''' Lockheed Martin 1021 test case (AIAA Sonic Boom Workshop) Note: this is only a simplified version of the original geometry. The planform is not accurate, and geometry is not a perfect match. https://lbpw.larc.nasa.gov/ ''' import os import sys sys.path.append('.') import copy import numpy as np from cst_modeling.operation import GuideCurve from cst_modeling.surface2 import Surface, BasicSurface from cst_modeling.io import plot3d_to_igs, output_plot3d_for_parts class Fuselage(BasicSurface): ''' The major difference between Fuselage and Surface is that the 'span-wise' direction changes from the 'z' direction to the 'x' direction. In consequence, the 3D section profile is in y-z plane. ''' def __init__(self, n_sec=1, name='Surf', nn=1001, ns=101, smooth_surface=False, smooth_sections = None, rotate_x_section=False, rotation_sections = None, is_guide_curve_at_LE=True): super().__init__(n_sec, name, nn, ns, smooth_surface, smooth_sections, rotate_x_section, rotation_sections, is_guide_curve_at_LE) @staticmethod def create_circle(n, r, x0, y0): ''' Create a circle in x-y plane ''' theta = np.linspace(0, 2*np.pi, n) x = r * np.cos(theta) + x0 y = r * np.sin(theta) + y0 return x, y def update_section(self) -> None: ''' Update all sections' profile curves, i.e., a closed circle ''' for i in range(self.n_section): theta = np.linspace(0, 2*np.pi, self.nn, endpoint=True) self.sections[i].xx = np.cos(theta) self.sections[i].yy = np.sin(theta) self.sections[i].x = np.ones(self.nn) * self.sections[i].xLE self.sections[i].y = np.cos(theta) * self.sections[i].chord / 2 + self.sections[i].yLE self.sections[i].z = np.sin(theta) * self.sections[i].chord / 2 + self.sections[i].zLE def read_setting(self, fname) -> None: ''' Read in Surface layout from file Parameters ---------- fname : str settings file name. ''' if not os.path.exists(fname): raise Exception(fname+' does not exist for surface read setting') key_dict = {'Layout:': 1} found_surf = False found_key = 0 with open(fname, 'r') as f: lines = f.readlines() i_line = 0 while i_line 1: if '[Surf]' in line[0] and self.name == line[1]: found_surf = True elif found_surf and '[Surf]' in line[0]: break elif found_surf and found_key == 0: if line[0] in key_dict: found_key = key_dict[line[0]] elif found_surf and found_key == 1: for i in range(self.n_section): i_line += 1 line = lines[i_line].split() self.sections[i].xLE = float(line[0]) self.sections[i].yLE = float(line[1]) self.sections[i].zLE = float(line[2]) self.sections[i].chord = float(line[3]) found_key = 0 else: # Lines that are not relevant pass i_line += 1 print('Read surface [%s] settings'%(self.name)) # Locate layout center for plot self.update_layout_center() def get_default_guide_curve(self, **kwargs) -> GuideCurve: ''' Initialize the default guide curve object. It has a piecewise linear distribution along the span, defined by the section parameters. Returns -------- guide: GuideCurve default guide curve object. ''' custom_control_points = { 'x': [sec.xLE for sec in self.sections], 'y': [sec.yLE for sec in self.sections], 'z': [sec.zLE for sec in self.sections], 'scale': [sec.chord for sec in self.sections], 'rot_x': [0.0 for _ in self.sections], 'rot_y': [90.0 for _ in self.sections], 'rot_z': [0.0 for _ in self.sections], 'rot_axis': [0.0 for _ in self.sections], } guide = super().get_default_guide_curve(custom_control_points, smooth_keys=['x', 'y', 'z', 'scale']) return guide if __name__ == "__main__": path = os.path.dirname(sys.argv[0]) #* Geometry if True: #* Delta wing wing1 = Surface(n_sec=4, name='wing', nn=201, ns=101, smooth_surface=True) wing1.read_setting(fname=os.path.join(path, 'aircraft.txt'), tail=0.005) wing1.prepare(smooth_keys=['x', 'y', 'z', 'scale', 'rot_z']) wing1.geo() wing2 = copy.deepcopy(wing1) wing2.flip(plane='XY') #* V-tail vTail1 = Surface(n_sec=2, name='vTail', nn=201, ns=21) vTail1.read_setting(fname=os.path.join(path, 'aircraft.txt'), tail=0.005) vTail1.prepare() vTail1.geo() vTail2 = copy.deepcopy(vTail1) vTail2.flip(plane='XY') #* Fuselage fuselage = Fuselage(n_sec=6, name='fuselage', nn=201, ns=21, smooth_surface=True, smooth_sections=[(0,2), (3,5)]) fuselage.read_setting(fname=os.path.join(path, 'aircraft.txt')) fuselage.prepare() fuselage.geo() #* Output each part if False: wing1.output_plot3d(fname=os.path.join(path, 'wing-1.xyz'), one_piece=True, split=False) wing2.output_plot3d(fname=os.path.join(path, 'wing-2.xyz'), one_piece=True, split=False) vTail1.output_plot3d(fname=os.path.join(path, 'vTail-1.xyz'), one_piece=True, split=False) vTail2.output_plot3d(fname=os.path.join(path, 'vTail-2.xyz'), one_piece=True, split=False) fuselage.output_plot3d(fname=os.path.join(path, 'fuselage.xyz'), one_piece=True) plot3d_to_igs(fname=os.path.join(path, 'wing-1')) plot3d_to_igs(fname=os.path.join(path, 'wing-2')) plot3d_to_igs(fname=os.path.join(path, 'vTail-1')) plot3d_to_igs(fname=os.path.join(path, 'vTail-2')) plot3d_to_igs(fname=os.path.join(path, 'fuselage')) #* Output parts in one file if True: fname = os.path.join(path, 'aircraft') output_plot3d_for_parts(fname+'.xyz', wing1.surfaces, wing2.surfaces, vTail1.surfaces, vTail2.surfaces, fuselage.surfaces) plot3d_to_igs(fname)