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Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. [email protected]
A Mars Heavy Transport Architecture
Using Existing Launchers and Technology
Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. [email protected]
Existing « throw capacity » to a direct Trans Mars Injection (C3 = 10 km2/s2)
Delta-IV Heavy Ariane V Proton / cryo[1] Proton/ Briz[2]
Payload after TMI: 8,000[3] 5,900[4] 5’800[5] 4,580[6] Kg
[1] Assumes developing a new cryogenic upper stage for the Proton, with same dry mass as the Briz-M.[2] Using the 327s isp Briz-M upper stage[3] Delta IV Heavy Demo brochure[4] Derived from GTO payload data[5] Derived from Briz-M payload data[6] Proton Launch System Mission Planner’s Guide, page 2-23
Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. [email protected]
Potential payload to Trans Mars Injection using a space tug for orbit raising from 400 x 400 km orbit to 400 x 300,000 km departure orbit (C3 = 10 km2/s2)
Delta-IV Heavy Ariane V Proton / cryo Proton / Briz
Payload after TMI: 17,600[1] 16,400 16’000[1]14,600[1]
kg
[1] Additional air drag due to increased payload fairing to 5.4m diameter
Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. [email protected]
Standard Delta-IV Fairing Proposed configuration
Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. [email protected]
Standard Delta-IV Fairing Proposed configuration
Mars entry aeroshell
Payload adaptor and cryogenic cooling system
Upper stage modified for cryogenic cooling of propellants
Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. [email protected]
Orbital Transfer Tug
3,500 m2 SLASR solar arrays
Propulsion Module equiped with several NEXT ion drives (13.3 tons)
Jettisoneable Propellant Tank (7.1 tons)
Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. [email protected]
Low Earth Orbit
Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. [email protected]
Low Earth Orbit to Earth Departure Orbit
Earth
LEO
Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. [email protected]
Low Earth Orbit to Earth Departure Orbit
Earth
LEO
Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. [email protected]
Low Earth Orbit to Earth Departure Orbit
Earth
LEO
Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. [email protected]
Low Earth Orbit to Earth Departure Orbit
Earth
LEO
Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. [email protected]
Low Earth Orbit to Earth Departure Orbit
Earth
LEO
Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. [email protected]
Low Earth Orbit to Earth Departure Orbit
Earth
LEO
Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. [email protected]
Low Earth Orbit to Earth Departure Orbit
Earth
LEO
Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. [email protected]
Low Earth Orbit to Earth Departure Orbit
Earth
LEO
Departure Orbit
Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. [email protected]
Earth Departure Orbit
Direct launch crew transfer capsule
Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. [email protected]
Space tug orbit lowering by multiple atmospheric passes
Earth
LEO
Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. [email protected]
Space tug Orbit lowering by multiple atmospheric passes
Earth
LEO
Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. [email protected]
Space tug Orbit lowering by multiple atmospheric passes
Earth
LEO
Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. [email protected]
Space tug Orbit lowering by multiple atmospheric passes
Earth
LEO
Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. [email protected]
Space tug Orbit lowering by multiple atmospheric passes
Earth
LEO
Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. [email protected]
Space tug Orbit lowering by multiple atmospheric passes
Earth
LEO
Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. [email protected]
Space tug Orbit lowering by multiple atmospheric passes
Earth
LEO
Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. [email protected]
Mars Capture Orbit
Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. [email protected]
Mars Capture Orbit
Mars
1 sol period capture orbit
250 x 33,793 km
Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. [email protected]
Transfer data: best 180-day opportunities from 2001 to 2039
Date Departure C3 Arrival C3 Departure dV Arrival dV Entry V TOF
(km2/s2) (km2/s2) (km/s) (km/s) (km/s) (days)
17.03.2001 8.65 22.27 0.53 1.90 6.53 180.00
05.06.2003 9.20 9.00 0.56 0.84 5.47 180.00
09.08.2005 16.52 13.80 0.90 1.24 5.87 180.00
28.09.2007 20.80 26.50 1.09 2.21 6.84 180.00
28.10.2009 20.20 44.38 1.06 3.38 8.00 180.00
02.12.2011 15.91 49.85 0.87 3.70 8.33 180.00
06.01.2014 11.09 44.16 0.65 3.36 7.99 180.00
20.02.2016 8.88 28.45 0.55 2.34 6.97 180.00
06.05.2018 8.13 10.85 0.51 1.00 5.63 180.00
19.07.2020 13.63 10.85 0.77 1.00 5.63 180.00
08.09.2022 19.69 22.09 1.04 1.89 6.52 180.00
17.10.2024 21.57 40.90 1.12 3.16 7.79 180.00
17.11.2026 17.92 50.47 0.96 3.74 8.37 180.00
21.12.2028 13.50 54.37 0.76 3.96 8.59 180.00
31.01.2031 9.28 35.98 0.56 2.85 7.48 180.00
