#Low fidelity instance -- aero_template_l.wgs
    aero_problem_dimensions = AeroProblemDimensions(aero_template_l)                                         
    na = aero_problem_dimensions.na
    na_unique = aero_problem_dimensions.na_unique
    network_info = aero_problem_dimensions.network_info

    #High fidelity instance -- aero_template_h.wgs
    aero_problem_dimensions_h = AeroProblemDimensions(aero_template_h)
    na_h = aero_problem_dimensions_h.na
    na_unique_h = aero_problem_dimensions_h.na_unique
    network_info_h = aero_problem_dimensions_h.network_info

    structure_problem_params = StaticStructureProblemParams(node_id, node_id_all)
    
    #Low fidelity instance -- aero_template_l.wgs
    aero_problem_params = AeroProblemParams(aero_template_l)
    
    #High fidelity instance -- aero_template_h.wgs
    aero_problem_params_h = AeroProblemParams(aero_template_h)

    #Design variable initial values (and other parameters)
    t_0 = 0.05*np.ones(15)

    theta_0 = np.zeros(5)

    # theta_0 = np.ones(n_sec)

    sweep_0 = np.array([26.62107398, 50.40477233, 64.93032268, 26.74549099])

    #X-position of the leading edge at the root
    xr = 50.
Esempio n. 2
0
    s0 = 40000000.0

    structure_problem_dimensions = StaticStructureProblemDimensions()
    aero_problem_dimensions = AeroProblemDimensions()

    ns = structure_problem_dimensions.ns
    ns_all = structure_problem_dimensions.ns_all
    node_id = structure_problem_dimensions.node_id
    node_id_all = structure_problem_dimensions.node_id_all
    n_stress = structure_problem_dimensions.n_stress
    tn = structure_problem_dimensions.tn
    mn = structure_problem_dimensions.mn

    structure_problem_params = StaticStructureProblemParams(
        node_id, node_id_all)
    aero_problem_params = AeroProblemParams()

    na = aero_problem_dimensions.na
    network_info = aero_problem_dimensions.network_info

    node_coord = structure_problem_params.node_coord
    node_coord_all = structure_problem_params.node_coord_all
    t = structure_problem_params.t
    m = structure_problem_params.m

    apoints_coord = aero_problem_params.apoints_coord

    top = Problem()
    top.root = root = Group()
    #==============================================================================
    #     UNCOMMENT JUST FOR SLSQP OPTIMIZER