Coverage for /opt/hostedtoolcache/Python/3.11.10/x64/lib/python3.11/site-packages/hypervehicle/hangar/hifire8.py: 96%

1import numpy as np

2from hypervehicle import Vehicle

3from hypervehicle.generator import Generator

4from hypervehicle.geometry import Vector3, Line, Polyline, Bezier

5from hypervehicle.components import (

6 Wing,

7 Fin,

8 RevolvedComponent,

9 CompositeComponent,

10 common,

11)

14def leading_edge_width_function(r):

15 temp = Bezier(

16 [

17 Vector3(x=0.0, y=0.01),

18 Vector3(x=0.5, y=0.1),

19 Vector3(x=1.0, y=0.01),

20 ]

21 )

22 le_width = temp(r).y

23 return le_width

26class ParametricHIFiRE8(Generator):

27 """Parametric generator for mock-up of the HIFiRE 8.

29 Dimensions have been approximated based on vehicle's visual proportions.

30 """

32 def __init__(self, **kwargs) -> None:

33 # Vehicle parameters

34 self.L = 1.2

35 self.R_base = 0.175

36 self.R_nose = 0.1

37 self.nozzle_length = 0.1

39 # Complete instantiation

40 super().__init__(**kwargs)

42 def create_instance(self) -> Vehicle:

43 # Instantiate hypervehicle and add all components

44 hifire8 = Vehicle()

45 hifire8.configure(

46 name="HIFiRE-8",

47 verbosity=1,

48 )

50 # Construct fuselage

51 # ====================

53 fuse_slope = np.arctan((self.R_base - self.R_nose) / self.L)

55 Xn = self.L

56 X1 = 1 * self.L

57 X2 = 0.0

58 X3 = -self.nozzle_length # Nozzle length

60 Rn = self.R_nose

61 R1 = self.R_base - X1 * np.tan(fuse_slope)

62 R2 = self.R_base - X2 * np.tan(fuse_slope)

63 R3 = R2 # R_base - X3*np.tan(fuse_slope)

65 fuse_line = Polyline(

66 [

67 Line(p0=Vector3(X1, R1), p1=Vector3(X2, R2)),

68 Line(p0=Vector3(X2, R2), p1=Vector3(X3, R3)),

69 Line(p0=Vector3(X3, R3), p1=Vector3(X3, 0)),

70 ]

71 )

72 fuselage_0 = RevolvedComponent(fuse_line)

74 fuse_base_line = Line(p0=Vector3(X1, 0), p1=Vector3(X1, R1))

75 fuselage_1 = RevolvedComponent(fuse_base_line)

77 # Create composite component for fuselage

78 fuselage = CompositeComponent(stl_resolution=8)

79 fuselage.add_component(fuselage_0)

80 fuselage.add_component(fuselage_1)

82 # Construct fins

83 # ====================

84 # |--p1-----p2

85 # | | \

86 # | | \

87 # | | \

88 # |--p0______________p3

90 fin_length = 0.4 # length from p0 to p3

91 fin_height = 0.4 * fin_length

92 fin_thickness = 0.02 * fin_length

93 fin_angle = np.deg2rad(90 - 45)

95 def eval_r_at_x(x):

96 """Returns the R value at a given x."""

97 return self.R_base - x * np.tan(fuse_slope)

99 p0 = Vector3(x=0, y=eval_r_at_x(0))

100 p1 = Vector3(x=0.2 * fin_length, y=eval_r_at_x(0.2 * fin_length) + fin_height)

101 p2 = Vector3(x=0.7 * fin_length, y=eval_r_at_x(0.7 * fin_length) + fin_height)

102 p3 = Vector3(x=fin_length, y=eval_r_at_x(fin_length))

103

104 fin1 = Fin(

105 p0=p0,

106 p1=p1,

107 p2=p2,

108 p3=p3,

109 fin_thickness=fin_thickness,

110 fin_angle=fin_angle,

111 top_thickness_function=common.uniform_thickness_function(

112 fin_thickness, "top"

113 ),

114 bot_thickness_function=common.uniform_thickness_function(

115 fin_thickness, "bot"

116 ),

117 LE_wf=leading_edge_width_function,

118 mirror=False,

119 stl_resolution=3,

120 )

121

122 # Copy for second fin

123 fin2 = Fin(

124 p0=p0,

125 p1=p1,

126 p2=p2,

127 p3=p3,

128 fin_thickness=fin_thickness,

129 fin_angle=fin_angle + np.deg2rad(90),

130 top_thickness_function=common.uniform_thickness_function(

131 fin_thickness, "top"

132 ),

133 bot_thickness_function=common.uniform_thickness_function(

134 fin_thickness, "bot"

135 ),

136 LE_wf=leading_edge_width_function,

137 mirror=False,

138 stl_resolution=3,

139 )

140

141 # Copy for third fin - this should be improved. Maybe

142 # make a fin geom func and modify fin height

143 fin3 = Fin(

144 p0=p0,

145 p1=0.5 * p1,

146 p2=0.5 * p2,

147 p3=p3,

148 fin_thickness=fin_thickness,

149 fin_angle=np.deg2rad(-90),

150 top_thickness_function=common.uniform_thickness_function(

151 fin_thickness, "top"

152 ),

153 bot_thickness_function=common.uniform_thickness_function(

154 fin_thickness, "bot"