06.04.2033 8.42 14.92 0.52 1.34 5.97 180.00
25.06.2035 10.47 8.48 0.62 0.79 5.42 180.00
24.08.2037 17.76 15.47 0.95 1.38 6.01 180.00
03.10.2039 21.00 31.83 1.10 2.57 7.20 180.00
Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. [email protected]
Payload to LEO (400 x 400 km orbit)
Delta-IV H Ariane V Proton/cryo Proton/Briz
Payload to LEO 22,560
21,000
22,200 * 21,600 kg
5.4m fairing penalty 326
-
2,118 2,118 kg
New payload to LEO 22,234
21,000
20,082 19,482 kg
Payload + upper stage 26,269
25,838
22,849 22,248 kg
Refrigeration system 426
285
345 - kg
Payload adapter 589
557
532 516 kg
=> Additional mass 1,015
842
877 516 kg
Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. [email protected]
Results: Gross payload mass to MOC including aeroshell
Date Delta-IV H Ariane V Proton/cryo Proton/Briz
17.03.2001 17'896 16'731 16'307 14'922 kg
05.06.2003 17'766 16'599 16'193 14'775 kg
09.08.2005 16'128 14'942 14'769 12'955 kg
28.09.2007 15'245 14'050 14'001 11'998 kg
28.10.2009 15'366 14'172 14'106 12'128 kg
02.12.2011 16'258 15'073 14'882 13'098 kg
06.01.2014 17'327 16'154 15'811 14'282 kg
20.02.2016 17'841 16'676 16'259 14'861 kg
06.05.2018 18'020 16'856 16'414 15'063 kg
19.07.2020 16'755 15'575 15'314 13'645 kg
08.09.2022 15'469 14'276 14'196 12'239 kg
17.10.2024 15'092 13'895 13'868 11'833 kg
17.11.2026 15'834 14'644 14'513 12'634 kg
21.12.2028 16'783 15'604 15'339 13'677 kg
31.01.2031 17'747 16'580 16'177 14'754 kg
06.04.2033 17'950 16'786 16'354 14'984 kg
25.06.2035 17'469 16'299 15'936 14'442 kg
24.08.2037 15'867 14'678 14'542 12'670 kg
03.10.2039 15'205 14'009 13'966 11'955 kg
Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. [email protected]
Results: Net mass to MOC without aeroshell mass (~3.5 tons)
Date Delta-IV H Ariane V Proton/cryo Proton/Briz
17.03.2001 14'297 13'179 12'771 11'442 kg
05.06.2003 14'286 13'158 12'766 11'396 kg
09.08.2005 12'664 11'520 11'354 9'605 kg
28.09.2007 11'724 10'579 10'532 8'613 kg
28.10.2009 11'733 10'597 10'535 8'653 kg
02.12.2011 12'551 11'426 11'245 9'550 kg
06.01.2014 13'600 12'484 12'158 10'703 kg
20.02.2016 14'197 13'082 12'683 11'344 kg
06.05.2018 14'514 13'391 12'964 11'659 kg
19.07.2020 13'292 12'154 11'902 10'290 kg
08.09.2022 11'969 10'823 10'746 8'867 kg
17.10.2024 11'492 10'352 10'326 8'388 kg
17.11.2026 12'144 11'015 10'891 9'107 kg
21.12.2028 13'024 11'906 11'655 10'079 kg
31.01.2031 14'054 12'940 12'556 11'197 kg
06.04.2033 14'410 13'289 12'873 11'553 kg
25.06.2035 14'004 12'873 12'521 11'077 kg
24.08.2037 12'399 11'254 11'123 9'320 kg
03.10.2039 11'653 10'510 10'468 8'545 kg
Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. [email protected]
Manned mission to Mars orbit
Example manned habitat: Destiny with 5 basic racks = 14.5 tons
Minimum consumables for 3 persons for 180 days = 2.4 tons
Rough estimation for a 3-person habitat to Mars = 17.7 tons
Activities in Mars orbit:
1. Explore the Moons of Mars
2. Remote-control surface robots for in situ resource exploitation (prepare base and manned ascent vehicle)
3. Land on the surface
Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. [email protected]
Getting down to the surface
Problem: Ballistic Coefficient is too high (560 kg/m2)
Solution: Raise Drag Coefficient, enlarge drag area
Standard aeroshell(works only for relatively light
payloads)
Large heatshield in front of payload
Light aeroshell and hypersonic parachute
Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. [email protected]
Results: Useful payload on the martian surface
- Depends on the atmospheric entry solution chosen
- Chemical thrust delta-v may vary between 600 m/s and 1,400 m/s depending on the solution
- Considering LOX/LH thrusters, final useful surface payload may vary between 30% and 50% of the atmospheric entry mass:
Delta-IV Heavy Ariane V Proton / cryo Proton / Briz
Useful payload on surface:
5.3 to 8.8 tons 4.9 to 8.2 tons 4.8 to 8.0 tons4.4 to 7.3 tons
Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. [email protected]
Conclusions
1. Light manned missions to Mars orbit can be made possible using existing launchers and technology
Requirements:
- Modifying upper stages for cryogenic cooling
- Developing an ion-driven space tug
- Developing a 5.4m Mars aeroshell
- Man-rating a heavy launcher to launch the CEV to 400 x 300,000 km
1. Manned missions to the martian surface may be possible using existing launchers provided certain new technologies are developed
Further requirements:
- Hypersonic parachutes
- Highly autonomous robots for surface activity
- Practical and lightweight LOX/LH extraction from martian water
Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. [email protected]
Thank you for your attention
Presented by Marco Christov at the 11th Mars Society Annual Convention, 14 – 17 August 2008, Boulder Colorado. [email protected]
Appendix: Orbital Transfer Tug Variations
Delta-v: 3.46 km/sPayload: 26.3 tons
Can be launched with existing launcher
Propulsion ISP (s) Wet Mass (tons) Dry Mass (tons)
NTO/MMH 327
86.0
8.1
LOX/LH 462
49.8
6.9
Nuclear Thermal 940
26.9
8.7
Ion drive 3940
20.3
15.3
