RocketDatabase

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   Load the properties for a rocket: mS, thrust, ISP, exhaust velocity.
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   Form:
   d = RocketData( name )
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   Inputs
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   name           (:)     Name of the rocket

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   Outputs
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   d              (.)        Data structure with fields:
                   .mTotal       (1)     Total mass of fueled rocket    (kg)
                   .mS          (1,N)    Total mass of each stage       (kg)
                   .mSS         (1,N)    Structural mass of each stage  (kg)
                   .mSP         (1,N)    Propellant mass of each stage  (kg)
                   .eS          (1,N)    Structural Ratio of each stage
                   .pS          (1,N)    Payload Ratio of each stage
                   .uE          (1,N)    Exhaust velocity of each stage (km/s)
                   .ISP         (1,N)    Specific impulse of each stage (s)
                   .thrust      (1,N)    Thrust of each stage           (kN)

   mTot           (1)        Total mS of fueled rocket.

   See also OptimalPayloadRatio, MSVRatio
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   References:   Weisel, "Spaceflight Dynamics", 2nd Edition.
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