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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()
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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!
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