aidl/airplane/airplane9


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airplane9 image
                
from AIDL import *

def airplane(
        fuselage_length: float = 12 * inches,
        fuselage_width: float = 1.5 * inches,
        wing_span: float = 10 * inches,
        wing_chord: float = 2 * inches,
        tail_height: float = 3 * inches,
        tail_span: float = 3 * inches,
        engine_diameter: float = 1 * inch
):
    """
    Model a simple airplane with a fuselage, wings, tail, and engines.
    """

    airplane = Solid()
    
    # Define the main structural components
    fuselage = Solid()
    left_wing = Solid(shift=(-wing_span / 2, 0))
    right_wing = Solid(shift=(wing_span / 2, 0))
    tail = Solid()
    vertical_stabilizer = Solid(shift=(0, tail_height / 2))
    horizontal_stabilizer = Solid(shift=(0, -tail_height / 2))
    engine_left = Solid(shift=(-wing_span / 4, -wing_chord / 2))
    engine_right = Solid(shift=(wing_span / 4, -wing_chord / 2))

    airplane.fuselage = fuselage
    airplane.left_wing = left_wing
    airplane.right_wing = right_wing
    airplane.tail = tail
    tail.vertical_stabilizer = vertical_stabilizer
    tail.horizontal_stabilizer = horizontal_stabilizer
    left_wing.engine_left = engine_left
    right_wing.engine_right = engine_right

    # Geometry for Fuselage
    fuselage.body = RoundedRectangle((0, 0), fuselage_length, fuselage_width, fuselage_width / 2)

    # Geometry for Wings
    left_wing.body = Rectangle((0, 0), wing_chord, wing_span)
    right_wing.body = Rectangle((0, 0), wing_chord, wing_span)

    # Geometry for Tail
    vertical_stabilizer.body = Rectangle((0, 0), tail_span, tail_height)
    horizontal_stabilizer.body = Rectangle((0, 0), tail_span, tail_height / 2)

    # Geometry for Engines
    engine_left.body = Circle((0, 0), engine_diameter / 2)
    engine_right.body = Circle((0, 0), engine_diameter / 2)

    return airplane

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 structures and their hierarchical relationships for the airplane. We'll create separate structures for the different parts of the airplane, such as the fuselage, wings, tail, and any other necessary components. 

Here's a basic outline to get us started:

1. **Fuselage:** The main body of the airplane.
2. **Wings:** Includes both left and right wings.
3. **Tail:** Includes the horizontal and vertical stabilizers.
4. **Engine:** This will be a simple representation, possibly as a cylinder or box.

Let's begin by defining the structures and their hierarchical relationships:

```python
from AIDL import *

def airplane(
        fuselage_length: float = 12 * inches,
        fuselage_width: float = 1.5 * inches,
        wing_span: float = 10 * inches,
        wing_chord: float = 2 * inches,
        tail_height: float = 3 * inches,
        tail_span: float = 3 * inches,
        engine_diameter: float = 1 * inch
):
    """
    Model a simple airplane with a fuselage, wings, tail, and engines.
    """

    airplane = Solid()
    
    # Define the main structural components
    fuselage = Solid()
    left_wing = Solid(shift=(-wing_span / 2, 0))
    right_wing = Solid(shift=(wing_span / 2, 0))
    tail = Solid()
    vertical_stabilizer = Solid(shift=(0, tail_height / 2))
    horizontal_stabilizer = Solid(shift=(0, -tail_height / 2))
    engine_left = Solid(shift=(-wing_span / 4, -wing_chord / 2))
    engine_right = Solid(shift=(wing_span / 4, -wing_chord / 2))

    airplane.fuselage = fuselage
    airplane.left_wing = left_wing
    airplane.right_wing = right_wing
    airplane.tail = tail
    tail.vertical_stabilizer = vertical_stabilizer
    tail.horizontal_stabilizer = horizontal_stabilizer
    left_wing.engine_left = engine_left
    right_wing.engine_right = engine_right

    return airplane

with AIDL_2D:
    model = airplane()
print(model.Solve())
model.Render()
```

This code sets up the basic structural components for the airplane. Next, we need to add constraints to position and size these components relative to each other. However, let's go through this in steps, and I'll await your feedback on the initial structure definition. If it's correct, we'll proceed to add the necessary constraints.

