 |
CLIP Score: 30.03
from AIDL import *
def airplane_model(fuselage_length: float = 10*inches, fuselage_width: float = 1*inch,
wing_length: float = 5*inches, wing_width: float = 2*inches,
tail_height: float = 2*inches, tail_width: float = 1*inch):
airplane = Solid()
# Define the fuselage
fuselage = Solid()
airplane.fuselage = fuselage
fuselage.body = RoundedRectangle((0, 0), fuselage_length, fuselage_width, fuselage_width / 2)
# Define the left wing with basic lines forming a Right-Triangle
left_wing = Solid(shift=(-fuselage_length / 4, fuselage_width / 2))
fuselage.left_wing = left_wing
left_wing.point1 = Point(0, 0)
left_wing.point2 = Point(wing_length, wing_width)
left_wing.point3 = Point(wing_length, 0)
left_wing.line1 = Line(left_wing.point1, left_wing.point2)
left_wing.line2 = Line(left_wing.point2, left_wing.point3)
left_wing.line3 = Line(left_wing.point3, left_wing.point1)
# Define the right wing similarly
right_wing = Solid(shift=(-fuselage_length / 4, -(fuselage_width / 2)))
fuselage.right_wing = right_wing
right_wing.point1 = Point(0, 0)
right_wing.point2 = Point(wing_length, -wing_width)
right_wing.point3 = Point(wing_length, 0)
right_wing.line1 = Line(right_wing.point1, right_wing.point2)
right_wing.line2 = Line(right_wing.point2, right_wing.point3)
right_wing.line3 = Line(right_wing.point3, right_wing.point1)
# Define the vertical tail
vertical_tail = Solid(shift=(fuselage_length / 2, 0))
fuselage.vertical_tail = vertical_tail
vertical_tail.point1 = Point(0, 0)
vertical_tail.point2 = Point(tail_width, tail_height)
vertical_tail.point3 = Point(tail_width, 0)
vertical_tail.line1 = Line(vertical_tail.point1, vertical_tail.point2)
vertical_tail.line2 = Line(vertical_tail.point2, vertical_tail.point3)
vertical_tail.line3 = Line(vertical_tail.point3, vertical_tail.point1)
return airplane
with AIDL_2D:
model = airplane_model()
print(model.Solve())
model.Render()
|
Please write an AIDL program to generate a airplane
Certainly! We'll start by outlining the key sections and parts of the airplane. Here's a step-by-step approach:
1. **Components Breakdown**:
- **Fuselage** (the main body)
- **Wings** (left and right)
- **Tail** (vertical stabilizer and horizontal stabilizers)
- **Detail Engravings** (optional, can be added as Drawing nodes)
2. **Basic Geometry**:
- The fuselage can be a long rectangle with rounded ends.
- Wings could be triangular with rounded tips.
- The tail can have a vertical stabilizer (a right-angled triangle) and horizontal stabilizers (small rectangles or triangles).
Let's start by defining the function `airplane()` which will use Solid structures for the main body, wings, and tail; and optionally Drawing structures for details.
```python
from AIDL import *
def airplane(fuselage_length: float = 10*inches, fuselage_width: float = 1*inch,
wing_length: float = 5*inches, wing_width: float = 2*inches,
tail_height: float = 2*inches, tail_width: float = 1*inch):
airplane = Solid()
# Define the fuselage
fuselage = Solid()
airplane.fuselage = fuselage
fuselage.body = RoundedRectangle((0, 0), fuselage_length, fuselage_width, fuselage_width / 2)
# Define the left wing
left_wing = Solid(shift=(-fuselage_length / 4, fuselage_width / 2))
fuselage.left_wing = left_wing
left_wing.shape = RightTriangle((0, 0), wing_length, wing_width)
# Define the right wing
right_wing = Solid(shift=(-fuselage_length / 4, -fuselage_width / 2))
fuselage.right_wing = right_wing
right_wing.shape = RightTriangle((0, 0), wing_length, -1 * wing_width)
# Define the vertical tail (stabilizer)
vertical_tail = Solid(shift=(fuselage_length / 2, fuselage_width / 2))
fuselage.vertical_tail = vertical_tail
vertical_tail.shape = RightTriangle((0, 0), tail_width, tail_height)
# Define the horizontal tails (stabilizers)
horizontal_tail_left = Solid(shift=(fuselage_length / 2, fuselage_width / 2 - tail_height))
vertical_tail.horizontal_tail_left = horizontal_tail_left
horizontal_tail_left.shape = RightTriangle((0, 0), wing_length / 2, fuselage_width)
horizontal_tail_right = Solid(shift=(fuselage_length / 2, fuselage_width / 2 - tail_height))
vertical_tail.horizontal_tail_right = horizontal_tail_right
horizontal_tail_right.shape = RightTriangle((0, 0), wing_length / 2, -1 * fuselage_width)
return airplane
with AIDL_2D:
model = airplane()
print(model.Solve())
model.Render()
```
Here is a simple model of an airplane with a main fuselage, wings, and vertical & horizontal tail stabilizers. You can customize the dimensions by changing the `fuselage_length`, `fuselage_width`, `wing_length`, `wing_width`, `tail_height`, and `tail_width` parameters when calling the function.
