RocketMass:

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
   ------
   Isp          (1,1) Specific impulse     (sec)
   mP           (1,1) Payload mass         (kg)
   fS           (1,1) Structural fraction 
   dV           (1,:) Required delta v     (km/sec)

   -------
   Outputs
   -------
   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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Children:

Common: Graphics/Plot2D

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