf1Mp1Mp2MpMa [t]Vinffilename cargocom cargof cargoa1b cargo1c cargo2b cargo3b cargo4b cargo5b cargo6b cargo7b cargo8b](http://images.slideplayer.com./13/4129701/slides/slide_5.jpg "Momf1Mp1Mp2MpMa [t]Vinffilename cargocom cargof cargoa1b cargo1c cargo2b cargo3b cargo4b cargo5b cargo6b cargo7b cargo8b")
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Elliptical Spiral Electric Propulsion ParameterValue TOF [days]669 M o [t]*196 M p [t]37.3 M f [t]158.7 *M o – mass at LEO (350 km) Samantha Rieger ParameterValue Power1.65 kW Thrust35 N Thrust for Decay orbit 1.78 N Isp4000 s
![ Elliptical Spiral Electric Propulsion ParameterValue TOF [days]669 M o [t]*196 M p [t]37.3 M f [t]158.7 *M o – mass at LEO (350 km) Samantha Rieger ParameterValue Power1.65 kW Thrust35 N Thrust for Decay orbit 1.78 N Isp4000 s](http://images.slideplayer.com./13/4129701/slides/slide_6.jpg " Elliptical Spiral Electric Propulsion ParameterValue TOF [days]669 M o [t]*196 M p [t]37.3 M f [t]158.7 *M o – mass at LEO (350 km) Samantha Rieger ParameterValue Power1.65 kW Thrust35 N Thrust for Decay orbit 1.78 N Isp4000 s")
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MissionEarth DepartureMars Arrival DateV ∞ [km/s]ΔV [km/s]DateV ∞ [km/s]V p [km/s] A/112/06/20264.861.19006/04/20275.837.625 201/14/20294.801.14607/13/20295.347.257 303/06/20314.801.14608/25/20314.526.677 405/05/20333.500.68311/01/20333.466.011 507/09/20353.470.67401/05/20362.735.622 609/11/20374.871.17403/10/20383.315.925 710/20/20395.001.22804/15/20404.936.961
![MissionEarth DepartureMars Arrival DateV ∞ [km/s]ΔV [km/s]DateV ∞ [km/s]V p [km/s] A/112/06/ /04/ /14/ /13/ /06/ /25/ /05/ /01/ /09/ /05/ /11/ /10/ /20/ /15/](http://images.slideplayer.com./13/4129701/slides/slide_7.jpg "MissionEarth DepartureMars Arrival DateV ∞ [km/s]ΔV [km/s]DateV ∞ [km/s]V p [km/s] A/112/06/ /04/ /14/ /13/ /06/ /25/ /05/ /01/ /09/ /05/ /11/ /10/ /20/ /15/")
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V - [km/s]V circular [km/s]ΔV [km/s]M p [t] 3.523.450.0882.26e-3 Drawing by Monica Pires Hyperbolic Approach Atmospheric Entry Atmospheric Exit Raise Maneuver Locations 8 V - [km/s]V circular [km/s]ΔV [km/s]M p [t] 3.523.450.0912.36e-3
![V - [km/s]V circular [km/s]ΔV [km/s]M p [t] e-3 Drawing by Monica Pires Hyperbolic Approach Atmospheric Entry Atmospheric Exit Raise Maneuver Locations 8 V - [km/s]V circular [km/s]ΔV [km/s]M p [t] e-3](http://images.slideplayer.com./13/4129701/slides/slide_8.jpg "V - [km/s]V circular [km/s]ΔV [km/s]M p [t] e-3 Drawing by Monica Pires Hyperbolic Approach Atmospheric Entry Atmospheric Exit Raise Maneuver Locations 8 V - [km/s]V circular [km/s]ΔV [km/s]M p [t] e-3")
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Elliptical Spiral Electric Propulsion ParameterValue TOF [days]89.48 M o [t]*29.5 M p [t]4.05 M f [t]25.45 *M o – mass at LEO (350 km) Samantha Rieger ParameterValue Power850 kW Thrust25 N Isp4900 s
![ Elliptical Spiral Electric Propulsion ParameterValue TOF [days]89.48 M o [t]*29.5 M p [t]4.05 M f [t]25.45 *M o – mass at LEO (350 km) Samantha Rieger ParameterValue Power850 kW Thrust25 N Isp4900 s](http://images.slideplayer.com./13/4129701/slides/slide_9.jpg " Elliptical Spiral Electric Propulsion ParameterValue TOF [days]89.48 M o [t]*29.5 M p [t]4.05 M f [t]25.45 *M o – mass at LEO (350 km) Samantha Rieger ParameterValue Power850 kW Thrust25 N Isp4900 s")
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Inputs/Assumptions › a = 2.8gMars › m = 105 t › Isp = 375 s › Constant mass › Drag of atmosphere Results › Δ V = 3.88 km/s › TOF = 404.1 s
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Stay on MarsTOFNecessary transfer Δ V Actual impulsive Δ V (reduces due to tug) 547 days180 days3.43 km/s1.88 km/s & Rosie Geeck
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