Path: Orbit/StraightLine

% Compute thrust for a minimum mass trajectory, with a fixed uE
 The power is calculated from the thrust and thrust efficiency.
 The engine mass is calculated from the specific power.

   P  = 0.5 T*uE/eta
   mE = P/sigma

 The total mass is

   m0 = mP + (1 + f)*mF + mE

 where mP is the mass of the payload, f is the fuel structural fraction, 
 and mE is the mass of the engine.

 Type StraightLineOptimalFixedUE for a demo.
   d = StraightLineOptimalFixedUE( d0 )

   d0     	(.)   Data structure
                 See StraightLineDataStructure

   d        (.)  Results data structure
                 .thrust (1,1) Thrust (N)
                 .p      (1,1) Power       (W)
                 .mD     (1,1) Dry mass    (kg)
                 .mF     (1,1) Fuel mass   (kg)
                 .dV     (1,1) Delta-V     (km/s)
                 .dF     (1,1) Final distance achieved (km)
                 .vF     (1,1) Final velocity achieved (km/s)
                 .tS     (1,1) Switch time

   See also StraightLineConstantThrust


AC: ACData/ACTConstants
Orbit: StraightLine/SimulateStraightLineTrajectory
Orbit: StraightLine/StraightLineConstantThrust
Orbit: StraightLine/StraightLineDataStructure
Orbit: StraightLine/SwitchTime
Orbit: StraightLine/UToMF
SC: SCData/sCTConstants
Common: CommonData/Constants
Common: CommonData/SwooshWatermark
Common: CommonData/xSplashSmall
Common: Database/Constant
Common: General/CellToMat
Common: General/DeleteCell
Common: General/MatToCell
Common: General/Watermark
Common: Graphics/DistanceLabel
Common: Graphics/NewFig
Common: Graphics/Plot2D
Common: Graphics/PltStyle
Common: Graphics/TimeLabl
Math: Integration/RK4

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