## aidl/airplane/airplane2

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###
CLIP Score: 26.8

    from AIDL import *

    def airplane():
        """
        Create a model of an airplane with basic components: fuselage, wings, and tail.
        """

        airplane = Solid()

        # Define fuselage
        fuselage = Solid()
        airplane.fuselage = fuselage
        fuselage.body = RoundedRectangle((0, 0), 30*inches, 3*inches, 1*inches)

        # Define wings
        left_wing = Solid(shift=(-10*inches, 0))
        right_wing = Solid(shift=(10*inches, 0))
        airplane.left_wing = left_wing
        airplane.right_wing = right_wing

        left_wing.shape = Rectangle((0, 0), 12*inches, 2*inches)
        right_wing.shape = Rectangle((0, 0), 12*inches, 2*inches)

        # Define tail
        horizontal_stabilizer = Solid(shift=(15*inches, 1.5*inches))
        vertical_stabilizer = Solid(shift=(15*inches, -1.5*inches))
        airplane.horizontal_stabilizer = horizontal_stabilizer
        airplane.vertical_stabilizer = vertical_stabilizer

        horizontal_stabilizer.shape = Rectangle((0, 0), 8*inches, 1*inch)
        vertical_stabilizer.shape = Rectangle((0, 0), 1*inch, 4*inches)

        # Position wings relative to fuselage
        airplane.AddConstraint(left_wing.bb.right == airplane.fuselage.bb.left + 5*inches)
        airplane.AddConstraint(right_wing.bb.left == airplane.fuselage.bb.right - 5*inches)
        airplane.AddConstraint(left_wing.bb.vertical_center == fuselage.bb.vertical_center)
        airplane.AddConstraint(right_wing.bb.vertical_center == fuselage.bb.vertical_center)

        # Position tail relative to fuselage
        airplane.AddConstraint(horizontal_stabilizer.bb.left == fuselage.bb.right - 15*inches)
        airplane.AddConstraint(horizontal_stabilizer.bb.vertical_center == fuselage.bb.vertical_center)
        airplane.AddConstraint(vertical_stabilizer.bb.left == fuselage.bb.right - 15*inches)
        airplane.AddConstraint(vertical_stabilizer.bb.vertical_center == fuselage.bb.vertical_center)

        return airplane

    # Solve and render the model.
    with AIDL_2D:
        model = airplane()
    print(model.Solve())
    model.Render()
                    Please write an AIDL program to generate a airplane

    Sure! Let's start by defining the basic structure and hierarchy of the airplane. We'll break it down into several main components: fuselage, wings, tail, and optionally, the cockpit and engines. Initially, these components will be represented as solid structures. Once the structures are defined, we can add the appropriate geometry and constraints.

    Here's the initial setup:

    ```python
    from AIDL import *

    def airplane():
        """
        Create a model of an airplane with basic components: fuselage, wings, and tail.
        """

        # Create the root structure for the airplane.
        airplane = Solid()

        # Define substructures for main components.
        fuselage = Solid()
        wings = Solid()
        tail = Solid()

        # Attach the substructures to the airplane.
        airplane.fuselage = fuselage
        airplane.wings = wings
        airplane.tail = tail

        # Return the root structure
        return airplane

    # Solve and render the model.
    with AIDL_2D:
        model = airplane()
    print(model.Solve())
    model.Render()
    ```

    Now let's proceed step-by-step to add constraints and geometry to each structure.

    1. **Fuselage**: The body of the airplane, generally a long cylinder or streamlined shape.
    2. **Wings**: Attach to the fuselage, with symmetrical left and right parts.
    3. **Tail**: Composed of horizontal and vertical stabilizers, attached to the end of the fuselage.

    Let's add geometry and constraints to the fuselage:

    ```python
    from AIDL import *

    def airplane():
        """
        Create a model of an airplane with basic components: fuselage, wings, and tail.
        """

        airplane = Solid()

        fuselage = Solid()
        wings = Solid()
        tail = Solid()

        airplane.fuselage = fuselage
        airplane.wings = wings
        airplane.tail = tail

        # Define the fuselage as a long rectangle
        fuselage.body = RoundedRectangle((0, 0), 30*inches, 3*inches, 1*inches)

        # Constrain positions of wings and tail relative to the fuselage
        wings.AddConstraint(wings.bb.left == fuselage.bb.left + 10*inches)
        wings.AddConstraint(wings.bb.vertical_center == fuselage.bb.vertical_center)

        tail.AddConstraint(tail.bb.left == fuselage.bb.right - 5*inches)
        tail.AddConstraint(tail.bb.vertical_center == fuselage.bb.vertical_center)

        return airplane

    # Solve and render the model.
    with AIDL_2D:
        model = airplane()
    print(model.Solve())
    model.Render()
    ```

