Problem with Aerostructural optimzation of wing

[Aming12-01]

I am currently working on an aero-structural optimization problem for an aircraft wing using OpenMDAO and the MPhys framework. The code involves setting up a multipoint optimization problem with both aerodynamic and structural analyses. The script is adapted from a tutorial on GitHub for aero-structural optimization, but the tutorial did not include constraints and objective function definitions.

The optimization script runs, but I am encountering issues:

No Mesh Deformation: Despite running the optimization, there is no visible mesh deformation.
No Drag Reduction: The objective function is set to minimize drag, but there is no observed reduction in drag.
Observations
The tutorial did not include the constraints and objective function definitions, which I have attempted to add.
the model i am trying to optimize is very simple can you please guide me to solve this problem

this is my attempt to add constraints and objectives

Create reference axis

    nRefAxPts = self.geometry.nom_addRefAxis(name="wing", xFraction=0.25, alignIndex="k")
    nTwist = nRefAxPts - 1

    # Set up global design variables
    def twist(val, geo):
        for i in range(1, nRefAxPts):
            geo.rot_y["wing"].coef[i] = val[i - 1]

    self.geometry.nom_addGlobalDV(dvName="twist", value=np.array([0] * nTwist), func=twist)
    nLocal = self.geometry.nom_addLocalDV(dvName="thickness", axis="z")
    
    # setup the volume and thickness constraints
    leList = [[0.1, 0.001, 0], [0.1, 9.8, 0]]
    teList = [[2.3, 0.001, 0], [2.3, 9.8, 0]]
    
    self.geometry.nom_addThicknessConstraints2D("thickcon", leList, teList, nSpan=10, nChord=10)
    self.geometry.nom_addVolumeConstraint("volcon", leList, teList, nSpan=10, nChord=10)
    
    # add the LE/TE constraints
    self.geometry.nom_add_LETEConstraint("lecon", volID=0, faceID="iLow")
    self.geometry.nom_add_LETEConstraint("tecon", volID=0, faceID="iHigh")

    
   
    # add dvs to ivc and connect
    self.dvs.add_output("aoa0", val=aoa0, units="deg")
    self.dvs.add_output("aoa1", val=aoa0, units="deg")        
    self.dvs.add_output("local", val=np.array([0] * nLocal))
    self.dvs.add_output("twist", val=np.array([0] * nTwist))


    
    self.connect("twist", "geometry.twist")      
    self.connect("local", "geometry.thickness")        
    self.connect("aoa0", ["cruise.coupling.aero.aoa", "cruise.aero_post.aoa"])
    self.connect("aoa1", ["maneuver.coupling.aero.aoa", "maneuver.aero_post.aoa"])


    # define the design variables
    self.add_design_var("aoa0", lower=0.0, upper=10.0, scaler=0.1, units="deg")
    self.add_design_var("aoa1", lower=0.0, upper=10.0, scaler=0.1, units="deg")        
    self.add_design_var("local", lower=-0.05, upper=0.05, scaler=10)
    self.add_design_var("twist", lower=-10.0, upper=10.0, scaler=10)

    # add constraints and the objective
    self.add_constraint("cruise.aero_post.cl", equals=0.5, scaler=10.0)
    self.add_constraint("geometry.thickcon", lower=1.0, scaler=1.0)
    self.add_constraint("geometry.volcon", lower=1.0, scaler=1.0)
    self.add_constraint("geometry.tecon", equals=0.0, scaler=1.0, linear=True)
    self.add_constraint("geometry.lecon", equals=0.0, scaler=1.0, linear=True)
    self.add_objective("cruise.aero_post.cd", scaler=100.0)
    self.add_objective("maneuver.aero_post.cd", scaler=100.0)