# Mass system setup

# Mass of aircraft minus pilot and motor
mass {
   name           = fuselage_wings
   mass           = 555.0
   inertia        = [ 3300.0  1200.0 5000.0 ]
   position       = [ 0.0  0.0 0.0 ]
}

# Pilot's mass, assume no inertia 
mass {
   name           = pilot
   mass           = 85.0
   position       = [   1.2    -0.4    0.0 ]
}

# Copilot mass, assume no inertia 
mass {
   name           = copilot
   mass           = 1.0
   position       = [   1.2    0.8    0.0 ]
}

fuel {
   name           = fueltank
   position       = [    0.0    0.0    0.0 ]
   capacity       = 80.0
   y_inner        = 3.5
   y_outer        = 8.8

   default_level  = 80.0
   tank_number    = 1
}