    Next, let's define the geometry for the wings. We'll consider a basic trapezoidal shape for each wing:

    ```python
    from AIDL import *

    def airplane():
        airplane = Solid()

        fuselage = Solid()
        wings = Solid()
        tail = Solid()

        airplane.fuselage = fuselage
        airplane.wings = wings
        airplane.tail = tail

        fuselage.body = RoundedRectangle((0, 0), 30*inches, 3*inches, 1*inches)

        wings.AddConstraint(wings.bb.left == fuselage.bb.left + 10*inches)
        wings.AddConstraint(wings.bb.vertical_center == fuselage.bb.vertical_center)

        tail.AddConstraint(tail.bb.left == fuselage.bb.right - 5*inches)
        tail.AddConstraint(tail.bb.vertical_center == fuselage.bb.vertical_center)

        left_wing = Solid(shift=(-6*inches, 0))
        right_wing = Solid(shift=(6*inches, 0))

        wings.left_wing = left_wing
        wings.right_wing = right_wing

        left_wing.shape = Rectangle((0,0), 12*inches, 2*inches)
        right_wing.shape = Rectangle((0,0), 12*inches, 2*inches)

        return airplane

    # Solve and render the model.
    with AIDL_2D:
        model = airplane()
    print(model.Solve())
    model.Render()
    ```

    Finally, let's define the geometry for the tail. We'll use a combination of horizontal and vertical stabilizers:

    ```python
    from AIDL import *

    def airplane():
        airplane = Solid()

        fuselage = Solid()
        wings = Solid()
        tail = Solid()

        airplane.fuselage = fuselage
        airplane.wings = wings
        airplane.tail = tail

        fuselage.body = RoundedRectangle((0, 0), 30*inches, 3*inches, 1*inches)

        wings.AddConstraint(wings.bb.left == fuselage.bb.left + 10*inches)
        wings.AddConstraint(wings.bb.vertical_center == fuselage.bb.vertical_center)

        tail.AddConstraint(tail.bb.left == fuselage.bb.right - 5*inches)
        tail.AddConstraint(tail.bb.vertical_center == fuselage.bb.vertical_center)

        left_wing = Solid(shift=(-6*inches, 0))
        right_wing = Solid(shift=(6*inches, 0))

        wings.left_wing = left_wing
        wings.right_wing = right_wing

        left_wing.shape = Rectangle((0,0), 12*inches, 2*inches)
        right_wing.shape = Rectangle((0,0), 12*inches, 2*inches)

        horizontal_stabilizer = Solid(shift=(0, -1.5*inches))
        vertical_stabilizer = Solid(shift=(2*inches, 0))

        tail.horizontal_stabilizer = horizontal_stabilizer
        tail.vertical_stabilizer = vertical_stabilizer

        horizontal_stabilizer.shape = Rectangle((0,0), 8*inches, 1*inch)
        vertical_stabilizer.shape = Rectangle((0,0), 1*inch, 4*inches)

        return airplane

    # Solve and render the model.
    with AIDL_2D:
        model = airplane()
    print(model.Solve())
    model.Render()
    ```

    This creates a simple 2D airplane model. The fuselage is a long rounded rectangle, the wings are rectangles attached to the sides, and the tail consists of a horizontal and a vertical stabilizer.

    Feel free to add more details, constraints, or change the shapes according to your needs! If you need any additional features or modifications, please let me know.

    Traceback (most recent call last):
      File "/net/projects/ranalab/jz/aidl/AIDL/generation/backend.py", line 21, in dumbrun
        exec(code, env)
      File "", line 46, in
      File "/net/projects/ranalab/jz/aidl/AIDL/structure.py", line 968, in Solve
        self._pre_solve(system)
      File "/net/projects/ranalab/jz/aidl/AIDL/structure.py", line 917, in _pre_solve
        structure._pre_solve(system)
      File "/net/projects/ranalab/jz/aidl/AIDL/structure.py", line 925, in _pre_solve
        constraint._pre_solve(system)
      File "/net/projects/ranalab/jz/aidl/AIDL/constraints.py", line 182, in _pre_solve
        self.expression._e.constrain(system, name=self.name)
      File "/net/projects/ranalab/jz/aidl/AIDL/expression.py", line 133, in _e
        return self._solver_expr()
      File "/net/projects/ranalab/jz/aidl/AIDL/expression.py", line 175, in _solver_expr
        return self.val[0]._e == self.val[1]._e
      File "/net/projects/ranalab/jz/aidl/AIDL/expression.py", line 133, in _e
        return self._solver_expr()
      File "/net/projects/ranalab/jz/aidl/AIDL/expression.py", line 169, in _solver_expr
        return self.val[0]._e - self.val[1]._e
      File "/net/projects/ranalab/jz/aidl/AIDL/expression.py", line 133, in _e
        return self._solver_expr()
      File "/net/projects/ranalab/jz/aidl/AIDL/expression.py", line 207, in _solver_expr
        return self.val[0]()._solver_expr()
      File "/net/projects/ranalab/jz/aidl/AIDL/structure.py", line 376, in _right
        return self._max_u()
      File "/net/projects/ranalab/jz/aidl/AIDL/structure.py", line 347, in _max_u
        bb = self._bounding_box()
      File "/net/projects/ranalab/jz/aidl/AIDL/structure.py", line 319, in _bounding_box
        raise NonLocalContext(context, self._structure)
    AIDL.feedback.NonLocalContext: .fuselage referenced from .tail.