This model should provide a good starting point. Feel free to request more details or modifications according to your specific requirements.
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 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 917, in _pre_solve
structure._pre_solve(system)
File "/net/projects/ranalab/jz/aidl/AIDL/structure.py", line 879, in _pre_solve
geometry._pre_solve(system)
File "/net/projects/ranalab/jz/aidl/AIDL/geometry.py", line 318, in _pre_solve
self.u._attach_to_entity(system, self._solver_point, 0)
AttributeError: 'Expression' object has no attribute '_attach_to_entity'
It looks like an error occurred during the solving process. The issue is likely due to an invalid reference or structure setup. Let's debug and fix the program step by step to ensure everything is correctly instantiated and linked.
To simplify and make sure everything is defined properly, I will adjust the horizontal tail stabilizers. Also, I'll ensure each geometry object is properly assigned to the structure without any invalid references. Let’s start with a cleaner implementation:
```python
from AIDL import *
def airplane_model(fuselage_length: float = 10*inches, fuselage_width: float = 1*inch,
wing_length: float = 5*inches, wing_width: float = 2*inches,
tail_height: float = 2*inches, tail_width: float = 1*inch):
airplane = Solid()
# Define the fuselage
fuselage = Solid()
airplane.fuselage = fuselage
fuselage.body = RoundedRectangle((0, 0), fuselage_length, fuselage_width, fuselage_width / 2)
# Define the left wing
left_wing = Solid(shift=(-fuselage_length / 4, fuselage_width / 2))
fuselage.left_wing = left_wing
left_wing_shape = RightTriangle((0, 0), wing_length, wing_width)
left_wing.shape = left_wing_shape
# Define the right wing
right_wing = Solid(shift=(-fuselage_length / 4, -fuselage_width / 2))
fuselage.right_wing = right_wing
right_wing_shape = RightTriangle((0, 0), wing_length, -wing_width)
right_wing.shape = right_wing_shape
# Define the vertical tail (stabilizer)
vertical_tail = Solid(shift=(fuselage_length / 2, fuselage_width / 2))
fuselage.vertical_tail = vertical_tail
vertical_tail_shape = RightTriangle((0, 0), tail_width, tail_height)
vertical_tail.shape = vertical_tail_shape
# Define the horizontal tails (stabilizers)
horizontal_tail_left = Solid(shift=(0, fuselage_width/2 - tail_height))
vertical_tail.horizontal_tail_left = horizontal_tail_left
left_tail_shape = RightTriangle((0, 0), wing_length / 2, fuselage_width)
horizontal_tail_left.shape = left_tail_shape
horizontal_tail_right = Solid(shift=(0, fuselage_width/2 - tail_height))
vertical_tail.horizontal_tail_right = horizontal_tail_right
right_tail_shape = RightTriangle((0, 0), wing_length / 2, -fuselage_width)
horizontal_tail_right.shape = right_tail_shape
return airplane
with AIDL_2D:
model = airplane_model()
print(model.Solve())
model.Render()
```
I have fine-tuned the horizontal stabilizer assignments and ensured they are properly linked and positioned. Let's test this implementation to see if it resolves the error. If an issue persists, we will continue to debug further details.
Traceback (most recent call last):
File "/net/projects/ranalab/jz/aidl/AIDL/generation/backend.py", line 21, in dumbrun
exec(code, env)
File "", line 48, 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 917, in _pre_solve
structure._pre_solve(system)
File "/net/projects/ranalab/jz/aidl/AIDL/structure.py", line 879, in _pre_solve
geometry._pre_solve(system)
File "/net/projects/ranalab/jz/aidl/AIDL/geometry.py", line 318, in _pre_solve
self.u._attach_to_entity(system, self._solver_point, 0)
AttributeError: 'Expression' object has no attribute '_attach_to_entity'
I apologize for the inconvenience. The issue might be deeper within the geometric definitions or references.
Let's simplify the model further to systematically find and solve the issue. We will start by creating the fuselage, wings, and tail without horizontal stabilizers to narrow down the error.
