# 우주왕복선 발사 형상(STS 스택) — 오비터 + 외부연료탱크(ET) + 고체로켓부스터(SRB) 2기. # 오비터 동체는 단면표(폭·바닥·지붕 높이)를 보간해 수십 개의 슈퍼타원 단면을 이어 붙인 로프트 메시이고, # 이중 삼각익과 수직꼬리날개는 평면형 위에 익형 두께 분포를 얹어 bmesh 로 직접 짰다. # 단열 타일의 흑백 경계, 창문, 앞전 RCC 는 면 위치에 따라 재질 슬롯을 나눠 칠했다. # ET·SRB·엔진 노즐은 회전체(lathe), 인터탱크 주름과 SRB 이음 링은 루프로 만들었다. 단위 m, 실제 크기. import math from atelier import * SHOT = {"azimuth": -70, "elevation": 8, "lens": 60, "light": "day", "background": "#1d2533"} # ---------------------------------------------------------------- 재질 M_WHITE = mat('Orbiter_White_Tiles', '#e6e4dd', 0.62) M_BLACK = mat('Orbiter_Black_Tiles', '#222326', 0.75) M_RCC = mat('RCC_Leading_Edge_Grey', '#5c5e61', 0.6) M_GLASS = mat('Cockpit_Window', '#1a2530', 0.08, 0.3) M_BASE = mat('Aft_Heat_Shield', '#3b3936', 0.8) M_SSME = mat('SSME_Nozzle_Metal', '#a39a8a', 0.35, 0.85) M_ET = mat('ET_Foam_Orange', '#ad5b2b', 0.85) M_IT = mat('ET_Intertank_Foam', '#9b4f28', 0.85) M_SRB = mat('SRB_White_Paint', '#e2e0d8', 0.5) M_JOINT = mat('SRB_Joint_Band', '#9c9b96', 0.55, 0.2) M_SRBN = mat('SRB_Nozzle_Ablative', '#4a4643', 0.8) M_STRUT = mat('Attach_Strut_Metal', '#8d9095', 0.4, 0.7) M_SEAM = mat('Panel_Seam_Grey', '#6f6e6a', 0.7) def build_mesh(name, verts, faces, mats=None, mat_idx=None, smooth_all=True): me = bpy.data.meshes.new(name) me.from_pydata(verts, [], faces) me.validate() ob = bpy.data.objects.new(name, me) link(ob) for m in (mats or []): me.materials.append(m) if mat_idx is not None: me.polygons.foreach_set('material_index', mat_idx) if smooth_all: for p in me.polygons: p.use_smooth = True return ob def pchip(xs, ys): """단조 3차 보간 함수(과도한 출렁임 없이 단면표를 매끄럽게).""" n = len(xs) h = [xs[i + 1] - xs[i] for i in range(n - 1)] d = [(ys[i + 1] - ys[i]) / h[i] for i in range(n - 1)] m = [0.0] * n m[0], m[-1] = d[0], d[-1] for i in range(1, n - 1): if d[i - 1] * d[i] <= 0: m[i] = 0.0 else: w1, w2 = 2 * h[i] + h[i - 1], h[i] + 2 * h[i - 1] m[i] = (w1 + w2) / (w1 / d[i - 1] + w2 / d[i]) def f(x): if x <= xs[0]: return ys[0] if x >= xs[-1]: return ys[-1] i = max(k for k in range(n - 1) if xs[k] <= x) t = (x - xs[i]) / h[i] h00, h10 = 2 * t ** 3 - 3 * t ** 2 + 1, t ** 3 - 2 * t ** 2 + t h01, h11 = -2 * t ** 3 + 3 * t ** 2, t ** 3 - t ** 2 return h00 * ys[i] + h10 * h[i] * m[i] + h01 * ys[i + 1] + h11 * h[i] * m[i + 1] return f def spow(x, p): return math.copysign(abs(x) ** p, x) # ================================================================ 오비터 (로컬 좌표: x=기수 방향 u, y=우익 v, z=지붕 w) orbiter = bpy.data.objects.new('Orbiter', None) link(orbiter) ORB_PARTS = [] # 단면표: u, 반폭, 바닥높이, 지붕높이 ST = [ (0.0, 2.65, 0.00, 5.30), (21.0, 2.65, 0.00, 5.30), (23.0, 2.65, 0.00, 5.45), (25.0, 2.65, 0.03, 5.95), (26.3, 2.62, 0.07, 6.05), (27.5, 2.52, 0.16, 5.62), (28.6, 2.30, 0.30, 4.72), (29.8, 1.95, 0.52, 4.05), (30.9, 1.50, 0.82, 3.45), (31.8, 1.00, 1.12, 2.95), (32.4, 0.58, 1.42, 2.55), (32.8, 0.12, 1.80, 2.15), ] f_hw = pchip([s[0] for s in ST], [s[1] for s in ST]) f_wb = pchip([s[0] for s in ST], [s[2] for s in ST]) f_wt = pchip([s[0] for s in ST], [s[3] for s in ST]) NOSE = 32.9 def black_line(u): """옆면 흑백 타일 경계 높이(기수 쪽으로 올라간다).""" if u < 22: return 1.05 t = min(1.0, (u - 22) / (NOSE - 22)) return 1.05 + 1.25 * t * t def sec(u): hw, wb, wt = f_hw(u), f_wb(u), f_wt(u) return hw, wb, wt, wb + 0.36 * (wt - wb) def fus_point(u, a, grow=0.0): """동체 단면(u, 각도 a) 위의 점. 각도 0=우측, 90°=지붕. grow 만큼 바깥으로.""" hw, wb, wt, wc = sec(u) hw, wb, wt = hw + grow, wb - grow, wt + grow c, s_ = math.cos(a), math.sin(a) y = hw * spow(c, 0.30 if s_ < 0 else 0.55) z = wc + (wt - wc) * spow(s_, 0.62) if s_ >= 0 else wc + (wc - wb) * spow(s_, 0.25) return (u, y, z) def boundary_angle(u): hw, wb, wt, wc = sec(u) zb = min(black_line(u), wb + 0.8 * (wt - wb)) if zb < wc: return -math.asin(min(1.0, ((wc - zb) / (wc - wb)) ** 4)) return math.asin(min(1.0, ((zb - wc) / (wt - wc)) ** (1 / 0.62))) NB, NT = 14, 18 # 반쪽 링의 아래(검은 타일)/위(흰 타일) 분할 수 def ring_angles(u): ab = boundary_angle(u) out = [-math.pi / 2 + (ab + math.pi / 2) * k / NB for k in range(NB)] out += [ab + (math.pi / 2 - ab) * k / NT for k in range(NT)] return out + [math.pi / 2] + [math.pi - a for a in reversed(out[1:])] def fuselage(): us = [] u = 0.0 while u < NOSE - 0.05: us.append(u) u += 0.9 if u < 20 else (0.35 if u < 26 else 0.16) us.append(NOSE - 0.04) N = 2 * (NB + NT) verts, faces, mi = [], [], [] for u in us: for a in ring_angles(u): verts.append(fus_point(u, a)) R = len(us) for i in range(R - 1): for k in range(N): a0, a1 = i * N + k, i * N + (k + 1) % N faces.append((a0, a1, a1 + N, a0 + N)) cu = (us[i] + us[i + 1]) / 2 bottom = k < NB or k >= N - NB m = 1 if bottom else 0 if cu > NOSE - 0.75: m = 2 # 기수 RCC mi.append(m) tip = len(verts) verts.append((NOSE, 0.0, f_wb(NOSE) * 0.5 + f_wt(NOSE) * 0.5)) for k in range(N): faces.append(((R - 1) * N + k, (R - 1) * N + (k + 1) % N, tip)) mi.append(2) faces.append(tuple(reversed(range(N)))) mi.append(4) return build_mesh('Orbiter_Fuselage', verts, faces, [M_WHITE, M_BLACK, M_RCC, M_GLASS, M_BASE], mi) def