Path: Propulsion/Rocket
% Compute masses for a single stage to produce the required delta-v.
The structural fraction will limit the achievable delta-v.
Type RocketMass for a demo of a LH2/LO2 rocket.
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Form:
[mF, mT, mS, e] = RocketMass( Isp, mP, fS, dV )
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Inputs
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Isp (1,1) Specific impulse (sec)
mP (1,1) Payload mass (kg)
fS (1,1) Structural fraction
dV (1,:) Required delta v (km/sec)
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Outputs
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mF (1,:) Fuel mass (kg)
mT (1,:) Total mass (kg)
mS (1,:) Structural mass (kg)
e (1,:) Payload fraction
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Reference: Wiesel, W. E., Spaceflight Dynamics, McGraw-Hill, 1988,
p. 187.
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Common: Graphics/Plot2D
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