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     = 0.0,
			 psi       = 0.0
			),
   rocket = (stage = (dry_mass        = .1,
	              Ix              = 0.0025,
	              Iy              = 0.84,
	              Iz              = 0.84,
	              Cdrag           = 0.2,
	              Clift           = 2.3,
	              Cbeta           = 2.3,
	              Cspin           = 20.0,
	              Cmoment         = 6.32,
	              Cdamping        = 31.6,
	              Diameter        = 0.1143,
	              # 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     = 2.0,
                      engine = (type            = "constant_thrust",
	                        propellant_mass = 0.1,
				dry_mass        = 0.05,
	                        thrust          = 10.0,
	                        mass_flow       = 0.1,
				start_time      = 0.0,
				burn_time       = 1.5,
				drop_time       = 0.0,
				position        = (x = -1.0,
                                                   y =  0.0,
                                                   z =  0.0),
                                direction       = (x =  1.0,
                                                   y =  0.0,
					           z =  0.0)
			       )
                     ),
             stage = (dry_mass        = .2,
	              Ix              = 0.0025,
	              Iy              = 0.84,
	              Iz              = 0.84,
	              Cdrag           = 0.2,
	              Clift           = 2.3,
	              Cbeta           = 2.3,
	              Cspin           = 20.0,
	              Cmoment         = 6.32,
	              Cdamping        = 31.6,
	              Diameter        = 0.1143,
	              # 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     = 3.0,
                      engine = (type             = "thrust_table_data",
	                        propellant_mass  = 0.2,
				dry_mass         = 0.3,
				thrust_data_file = "thrust.dat",
				c                = 2500.0, #effective exhaust velocity
				start_time       = 0.0,
				burn_time        = 2.0,
				drop_time        = 0.0,
				position         = (x = -1.0,
                                                    y =  0.0,
                                                    z =  0.0),
                                direction        = (x =  1.0,
                                                    y =  0.0,
					            z =  0.0)
			       )
                    )
              )
  ,solution = (duration  = 5.0,
               dt        = 0.01,
               precision = 0.0001)
  )