Path: StraightLine/StraightLine
% Payload fraction demo for a variety of reference missions Find the mass-optimal exhaust velocity for a Jupiter mission given other engine parameters. Our nominal engine has a specific power of 1000 W/kg, a thrust efficiency of 0.4, and a tank structural fraction of 0.05. Our exhaust velocity is in the neighborhood of 100 to 150 km/s. Changing the specific power or efficiency will have a large effect on the payload fraction. See also: ComputePayloadFraction, OptimalExhaustVelocity, Straight2DStructure
StraightLine: Straight2D/ComputePayloadFraction StraightLine: Straight2D/OptimalExhaustVelocity StraightLine: Straight2D/Straight2DStructure StraightLine: Straight2D/ZeroPayloadTime Common: Database/Constant Common: Graphics/Plot2D Common: Graphics/TimeLabl
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