TSTOOptimization:

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   Size a horizontal launch/horizontal landing two stage to orbit vehicle.
   The mission is

   Stage 0 (Stages 1 and 2 combined)
   ---------------------------------
   Takeoff roll
   Liftoff
       Both performed by Takeoff.m
   2 segment piecewise constant angle climb
       Performed by TurboRamjetSimForOptGamma.m

   Stage 1
   -------
   Descent
       Constant level flight at 10000 m
   Landing
       No fuel or mass required

   Stage 2
   -------
   Insertion into transfer orbit (2 segments with piecewise constant flightpath angles)
       RocketSim.m
   Insertion into circular orbit
       Impulsive Circularization Burn
   Reentry interface burn
       DVReentry.m
   Gliding reentry
       No fuel needed or mass consumed
   Landing
       No fuel or mass Consumed

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   Form:
   [f,cineq,ceq] = TSTOOptimization( X )
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   ------
   Inputs
   ------
   X               (1,n) Optimization Variables

   -------
   Outputs
   -------
   f               (1,1) Objective function (kg of payload to orbit)
   ceq             (1,m) Value of the equality constraints
   cineq           (1,p) Value of the inequality constraints

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Children:

Common: General/StdAtm
Common: Math/Mag
Orbit: OrbitManeuver/DVReentry
Propulsion: Airbreathing/Turbofanramjet
Propulsion: Chemical/RocketH2
SC: BasicOrbit/El2RV
SC: BasicOrbit/RV2El
SC: BasicOrbit/VOrbit
SCPro: AirbreathingVehicle/ComputeAlphaConstantFlightPathAngle
SCPro: AirbreathingVehicle/SimpleLiftAndDrag
SCPro: AirbreathingVehicle/Takeoff
SCPro: AirbreathingVehicle/TurboRamjetSim
SCPro: DynamicalModels/RocketSim