Source code for RCAIDE.Library.Plots.Geometry.generate_3d_fuselage_points
# RCAIDE/Library/Plots/Geometry/generate_3d_fuselage_points.py
#
#
# Created: Jul 2023, M. Clarke
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# IMPORT
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from RCAIDE.Framework.Core import Data
import numpy as np
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# PLOTS
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[docs]
def generate_3d_fuselage_points(fuselage, tessellation = 24):
"""
Generates 3D coordinate points that define a fuselage surface.
Parameters
----------
fuselage : Fuselage
RCAIDE fuselage data structure containing geometry information
tessellation : int, optional
Number of points to use in circumferential discretization (default: 24)
Returns
-------
G : Data
Data structure containing generated points
- PTS : ndarray
Array of shape (num_segments, tessellation, 3) containing
x,y,z coordinates of surface points
Notes
-----
Points are generated by creating super-elliptical cross-sections at each segment
and positioning them according to segment locations.
**Major Assumptions**
* Cross-sections lie in y-z plane
* Segments are ordered from nose to tail
* Origin is at the nose of the fuselage
See Also
--------
plot_3d_fuselage : Function to visualize the generated surface
"""
num_fus_segs = len(fuselage.segments.keys())
fuselage_points = np.zeros((num_fus_segs,tessellation ,3))
if num_fus_segs > 0:
for i_seg, segment in enumerate(fuselage.segments):
a = segment.width/2
b = segment.height/2
n = segment.curvature
theta = np.linspace(0,2*np.pi,tessellation)
fus_ypts = (abs((np.cos(theta)))**(2/n))*a * ((np.cos(theta)>0)*1 - (np.cos(theta)<0)*1)
fus_zpts = (abs((np.sin(theta)))**(2/n))*b * ((np.sin(theta)>0)*1 - (np.sin(theta)<0)*1)
fuselage_points[i_seg,:,0] = segment.percent_x_location*fuselage.lengths.total + fuselage.origin[0][0]
fuselage_points[i_seg,:,1] = fus_ypts + segment.percent_y_location*fuselage.lengths.total + fuselage.origin[0][1]
fuselage_points[i_seg,:,2] = fus_zpts + segment.percent_z_location*fuselage.lengths.total + fuselage.origin[0][2]
G = Data()
G.PTS = fuselage_points
return G