Traceback (most recent call last):
  File "/net/projects/ranalab/jz/aidl/AIDL/generation/backend.py", line 21, in dumbrun
    exec(code, env)
  File "", line 43, in 
  File "/net/projects/ranalab/jz/aidl/AIDL/structure.py", line 1093, in Render
    self._solver_system.render(MPLRenderer(show_construction=show_construction))
  File "/net/projects/ranalab/jz/aidl/AIDL/solver.py", line 538, in render
    renderer.render(view_data)
  File "/net/projects/ranalab/jz/aidl/AIDL/renderer.py", line 159, in render
    min_corner = visible_coords.min(axis=0)
  File "/home/zzhang18/.local/lib/python3.10/site-packages/numpy/core/_methods.py", line 44, in _amin
    return umr_minimum(a, axis, None, out, keepdims, initial, where)
ValueError: zero-size array to reduction operation minimum which has no identity


It looks like the issue is that there is no geometry defined yet, and thus no visible coordinates for rendering. Let's add some geometry to each of the airplane components before we proceed with constraints. 

We will define:

1. **Fuselage:** A rounded rectangle to represent the main body of the airplane.
2. **Wings:** Simple rectangles for both the left and right wings.
3. **Tail:** Two components, vertical and horizontal stabilizers, also using rectangles.
4. **Engines:** Simple circles for both engines.

Here's the updated code with geometry definitions:

```python
from AIDL import *

def airplane(
        fuselage_length: float = 12 * inches,
        fuselage_width: float = 1.5 * inches,
        wing_span: float = 10 * inches,
        wing_chord: float = 2 * inches,
        tail_height: float = 3 * inches,
        tail_span: float = 3 * inches,
        engine_diameter: float = 1 * inch
):
    """
    Model a simple airplane with a fuselage, wings, tail, and engines.
    """

    airplane = Solid()
    
    # Define the main structural components
    fuselage = Solid()
    left_wing = Solid(shift=(-wing_span / 2, 0))
    right_wing = Solid(shift=(wing_span / 2, 0))
    tail = Solid()
    vertical_stabilizer = Solid(shift=(0, tail_height / 2))
    horizontal_stabilizer = Solid(shift=(0, -tail_height / 2))
    engine_left = Solid(shift=(-wing_span / 4, -wing_chord / 2))
    engine_right = Solid(shift=(wing_span / 4, -wing_chord / 2))

    airplane.fuselage = fuselage
    airplane.left_wing = left_wing
    airplane.right_wing = right_wing
    airplane.tail = tail
    tail.vertical_stabilizer = vertical_stabilizer
    tail.horizontal_stabilizer = horizontal_stabilizer
    left_wing.engine_left = engine_left
    right_wing.engine_right = engine_right

    # Geometry for Fuselage
    fuselage.body = RoundedRectangle((0, 0), fuselage_length, fuselage_width, fuselage_width / 2)

    # Geometry for Wings
    left_wing.body = Rectangle((0, 0), wing_chord, wing_span)
    right_wing.body = Rectangle((0, 0), wing_chord, wing_span)

    # Geometry for Tail
    vertical_stabilizer.body = Rectangle((0, 0), tail_span, tail_height)
    horizontal_stabilizer.body = Rectangle((0, 0), tail_span, tail_height / 2)

    # Geometry for Engines
    engine_left.body = Circle((0, 0), engine_diameter / 2)
    engine_right.body = Circle((0, 0), engine_diameter / 2)

    return airplane

with AIDL_2D:
    model = airplane()
print(model.Solve())
model.Render()
```

With this addition, we should have the basic geometry defined for each structure. Let's run this and check for any further issues. Once it runs correctly, we can proceed to add the necessary constraints to position and size the components relative to each other.

Please try running this code and let me know if there are any issues or if we should proceed to the next step.