
simulation = 
  (initial_conditions = (u         = 0.0,
			 v         = 0.0,
			 w         = 0.0,
			 P         = 0.0,
			 Q         = 0.0,
			 R         = 0.0,
			 latitude  = 0.0,
			 longitude = 0.0,
			 altitude  = 0.0,
			 phi       = 0.0,
			 theta     = 89.0,
			 psi       = 0.0
			),
   rocket = (stage = (dry_mass        = 1000., # (Head)
	              Ix              = 4390.,
	              Iy              = 318245.,
	              Iz              = 318245.,
	              Cd              = 0.15,
	              Cd_data_file    = "V2drag.dat",
	              CL              = 0.1,
	              CB              = 0.1,
	              Cspin           = 20.0,
	              Cmoment         = 6.32,
	              Cdamping        = 31.6,
	              Diameter        = 1.65,
	              # this is the total duration during which the
	              # stage is active, i.e. from the time the previous 
	              # stage were drop until this stage is drop.
	              active_time     = 1000.0,
                      engine = (thrust          = 250000.0,
                                thrust_data_file = "V2thrust.dat",
	                        propellant_mass = 8935.,
				dry_mass        = 2965.,
	                        mass_flow       = 0.1,
				start_time      = 0.0,
				burn_time       = 65.,
				drop_time       = 65.0,
				position        = (x = -1.0,
                                                   y =  0.0,
                                                   z =  0.0),
                                direction       = (x =  1.0,
                                                   y =  0.0,
					           z =  0.0)
			       )
                     )
              )
  ,solution = (duration  = 100.0,
               dt        = 0.1,
               precision = 0.01)
  )




