def setup(self):
indeps = self.add_subsystem('indeps', IndepVarComp(), promotes=['*'])
indeps.add_output('Diameter_stage_1',4.6)
indeps.add_output('Diameter_stage_2',4.6)
indeps.add_output('Mass_flow_rate_stage_1',219.)
indeps.add_output('Mass_flow_rate_stage_2',219.)
indeps.add_output('Thrust_stage_1',1000.)
indeps.add_output('Thrust_stage_2',1150.)
indeps.add_output('Pc_stage_1',100.)
indeps.add_output('Pc_stage_2',100.)
indeps.add_output('Pe_stage_1',1.)
indeps.add_output('Pe_stage_2',1.)
indeps.add_output('OF_stage_1',2.7)
indeps.add_output('OF_stage_2',2.7)
indeps.add_output('N_eng_stage_1',7.)
indeps.add_output('N_eng_stage_2',1.)
indeps.add_output('Prop_mass_stage_1',350000.)
indeps.add_output('Prop_mass_stage_2',75000.)
indeps.add_output('Pdyn_max_dim',40.)
indeps.add_output('thetacmd_i',2.72)
indeps.add_output('thetacmd_f',20.)
indeps.add_output('ksi',0.293)
indeps.add_output('Pitch_over_duration',5.)
indeps.add_output('Exit_nozzle_area_stage_1',0.5)
indeps.add_output('Exit_nozzle_area_stage_2',0.5)
indeps.add_output('Delta_vertical_phase',10.)
indeps.add_output('Delta_theta_pitch_over',1.)
indeps.add_output('is_fallout',1.)
indeps.add_output('command_stage_1_exo',np.array([1.,1.]))
cycle = self.add_subsystem('cycle', Group(), promotes=['*'])
Propu = cycle.add_subsystem('Propu', Propulsion.Propulsion_Comp(),promotes_inputs=['Pc_stage_1','Pe_stage_1',
'OF_stage_1','Pc_stage_2','Pe_stage_2','OF_stage_2'],
promotes_outputs=['Isp_stage_1','Isp_stage_2'])
Struct_1 = cycle.add_subsystem('Struct_1', Dry_Mass_stage_1.Dry_Mass_stage_1_Comp(),
promotes_inputs=['Diameter_stage_1','OF_stage_1',
'N_eng_stage_1','Diameter_stage_2','Isp_stage_1','Prop_mass_stage_1',
'Thrust_stage_1','Pdyn_max_dim'],
promotes_outputs=['Dry_mass_stage_1'])
Struct_2 = cycle.add_subsystem('Struct_2', Dry_Mass_stage_2.Dry_Mass_stage_1_Comp(),
promotes_inputs=['Prop_mass_stage_2'],promotes_outputs=['Dry_mass_stage_2'])
Aero = cycle.add_subsystem('Aero', Aerodynamics.Aerodynamics_Comp(),promotes_outputs=['Table_CX_complete_ascent',
'Mach_table','AoA_table','CX_fallout_stage_1','CZ_fallout_stage_1',])
Traj = cycle.add_subsystem('Traj', Trajectory.Trajectory_comp(),
promotes_inputs=['Diameter_stage_1','Diameter_stage_2','Mass_flow_rate_stage_1',
'Mass_flow_rate_stage_2','N_eng_stage_1','N_eng_stage_2',
'OF_stage_1','OF_stage_2','Isp_stage_1','Isp_stage_2',
'Prop_mass_stage_1','Prop_mass_stage_2','Dry_mass_stage_1',
'Dry_mass_stage_2','Pitch_over_duration','thetacmd_i',
'thetacmd_f','ksi','Exit_nozzle_area_stage_1','Exit_nozzle_area_stage_2',
'Delta_vertical_phase','Delta_theta_pitch_over','Table_CX_complete_ascent',
'Mach_table','AoA_table','command_stage_1_exo','CX_fallout_stage_1','CZ_fallout_stage_1','is_fallout'],
promotes_outputs=['T_ascent','alt_ascent','flux_ascent','r_ascent',
'V_ascent','theta_ascent','alpha_ascent','nx_ascent','alpha_cont',
'Nb_pt_ascent','m_ascent','CX_ascent','GLOW',
'lat_ascent','gamma_ascent','longi_ascent','thrust_ascent',
'mass_flow_rate_ascent','Mach_ascent','pdyn_ascent',
'rho_ascent','distance_ascent','state_separation_stage_1',
'max_pdyn_load_ascent_stage_1',\
'T_fallout','alt_fallout','flux_fallout','r_fallout',
'V_fallout','theta_fallout','alpha_fallout','nx_fallout',
'Nb_pt_fallout','m_fallout','CX_fallout',
'lat_fallout','gamma_fallout','longi_fallout','thrust_fallout',
'mass_flow_rate_fallout','Mach_fallout','pdyn_fallout',
'rho_fallout','distance_fallout',])
