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What is the mass capacity for the Delta IV Heavy for a trans-lunar injection? Or is there a way to take its capacity to GEO or LEO and substitute it into a formula which would bring the approximate capacity for a trans-lunar injection?

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According to John Schilling's calculator, Delta IV Heavy should be able do about 9.8 tons to TLI (defined as a 185km perigee, 400000km apogee Earth orbit).

Because of the nonlinearity of the rocket equation and wide range of launcher performance characteristics, there's not a general rule for estimating TLI capacity from LEO or GEO capacity, unfortunately.

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