Supsersynchronous Transfer Comparison
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A: “Standard” GTO
B: Supersynchronous Transfer
Data
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Launch with apogee at GEO altitude
Launch with apogee above GEO altitude (and optionally higher perigee)
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Initial orbit injection by launch vehicle
Initial orbit injection by launch vehicle
Second transfer orbit (after first burn by spacecraft)
Earth
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Perigee alt200kmPerigee alt3,500kmPerigee alt35,786kmmu3.9860E+05km³/s²
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Apogee alt35,786kmApogee alt90,000kmApogee alt90,000kmR6,378km
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Inclination27degsInclination20degsInclination0degs
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r_pe6,578kmr_pe9,878kmr_pe42,164kmGEO
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r_ap42,164kmr_ap96,378kmr_ap96,378kmAltitude35,786km
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sma24,371kmsma53,128kmsma69,271kmRadius42,164km
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Period37,864secsPeriod121,870secsPeriod181,442secsInclination0degs
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10hours33hours50hoursPeriod86,164secs
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31minutes51minutes24minutes23hours
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4seconds10seconds2seconds56minutes
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v_pe10.24km/sv_pe8.56km/sv_pe3.63km/s4seconds
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v_ap1.60km/sv_ap0.88km/sv_ap1.59km/sSpeed3.07km/s
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Burn 1Burn 1
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Inclination change + circularization burn at GEO altitude
Inclination change + perigee raise to apogee
User input
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Δv1,804m/sΔv819m/sAuto quantities
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Final results
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Burn 2
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TOTAL Δv1,804m/s
Circularization at GEO altitude + remaining inc. change
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Δv552m/s
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TOTAL Δv1,371m/s
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Saving24.0%
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