Here’s a more simplified and isolated version of the airplane model:
```python
from AIDL import *
def airplane_model(fuselage_length: float = 10*inches, fuselage_width: float = 1*inch,
wing_length: float = 5*inches, wing_width: float = 2*inches,
tail_height: float = 2*inches, tail_width: float = 1*inch):
airplane = Solid()
# Define the fuselage
fuselage = Solid()
airplane.fuselage = fuselage
fuselage.body = RoundedRectangle((0, 0), fuselage_length, fuselage_width, fuselage_width / 2)
# Define the left wing
left_wing = Solid(shift=(-fuselage_length / 4, fuselage_width / 2))
fuselage.left_wing = left_wing
left_wing.shape = RightTriangle((0, 0), wing_length, wing_width)
# Define the right wing
right_wing = Solid(shift=(-fuselage_length / 4, -(fuselage_width / 2)))
fuselage.right_wing = right_wing
right_wing.shape = RightTriangle((0, 0), wing_length, -wing_width)
# Define the vertical tail (stabilizer)
vertical_tail = Solid(shift=(fuselage_length / 2, 0))
fuselage.vertical_tail = vertical_tail
vertical_tail.shape = RightTriangle((0, 0), tail_width, tail_height)
return airplane
with AIDL_2D:
model = airplane_model()
print(model.Solve())
model.Render()
```
This script defines a simplified version of the airplane model, focusing only on the main components: fuselage, wings, and vertical stabilizer.
If this works correctly, we can add the horizontal stabilizers step by step. This allows us to pinpoint where the errors might be occurring.
Try running this simplified version and let me know if it resolves the issue or if there are any additional errors.
Traceback (most recent call last):
File "/net/projects/ranalab/jz/aidl/AIDL/generation/backend.py", line 21, in dumbrun
exec(code, env)
File "", line 34, 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 917, in _pre_solve
structure._pre_solve(system)
File "/net/projects/ranalab/jz/aidl/AIDL/structure.py", line 879, in _pre_solve
geometry._pre_solve(system)
File "/net/projects/ranalab/jz/aidl/AIDL/geometry.py", line 318, in _pre_solve
self.u._attach_to_entity(system, self._solver_point, 0)
AttributeError: 'Expression' object has no attribute '_attach_to_entity'
I apologize for the persistent error. It appears that the issue may be with the right-handed coordinates of the RightTriangle geometry or potentially how the geometry is being referenced and instantiated.
Let's replace the use of RightTriangle with simpler structures to isolate the issue. We will use basic Line geometry to define the wings and vertical tail.
Here's a more fundamental approach:
```python
from AIDL import *
def airplane_model(fuselage_length: float = 10*inches, fuselage_width: float = 1*inch,
wing_length: float = 5*inches, wing_width: float = 2*inches,
tail_height: float = 2*inches, tail_width: float = 1*inch):
airplane = Solid()
# Define the fuselage
fuselage = Solid()
airplane.fuselage = fuselage
fuselage.body = RoundedRectangle((0, 0), fuselage_length, fuselage_width, fuselage_width / 2)
# Define the left wing with basic lines forming a Right-Triangle
left_wing = Solid(shift=(-fuselage_length / 4, fuselage_width / 2))
fuselage.left_wing = left_wing
left_wing.point1 = Point(0, 0)
left_wing.point2 = Point(wing_length, wing_width)
left_wing.point3 = Point(wing_length, 0)
left_wing.line1 = Line(left_wing.point1, left_wing.point2)
left_wing.line2 = Line(left_wing.point2, left_wing.point3)
left_wing.line3 = Line(left_wing.point3, left_wing.point1)
# Define the right wing similarly
right_wing = Solid(shift=(-fuselage_length / 4, -(fuselage_width / 2)))
fuselage.right_wing = right_wing
right_wing.point1 = Point(0, 0)
right_wing.point2 = Point(wing_length, -wing_width)
right_wing.point3 = Point(wing_length, 0)
right_wing.line1 = Line(right_wing.point1, right_wing.point2)
right_wing.line2 = Line(right_wing.point2, right_wing.point3)
right_wing.line3 = Line(right_wing.point3, right_wing.point1)
# Define the vertical tail
vertical_tail = Solid(shift=(fuselage_length / 2, 0))
fuselage.vertical_tail = vertical_tail
vertical_tail.point1 = Point(0, 0)
vertical_tail.point2 = Point(tail_width, tail_height)
vertical_tail.point3 = Point(tail_width, 0)
vertical_tail.line1 = Line(vertical_tail.point1, vertical_tail.point2)
vertical_tail.line2 = Line(vertical_tail.point2, vertical_tail.point3)
vertical_tail.line3 = Line(vertical_tail.point3, vertical_tail.point1)
return airplane
with AIDL_2D:
model = airplane_model()
print(model.Solve())
model.Render()
```
In this version:
- We've replaced the `RightTriangle` geometry with explicit `Point` and `Line` geometries to form the wings and vertical stabilizer.
- This step-by-step approach should help us pinpoint any issues related to geometry references or assignments.
Please try running this simplified script. If it works, we can then incrementally add more complexity while ensuring correctness at each stage. Let me know the result, and we'll proceed accordingly.
|