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unkn. / guesstim.
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Summary, Falcon 9 ReusableSummary
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Payload (300x1500 80°), kg816This is a simulation of the CASSIOPE launch with the purpose of figuring out if it would be possible to send the Falcon 9 Upper Stage (only) on a fly-by mission of Mars (no orbit). Result: It will not (using C3 number)
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Stage 1 RTLS delta-v, m/s3,635Reused
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Stage 2 RTLS delta-v, m/s1,980
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Payload TMI, kg0
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StackLaunch from Earth, Reusable Editionhttp://www.silverbirdastronautics.com/LaunchMethodology.pdf
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Total mass, lbs1,115,200
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Thrust at liftoff1,323,000Acceleration @ MECO1, Gee4.09Lunch latitude, deg28
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Thrust / weight ratio1.22MECO1 time after launch, s163.00Orbital inclination, deg80Earth Mass5.97E+24
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Mass, stage 1, lbs886,209Mass post MECO1, lbs323,175Orbital altitude, km3001500Gravitational Const6.67E-11
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Mass, stage 2, lbs200,000Delta-v from stage1 burn3,357Ascent time, s532.0608347ApproxEarth Radius6371000
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Mass, payload, lbs1,800Tmix493.1486387Standard Gravity9.80665
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Total mass, check, lbs1,088,009Stage separation time, s14K3, eq 51020.66ISP282
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Gravity loss, stage separation-137K4, eq 52.03739Acceleration at launch11.92471565
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Vpen, eq 52025.396105
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Stage 1, including interstageAcceleration @ MECO2, Gee10.90Vcirc7725.99837http://en.wikipedia.org/wiki/Orbital_speed
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Total thrust, 9x Merlin 1D, lbf1,323,000MECO2 time after launch, s532.06Vrot71.11720807
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Total thrust, 9x Merlin 1D, N5,884,997Mass post MECO2, lbs16,521
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Average isp, sl282Delta-v from stage2 burn8,467Delta-V Required (eq 3)9,680
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Average isp, vac320
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Wet mass, lbs886,209Total delta-v 11,687
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Dry/wet ratio4.00%Delta-v from 300x300 circ to 300x1500312.45http://en.wikipedia.org/wiki/Hohmann_transfer_orbit
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Dry mass, lbs35,448Delta-v margin1,694C3 energy trajectory 16
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Fuel mass, lbs850,761385836.9655Velocity needed in LEO at perigee, m/s11,635.38http://design.ae.utexas.edu/mission_planning/mission_resources/orbital_mechanics/DV_versus_C3_Writeup.pdf
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Ratio residual (RTLS, ullage, etc)10.1%Delta-v from 300x300 needed for hohmann TMI 3,909
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Fuel for RTLS, lbs85,927Margin for TMI / Earth departureAdditional delta-v needed for TMI3,597
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RTLS delta-v capacity, m/s3,635Mass of TMI stack, lbs25,843
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Fuel for ascent, kg346,867Fuel for TMI, lbs6,521
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Total fuel burn rate, kg/s2,128Residual fuel (not possible to use)1,918Delta-v from 300x300 circ to 300x15002,248.22http://en.wikipedia.org/wiki/Hohmann_transfer_orbit
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Burn time, s163.00Mass post MECO3, lbs10,502C3 energy trajectory for Mars, departure on September 9th, km2/s29
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Delta-v potential (until "depletion"), m/s3,047Velocity needed in LEO at perigee, m/s11,330.58http://design.ae.utexas.edu/mission_planning/mission_resources/orbital_mechanics/DV_versus_C3_Writeup.pdf
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Delta-v from 300x300 needed for Earth Departure, C3 = 93,605
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Stage 2Delta-v margin for TMI, C3 = 53-550Additional delta-v needed for earth departure1,356
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Total thrust, 1x Merlin 1D Vac, lbf180000Delta-v margin for C3 = 91,690
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Total thrust, 1x Merlin 1D Vac, N800,680
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Average isp, vac345
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Wet mass, lbs200,000
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Dry/wet ratio4.10%
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Dry mass, lbs8,200
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Fuel mass, lbs191,800
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Ratio Fuel for extra mission (TMI?)3.4%
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Fuel for extra mission (TMI?)6,521
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RTLS delta-v capacity, m/s1,980
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Fuel for ascent, kg84,028
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Total fuel burn rate, kg/s237
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Initial burn time, s355
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Payload
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Mass of payload, lbs1,800
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Mass of payload, kg816
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Mass of Mars Sattelite, kg0
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Mass of Mars Sattelite, lbs0
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Mass of mounting hw, kg174
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Mass of mounting hw, lbs384
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Constants
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Standard Gravity9.81
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lbf/N4.4482216
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lbs/kg0.45352
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