    Thank you for providing the error log. The issue is related to a constraint in the tail component that references the fuselage's bounding box, which crosses the contextual boundary. In AIDL, constraints can only reference geometry or structures within the subtree of the structure they are added to.

    To fix this, we need to avoid using constraints that directly reference the bounding box coordinates of the fuselage from within the tail structure. Instead, we need to set up the relative positions of the structures within the main context.

    Let's revise the implementation to set relative positions correctly without crossing the context boundary. We will set the shift and relative constraints correctly to avoid such issues.

    Here's the corrected version:

    ```python
    from AIDL import *

    def airplane():
        """
        Create a model of an airplane with basic components: fuselage, wings, and tail.
        """

        airplane = Solid()

        fuselage = Solid()
        wings = Solid()
        tail = Solid()

        airplane.fuselage = fuselage
        airplane.wings = wings
        airplane.tail = tail

        # Define the fuselage as a long rectangle
        fuselage.body = RoundedRectangle((0, 0), 30*inches, 3*inches, 1*inches)

        # Set wing positions relative to the fuselage
        wings_left = Solid(shift=(-6*inches, 0))
        wings_right = Solid(shift=(6*inches, 0))
        wings.left_wing = wings_left
        wings.right_wing = wings_right

        wings_left.shape = Rectangle((0,0), 12*inches, 2*inches)
        wings_right.shape = Rectangle((0,0), 12*inches, 2*inches)

        # Set tail positions relative to the fuselage
        tail_horizontal = Solid(shift=(0, -1.5*inches))
        tail_vertical = Solid(shift=(2*inches, 0))

        tail.horizontal_stabilizer = tail_horizontal
        tail.vertical_stabilizer = tail_vertical

        tail_horizontal.shape = Rectangle((0,0), 8*inches, 1*inch)
        tail_vertical.shape = Rectangle((0,0), 1*inch, 4*inches)

        # Constrain wing positions relative to fuselage
        wings.AddConstraint(wings.left_wing.bb.right == wings.bb.horizontal_center - 6*inches)
        wings.AddConstraint(wings.right_wing.bb.left == wings.bb.horizontal_center + 6*inches)
        wings.AddConstraint(wings.bb.vertical_center == fuselage.bb.vertical_center)
        wings.AddConstraint(wings.bb.left == fuselage.bb.left + 10*inches)

        # Constrain tail positions relative to fuselage
        tail.AddConstraint(tail.horizontal_stabilizer.bb.vertical_center == tail.bb.vertical_center)
        tail.AddConstraint(tail.vertical_stabilizer.bb.top == tail.bb.vertical_center + 2*inches)
        tail.AddConstraint(tail.bb.left == fuselage.bb.right - 5*inches)
        tail.AddConstraint(tail.bb.vertical_center == fuselage.bb.vertical_center)

        return airplane

    # Solve and render the model.
    with AIDL_2D:
        model = airplane()
    print(model.Solve())
    model.Render()
    ```

    This code avoids directly referencing the fuselage's bounding box from within the tail structure by setting the relative shifts and constraints at the correct level.

    Please run this updated version, and if there are any further issues or additional requirements, let me know!

