Path: Orbit/StraightLine
% Size a spacecraft from acceleration data
Some combinations of parameters will not converge and the mission will
be impossible for the given maximum acceleration, which is used to
compute the maximum thrust and therefore the power plant size. You will
get an error if it does not converge.
Payload mass includes everything that is not engine, fuel or fuel tanks.
This does not have any outputs, it just draws a plot.
--------------------------------------------------------------------------
Form:
SpacecraftFromAccel( sC, s )
--------------------------------------------------------------------------
------
Inputs
------
sC (.)
.uE (1,1) Exhaust velocity (km/s)
.sigma (1,1) Specific power (W/kg)
.mP (1,1) Payload mass (kg)
.fS (1,1) Fuel structural fraction
.eff (1,1) Engine thrust efficiency
s (.)
.a (3,:) Acceleration profile (km/s^2)
.t (1,:) Times corresponding to a
--------------------------------------------------------------------------
Propulsion: Rocket/RocketMass Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Common: Graphics/TimeLabl Math: Linear/Mag
Back to the Orbit Module page