155 ),

156 LE_wf=leading_edge_width_function,

157 mirror=False,

158 stl_resolution=3,

159 )

160

161 # Construct wing

162 # ====================

163

164 # |---B0-------B1__

165 # | | ----____

166 # | | ----_____

167 # | | B2-----------____B3

168 # |---A0-----------------------------A1---------------TT

169 #

170 # |------------------- wing_L ---------------------|

171

172 wing_L = 1.3

173 wing_thickness = 0.04

174 wing_width = 0.4

175 wing_origin = 0.2

176 flap_length = 0.2

177

178 # Required points

179 A0 = Vector3(x=wing_origin, y=0)

180 A1 = Vector3(x=A0.x + 0.5 * wing_L, y=0)

181 TT = Vector3(x=A0.x + wing_L, y=0)

182 B0 = Vector3(x=A0.x, y=wing_width)

183

184 # Construction points

185 B1 = Vector3(x=A0.x + 0.1 * wing_L, y=B0.y)

186 B2 = Vector3(x=A1.x, y=0.5 * wing_width)

187 B3 = Vector3(x=TT.x, y=0.13 * wing_width)

188

189 # Leading edge line

190 B0B1 = Line(p0=B0, p1=B1)

191 B1B2 = Line(p0=B1, p1=B2)

192 B2B3 = Line(p0=B2, p1=B3)

193 B3TT = Line(p0=B3, p1=TT)

194 Line_B0TT = Polyline([B0B1, B1B2, B2B3, B3TT])

195

196 wing = Wing(

197 A0=A0,

198 A1=A1,

199 TT=TT,

200 B0=B0,

201 Line_B0TT=Line_B0TT,

202 top_tf=common.uniform_thickness_function(wing_thickness, "top"),

203 bot_tf=common.uniform_thickness_function(wing_thickness, "bot"),

204 LE_wf=leading_edge_width_function,

205 flap_length=flap_length,

206 stl_resolution=4,

207 )

208

209 # Construct nose cap

210 # ====================

211 L_n = 0.5

212 r_b = eval_r_at_x(Xn)

213 t_n = 0.005

214 w_n = 0.15

215

216 # Side width angle

217 side_theta = np.arctan((r_b - 0.5 * w_n) / L_n)

218

219 # Points

220 A0n = Vector3(x=Xn, y=0)

221 A1n = Vector3(x=Xn + 0.5 * L_n, y=0)

222 TTn = Vector3(x=Xn + L_n, y=0)

223

224 B0n = Vector3(x=A0n.x, y=r_b)

225 B1n = Vector3(x=A1n.x, y=r_b - (A1n.x - Xn) * np.tan(side_theta))

226 B2n = Vector3(x=TTn.x, y=0.5 * w_n)

227

228 B0B1n = Line(p0=B0n, p1=B1n)

229 B1B2n = Line(p0=B1n, p1=B2n)

230 B2TTn = Line(p0=B2n, p1=TTn)

231

232 Line_B0TTn = Polyline([B0B1n, B1B2n, B2TTn])

233

234 def nose_tf_top(x, y, z=0):

235 # Calculate function weightings for linear blending

236 circular_weighting = 1 - (1 / L_n) * (x - Xn)

237 flat_weighting = 1 - circular_weighting

238

239 # Calculate functions at x

240 z_circle = np.sqrt(r_b**2 - y**2)

241 z_flat = t_n

242 # z_flat = t_n*np.sqrt(w_n - y**2)

243

244 # Weighted sum of function contributions

245 z = circular_weighting * z_circle + flat_weighting * z_flat

246 # z = t_n

247 return Vector3(x=0, y=0, z=-z)

248

249 def nose_tf_bot(x, y, z=0):

250 # Calculate function weightings for linear blending

251 circular_weighting = 1 - (1 / L_n) * (x - Xn)

252 flat_weighting = 1 - circular_weighting

253

254 # Calculate functions at x

255 z_circle = np.sqrt(r_b**2 - y**2)

256 z_flat = t_n

257 # z_flat = np.sqrt(w_n - y**2)

258

259 # Weighted sum of function contributions

260 z = circular_weighting * z_circle + flat_weighting * z_flat

261 # z = t_n

262 return Vector3(x=0, y=0, z=z)

263

264 nose = Wing(

265 A0=A0n,

266 A1=A1n,

267 TT=TTn,

268 B0=B0n,

269 Line_B0TT=Line_B0TTn,

270 top_tf=nose_tf_top,

271 bot_tf=nose_tf_bot,

272 LE_wf=leading_edge_width_function,

273 LE_type="FLAT",

274 stl_resolution=4,

275 )

276

277 # Add components

278 hifire8.add_component(fuselage, name="fuselage")

279 hifire8.add_component(wing, reflection_axis="y", name="wing")

280 hifire8.add_component(nose, reflection_axis="y", name="nose")

281 hifire8.add_component(fin1, name="fin1")

282 hifire8.add_component(fin2, name="fin2")

283 hifire8.add_component(fin3, name="fin3")

284

285 return hifire8

286

287

288if __name__ == "__main__":

289 # To create the nominal geometry

290 parametric_generator = ParametricHIFiRE8()

291 hifire8 = parametric_generator.create_instance()

292 hifire8.generate()

293 hifire8.to_stl()