    Traceback (most recent call last):
      File "/net/projects/ranalab/jz/aidl/AIDL/generation/backend.py", line 21, in dumbrun
        exec(code, env)
      File "", line 58, in
      File "/net/projects/ranalab/jz/aidl/AIDL/structure.py", line 968, in Solve
        self._pre_solve(system)
      File "/net/projects/ranalab/jz/aidl/AIDL/structure.py", line 917, in _pre_solve
        structure._pre_solve(system)
      File "/net/projects/ranalab/jz/aidl/AIDL/structure.py", line 925, in _pre_solve
        constraint._pre_solve(system)
      File "/net/projects/ranalab/jz/aidl/AIDL/constraints.py", line 182, in _pre_solve
        self.expression._e.constrain(system, name=self.name)
      File "/net/projects/ranalab/jz/aidl/AIDL/expression.py", line 133, in _e
        return self._solver_expr()
      File "/net/projects/ranalab/jz/aidl/AIDL/expression.py", line 175, in _solver_expr
        return self.val[0]._e == self.val[1]._e
      File "/net/projects/ranalab/jz/aidl/AIDL/expression.py", line 133, in _e
        return self._solver_expr()
      File "/net/projects/ranalab/jz/aidl/AIDL/expression.py", line 169, in _solver_expr
        return self.val[0]._e - self.val[1]._e
      File "/net/projects/ranalab/jz/aidl/AIDL/expression.py", line 133, in _e
        return self._solver_expr()
      File "/net/projects/ranalab/jz/aidl/AIDL/expression.py", line 207, in _solver_expr
        return self.val[0]()._solver_expr()
      File "/net/projects/ranalab/jz/aidl/AIDL/structure.py", line 376, in _right
        return self._max_u()
      File "/net/projects/ranalab/jz/aidl/AIDL/structure.py", line 347, in _max_u
        bb = self._bounding_box()
      File "/net/projects/ranalab/jz/aidl/AIDL/structure.py", line 319, in _bounding_box
        raise NonLocalContext(context, self._structure)
    AIDL.feedback.NonLocalContext: .fuselage referenced from .tail.

    Thank you for your patience. It seems the constraints defining the relative positions of wings and tail are still too complex for the solver to handle within the current context.

    Let's simplify the context management by adding constraints at the root structure level while ensuring the geometry and substructures are consistent with the described airplane model.

    Here's a simplified approach:

    1. Define the fuselage, wings, and tail as individual solid components.
    2. Set positions for wings and tail relative to the airplane's main structure directly, avoiding interdependencies.

    Here's the updated version:

    ```python
    from AIDL import *

    def airplane():
        """
        Create a model of an airplane with basic components: fuselage, wings, and tail.
        """

        airplane = Solid()

        # Define fuselage
        fuselage = Solid()
        airplane.fuselage = fuselage
        fuselage.body = RoundedRectangle((0, 0), 30*inches, 3*inches, 1*inches)

        # Define wings
        left_wing = Solid(shift=(-10*inches, 0))
        right_wing = Solid(shift=(10*inches, 0))
        airplane.left_wing = left_wing
        airplane.right_wing = right_wing

        left_wing.shape = Rectangle((0, 0), 12*inches, 2*inches)
        right_wing.shape = Rectangle((0, 0), 12*inches, 2*inches)

        # Define tail
        horizontal_stabilizer = Solid(shift=(15*inches, 1.5*inches))
        vertical_stabilizer = Solid(shift=(15*inches, -1.5*inches))
        airplane.horizontal_stabilizer = horizontal_stabilizer
        airplane.vertical_stabilizer = vertical_stabilizer

        horizontal_stabilizer.shape = Rectangle((0, 0), 8*inches, 1*inch)
        vertical_stabilizer.shape = Rectangle((0, 0), 1*inch, 4*inches)

        # Position wings relative to fuselage
        airplane.AddConstraint(left_wing.bb.right == airplane.fuselage.bb.left + 5*inches)
        airplane.AddConstraint(right_wing.bb.left == airplane.fuselage.bb.right - 5*inches)
        airplane.AddConstraint(left_wing.bb.vertical_center == fuselage.bb.vertical_center)
        airplane.AddConstraint(right_wing.bb.vertical_center == fuselage.bb.vertical_center)

        # Position tail relative to fuselage
        airplane.AddConstraint(horizontal_stabilizer.bb.left == fuselage.bb.right - 15*inches)
        airplane.AddConstraint(horizontal_stabilizer.bb.vertical_center == fuselage.bb.vertical_center)
        airplane.AddConstraint(vertical_stabilizer.bb.left == fuselage.bb.right - 15*inches)
        airplane.AddConstraint(vertical_stabilizer.bb.vertical_center == fuselage.bb.vertical_center)

        return airplane

    # Solve and render the model.
    with AIDL_2D:
        model = airplane()
    print(model.Solve())
    model.Render()
    ```

    In this version:

    - `left_wing`, `right_wing`, `horizontal_stabilizer`, and `vertical_stabilizer` are directly added to `airplane`.
    - Constraints are defined to position wings and the tail relative to the `fuselage` and airplane root structure without crossing boundaries.

    Please run this code and let me know if it works or if any further adjustments are needed!