Mission Design Back Up Slides Samantha Rieger Dewayne
Mission Design Back Up Slides Samantha Rieger Dewayne Bishop Peter Borchert Rosalie Geeck Monica Pires Fernando Ramirez
Crew Launch Vehicle � Falcon 9 Heavy › To carry crew capsule and propellant required to rendezvous with transit vehicle Payload Mass [t] Cost Per Launch Cost per kg of payload 53. 0 $125 Million $2358. 49 Cargo Launch Vehicle 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 Image Credit: http: //www. spacex. com/assets/img/20110405 -falcon-heavy. jpg
![Cargo Missions: Departure � Circular Spiral Out › Constant thrust Parameter Value TOF [days]](http://slidetodoc.com/presentation_image_h2/404a9fe79ae8345c158c65cc3e92abbf/image-3.jpg "Cargo Missions: Departure � Circular Spiral Out › Constant thrust Parameter Value TOF [days]")
Cargo Missions: Departure � Circular Spiral Out › Constant thrust Parameter Value TOF [days] 350 Mo[t]* 113 Mp[t] 15 Mf[t] 98 *Mo – mass at LEO (350 km)
Cargo Missions: Transit � Various departure dates starting in 2022 › Multiple cargo missions per departure date › 21 Total Cargo Missions Parameter Value TOF [days] 316 Mo[t]* 98 Mp[t] 12 Mf[t]t 87 *Mo – Earth Departure Mass t M – Mars Arrival Mass f
Cargo Dates
![Crew Missions: Departure � Elliptical Spiral Parameter Value TOF [days] 669 Mo[t]* 196 Mp[t]](http://slidetodoc.com/presentation_image_h2/404a9fe79ae8345c158c65cc3e92abbf/image-6.jpg "Crew Missions: Departure � Elliptical Spiral Parameter Value TOF [days] 669 Mo[t]* 196 Mp[t]")
Crew Missions: Departure � Elliptical Spiral Parameter Value TOF [days] 669 Mo[t]* 196 Mp[t] 37. 3 Mf[t] 158. 7 *Mo – mass at LEO (350 km) � Electric Propulsion Parameter Value Power 1. 65 k. W Thrust 35 N Thrust for Decay orbit 1. 78 N Isp 4000 s Samantha Rieger
![Crew Launch Dates Mission Earth Departure Mars Arrival Date V∞ [km/s] ΔV [km/s] Date](http://slidetodoc.com/presentation_image_h2/404a9fe79ae8345c158c65cc3e92abbf/image-7.jpg "Crew Launch Dates Mission Earth Departure Mars Arrival Date V∞ [km/s] ΔV [km/s] Date")
Crew Launch Dates Mission Earth Departure Mars Arrival Date V∞ [km/s] ΔV [km/s] Date V∞ [km/s] Vp [km/s] A/1 12/06/2026 4. 86 1. 190 06/04/2027 5. 83 7. 625 2 01/14/2029 4. 80 1. 146 07/13/2029 5. 34 7. 257 3 03/06/2031 4. 80 1. 146 08/25/2031 4. 52 6. 677 4 05/05/2033 3. 50 0. 683 11/01/2033 3. 46 6. 011 5 07/09/2035 3. 47 0. 674 01/05/2036 2. 73 5. 622 6 09/11/2037 4. 87 1. 174 03/10/2038 3. 31 5. 925 7 10/20/2039 5. 00 1. 228 04/15/2040 4. 93 6. 961
LMO Entry Maneuvers Atmospheric Entry c oli b r pe oach y H pr Ap Raise Maneuver Locations Atmospheric Exit Drawing by Monica Pires -- [km/s] V V [km/s] 3. 52 V [km/s] Vcircular [km/s] 3. 45 ΔV ΔV [km/s] 0. 091 0. 088 M Mpp [t] 2. 36 e-3 2. 26 e-3 8
![Crew Missions: Departure � Elliptical Spiral Parameter Value TOF [days] 89. 48 Mo[t]* 29.](http://slidetodoc.com/presentation_image_h2/404a9fe79ae8345c158c65cc3e92abbf/image-9.jpg "Crew Missions: Departure � Elliptical Spiral Parameter Value TOF [days] 89. 48 Mo[t]* 29.")
Crew Missions: Departure � Elliptical Spiral Parameter Value TOF [days] 89. 48 Mo[t]* 29. 5 Mp[t] 4. 05 Mf[t] 25. 45 *Mo – mass at LEO (350 km) � Electric Propulsion Parameter Value Power 850 k. W Thrust 25 N Isp 4900 s Samantha Rieger
Crew A Launch off Mars � Inputs/Assumptions › › › � a = 2. 8 g. Mars m = 105 t Isp = 375 s Constant mass Drag of atmosphere Results › ΔV = 3. 88 km/s › TOF = 404. 1 s
Crew A Return to Earth & Rosie Geeck Stay on Mars TOF Necessary transfer ΔV Actual impulsive ΔV (reduces due to tug) 547 days 180 days 3. 43 km/s 1. 88 km/s
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