Path: Orbit/Optimization
% Size a spacecraft from acceleration time history
The acceleration and time is typically an output of the orbit
optimization. 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.
Creates a plot of the thrust, mass, and power over time.
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Form:
sC = SpacecraftFromAccel; % data structure for input
out = SpacecraftFromAccel( sC, s )
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Inputs
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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 (0-1)
.eff (1,1) Engine thrust efficiency (0-1)
s (.)
.a (3,:) Acceleration profile (km/s^2)
.t (1,:) Times corresponding to a
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Outputs
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out (.)
.DV (1,1) Total delta-V (km/s)
.p (1,1) Engine power (W)
.m0 (1,1) Initial mass (kg)
.mP (1,1) Payload mass (kg)
.mE (1,1) Engine mass (kg)
.mF (1,1) Fuel mass (kg)
.mS (1,1) Structural mass (kg)
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Propulsion: Rocket/RocketMass Common: Graphics/Plot2D Common: Graphics/TimeLabl Math: Linear/Mag
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