surface_patch(name, u0, u1, a0, a1, grow, material, nu=8, na=10): """동체 표면을 grow 만큼 띄워 따라가는 얇은 패널(창문·검은 마스크).""" verts, faces = [], [] for i in range(nu + 1): u = u0 + (u1 - u0) * i / nu for j in range(na + 1): verts.append(fus_point(u, a0 + (a1 - a0) * j / na, grow)) for i in range(nu): for j in range(na): a = i * (na + 1) + j faces.append((a, a + na + 1, a + na + 2, a + 1)) return build_mesh(name, verts, faces, [material]) ORB_PARTS.append(fuselage()) D = math.radians ORB_PARTS.append(surface_patch('Cockpit_Black_Mask', 27.25, 28.95, D(34), D(146), 0.008, M_BLACK, 12, 28)) for k in range(3): lo = 50 + k * 13.5 for a0, a1 in ((lo, lo + 12), (180 - lo - 12, 180 - lo)): ORB_PARTS.append(surface_patch('Forward_Windshield', 27.62, 28.62, D(a0), D(a1), 0.018, M_GLASS, 6, 4)) for a0, a1 in ((74, 87), (93, 106)): ORB_PARTS.append(surface_patch('Overhead_Window', 26.95, 27.45, D(a0), D(a1), 0.016, M_GLASS, 4, 4)) for a0, a1 in ((20, 36), (144, 160)): ORB_PARTS.append(surface_patch('Side_Hatch_Window', 26.35, 26.95, D(a0), D(a1), 0.016, M_GLASS, 4, 4)) def airfoil_t(xa): """앞전 0 → 뒷전 1 의 두께 분포(NACA 4자리형).""" x = xa return 1.0 * (0.2969 * math.sqrt(x) - 0.1260 * x - 0.3516 * x * x + 0.2843 * x ** 3 - 0.1036 * x ** 4) / 0.5 + 0.012 def hinge_xs(K1, K2, xh, g=0.006): """앞전 0→뒷전 1 시위 분할. 인덱스 K1~K1+1 사이가 힌지선 띠가 되도록 고정.""" a = [(xh - g) * (1 - math.cos(math.pi / 2 * k / K1)) for k in range(K1 + 1)] b = [xh + g + (1 - xh - g) * k / K2 for k in range(K2 + 1)] return a + b def wings(): # 평면형: 스트레이크(81°) + 주익(45°), 반스팬 11.9 m def le(v): return 24.5 - (v - 2.6) * math.tan(math.radians(81)) if v <= 4.7 else 11.2 - (v - 4.7) def te(v): return 0.25 + 0.05 * (v - 2.6) vs = [2.25, 2.6, 3.1, 3.6, 4.2, 4.7, 5.3, 6.0, 6.6, 7.22, 7.32, 8.0, 9.0, 10.0, 10.8, 11.4, 11.9] K1, K2 = 20, 5 K = K1 + K2 + 1 verts, faces, mi = [], [], [] loop_n = 2 * K for side in (1, -1): base = len(verts) for v in vs: u_le, u_te = le(v), te(v) chord = u_le - u_te u_lem = 4.0 + (11.9 - v) # 주익 앞전 연장선 T = 0.12 * (u_lem - u_te) w0 = 0.32 + (v - 2.6) * 0.058 xs = hinge_xs(K1, K2, 1 - 2.3 / chord) ring = [] for k in range(loop_n): # 0..K 윗면(앞전→뒷전), K+1..2K-1 아랫면(뒷전→앞전) xa = xs[k] if k <= K else xs[2 * K - k] u = u_le - xa * chord xm = (u_lem - u) / (u_lem - u_te) if xm < 0: # 스트레이크 구간은 얇게 th = T * airfoil_t(min(1, xa * chord / 3.0)) * max(0.22, 0.55 + 0.04 * xm) else: th = T * airfoil_t(min(1.0, max(0.0, xm))) if xa * chord > 0.6 else T * airfoil_t(xm if xm > 0 else 0) * math.sqrt(xa * chord / 0.6) z = w0 + 0.8 * th if k <= K else w0 - 0.2 * th ring.append((u, side * v, z)) verts.extend(ring) S = len(vs) for i in range(S - 1): for k in range(loop_n): a0 = base + i * loop_n + k a1 = base + i * loop_n + (k + 1) % loop_n f = (a0, a1, a1 + loop_n, a0 + loop_n) faces.append(f if side == 1 else tuple(reversed(f))) kk = k + 0.5 vm = (vs[i] + vs[i + 1]) / 2 if kk < K: xa = xs[k] m = 2 if xa < 0.035 else (1 if xa < 0.09 else 0) if vm > 3.3 and (k == K1 or (k > K1 and 7.22 < vm < 7.32)): m = 3 # 엘레본 힌지·분할선 mi.append(m) else: xa = xs[2 * K - k - 1] if k < 2 * K - 1 else 0 mi.append(2 if xa < 0.02 else 1) tipring = list(range(base + (S - 1) * loop_n, base + S * loop_n)) rootring = list(range(base, base + loop_n)) faces.append(tuple(tipring) if side == -1 else tuple(reversed(tipring))) mi.append(2) faces.append(tuple(rootring) if side == 1 else tuple(reversed(rootring))) mi.append(1) ob = build_mesh('Orbiter_Wings', verts, faces, [M_WHITE, M_BLACK, M_RCC, M_SEAM], mi) return ob ORB_PARTS.append(wings()) def vertical_tail(): ws = [4.9, 5.4, 6.5, 7.6, 8.8, 10.0, 11.2, 12.4, 13.4, 14.3] K1, K2 = 13, 6 K = K1 + K2 + 1 xs = hinge_xs(K1, K2, 0.64, 0.004) verts, faces, mi = [], [], [] loop_n = 2 * K for w in ws: u_le = 8.8 - (w - 5.4) * 1.0 u_te = -1.0 - (w - 5.4) * 0.19 chord = u_le - u_te T = 0.075 * chord for k in range(loop_n): xa = xs[k] if k <= K else xs[2 * K - k] side = 1 if k <= K else -1 th = T * airfoil_t(xa) * 0.5 verts.append((u_le - xa * chord, side * th, w)) S = len(ws) for i in range(S - 1): for k in range(loop_n): a0 = i * loop_n + k a1 = i * loop_n + (k + 1) % loop_n faces.append((a0, a0 + loop_n, a1 + loop_n, a1)) j = k if k < K else 2 * K - k - 1 m = 2 if xs[j] < 0.03 else 0 if j == K1 and ws[i] >= 5.4: m = 3 # 러더/스피드브레이크 힌지선 mi.append(m) faces.append(tuple(range((S - 1) * loop_n, S * loop_n))) mi.append(2) faces.append(tuple(reversed(range(loop_n)))) mi.append(0) return build_mesh('Orbiter_Vertical_Tail', verts, faces, [M_WHITE, M_BLACK, M_RCC, M_SEAM], mi) ORB_PARTS.append(vertical_tail()) def oms_pod(side): us = [-0.9, -0.75, -0.5, 0.0, 2.0, 4.0, 5.5, 7.0, 8.5, 9.8, 10.8] sc = [0.45, 0.82, 0.95, 1.0, 1.0, 0.98, 0.9, 0.74, 0.52, 0.3, 0.06] N = 32 verts, faces = [], [] for u, s in zip(us, sc): for k in range(N): a = 2 * math.pi * k / N verts.append((u, side * 1.95 + 1.15 * s * math.cos(a), 4.8 + 1.15 * s * math.sin(a) - (1 - s) * 0.45)) R = len(us) for i in range(R - 1): for k in range(N): a0, a1 = i * N + k, i * N + (k + 1) % N f = (a0, a1, a1 + N, a0 + N) faces.append(f if side > 0 else tuple(reversed(f))) faces.append(tuple(reversed(range(N))) if side > 0 else tuple(range(N))) faces.append(tuple(range((R - 1) * N, R * N)) if side > 0 else tuple(reversed(range((R - 1) * N, R * N)))) ob = build_mesh('Orbiter_OMS_Pod_' + ('R' if side > 0 else 'L'), verts, faces, [M_WHITE]) return ob for sd in (1, -1): ORB_PARTS.append(oms_pod(sd)) def bell(name, r0, r1, L, material, seg=40): prof = [] n = 14 for i in range(n + 1): t = i / n prof.append((r0 + (r1 - r0) * (t ** 0.62), -L * t)) ob = lathe(name, prof, material=material, seg=seg) solidify(ob, 0.04) return ob # 주 엔진(SSME) 3기: 위 1, 아래 2 — 노즐은 -u 방향 ssme_proto = bell('SSME_Nozzle', 0.52, 1.15, 3.0, M_SSME) ssme_proto.rotation_euler = (0, math.radians(-90), 0) ENG_POS = [(0.0, 4.1), (1.38, 1.85), (-1.38, 1.85)] for i, (v, w) in enumerate(ENG_POS): ob = ssme_proto if i == 0 else duplicate(ssme_proto, name='SSME_Nozzle') ob.location = (-0.55, v, w) mount = cylinder('SSME_Powerhead_Mount', r=0.62, h=0.6, loc=(-0.6, v, w), rot=(0, math.radians(90), 0), material=M_BASE, seg=24) ORB_PARTS += [ob, mount] # OMS 엔진 노즐 oms_n = bell('OMS_Nozzle', 0.28, 0.55, 1.3, M_SSME, seg=28) oms_n.rotation_euler = (0, math.radians(-90), 0) oms_n.location = (-0.85, 1.95, 4.85) ORB_PARTS += [oms_n, duplicate(oms_n, loc=(-0.85, -1.95, 4.85))] # 보디 플랩 flap = prism('Orbiter_Body_Flap', [(-2.55, -3.0), (0.1, -3.05), (0.1, 3.05), (-2.55, 3.0)], 0.5, loc=(0, 0, 0.06), material=M_BLACK) ORB_PARTS.append(flap) # 화물칸 도어: 가로 이음선 5줄, 힌지선 2줄, 중앙선 1줄 A_HINGE = math.radians(28) for i, u in enumerate((4.2, 8.75, 13.3, 17.85, 22.4)): pts = [fus_point(u, A_HINGE + (math.pi - 2 * A_HINGE) * k / 24, 0.012) for k in range(25)] ORB_PARTS.append(curve_tube('Payload_Bay_Door_Seam', pts, radius=0.03, material=M_SEAM, bevel_res=1)) for a in (A_HINGE, math.pi - A_HINGE, math.pi / 2): pts = [fus_point(4.2 + 18.2 * k / 20, a, 0.012) for k in range(21)] ORB_PARTS.append(curve_tube('Payload_Bay_Hinge_Line', pts, radius=0.03, material=M_SEAM, bevel_res=1)) parent_to(ORB_PARTS, orbiter) # ================================================================ 스택 배치(월드) ET_R = 4.2 ET_Z0 = 8.0 ORB_X = ET_R + 1.35 # 오비터 배면(w=0)의 X ORB_Z = 6.6 # 오비터 후미(u=0)의 Z orbiter.matrix_world = Matrix(((0, 0, 1, ORB_X), (0, -1, 0, 0), (1, 0, 0, ORB_Z), (0, 0, 0, 1))) # ================================================================ 외부연료탱크(ET) lh2 = [(0.0, ET_Z0)] for i in range(1, 9): t = i / 8 * math.pi / 2 lh2.append((ET_R * math.sin(t), ET_Z0 + 1.7 * (1 - math.cos(t)))) lh2 += [(ET_R, 33.5), (0.0, 33.5)] et_lh2 = lathe('ET_LH2_Tank', lh2, material=M_ET, seg=96) lox = [(0.0, 40.2), (ET_R, 40.2), (ET_R, 42.0)] L, R = 12.3, ET_R rho = (R * R + L * L) / (2 * R) for i in range(1, 25): zz = L * i / 24 r = math.sqrt(max(0.0, rho * rho - zz * zz)) + R - rho if r < 0.62: break lox.append((r, 42.0 + zz)) ztop = lox[-1][1] lox += [(0.55, ztop + 0.05), (0.22, ztop + 0.9), (0.06, ztop + 1.25), (0.0, ztop + 1.3)] et_lox = lathe('ET_LOX_Tank', lox, material=M_ET, seg=96) # 인터탱크: 주름(스트링거) 단면 def intertank(): N = 216 z0, z1 = 33.35, 40.35 verts, faces = [], [] for z in (z0, z1): for k in range(N): a = 2 * math.pi * k / N r = ET_R + (0.07 if (k // 2) % 3 == 0 else 0.03) verts.append((r * math.cos(a), r * math.sin(a), z)) for k in range(N): faces.append((k, (k + 1) % N, N + (k + 1) % N, N + k)) return build_mesh('ET_Intertank', verts, faces, [M_IT], smooth_all=False) et_it = intertank() for zz in (33.4, 40.3): torus('ET_Flange_Ring', R=ET_R + 0.06, r=0.09, loc=(0, 0, zz), material=M_IT, seg=96, rseg=8) # ================================================================ 고체로켓부스터(SRB) SRB_R = 1.855 SRB_Y = ET_R + SRB_R + 0.95 srb_prof = [(0.0, 3.0), (1.72, 3.0), (2.5, 0.0), (2.66, 0.0), (2.62, 0.3), (1.87, 3.4), (SRB_R, 3.45), (SRB_R, 39.0)] for i in range(1, 7): t = i / 6 srb_prof.append((SRB_R - 0.33 * t, 39.0 + 1.9 * t)) zc = 40.9 for i in range(1, 13): t = i / 12 r = 1.525 * (1 - t) ** 1.25 + 0.1 * (1 - t) srb_prof.append((max(r, 0.12), zc + 4.35 * t)) srb_prof += [(0.06, 45.36), (0.0, 45.42)] srb_body = lathe('SRB_Case', srb_prof, material=M_SRB, seg=64) srb_noz = bell('SRB_Nozzle', 0.7, 1.75, 2.8, M_SRBN, seg=48) srb_noz.location = (0, 0, 3.0) SRB_PARTS = [srb_body, srb_noz] for zz in (3.45, 11.4, 19.4, 27.4, 35.4, 38.9): SRB_PARTS.append(cylinder('SRB_Field_Joint', r=SRB_R + 0.035, h=0.38, loc=(0, 0, zz - 0.19), material=M_JOINT, seg=64, cap=False)) SRB_PARTS.append(cylinder('SRB_Aft_Attach_Ring', r=SRB_R + 0.07, h=0.55, loc=(0, 0, 9.2), material=M_JOINT, seg=64, cap=False)) srb_L = bpy.data.objects.new('SRB_Left', None) link(srb_L) parent_to(SRB_PARTS, srb_L) srb_L.location = (0, -SRB_Y, 0) srb_R = bpy.data.objects.new('SRB_Right', None) link(srb_R) srb_R.location = (0, SRB_Y, 0) for p in SRB_PARTS: c = duplicate(p, name=p.name) c.parent = srb_R srb_R.rotation_euler = (0, 0, math.pi) # SRB 부속: 시스템 터널, 홀드다운 포스트(로컬 좌표, 좌우 공유) SRB_EXTRA = [] ta = math.atan2(-0.87, 0.5) tun = box('SRB_Systems_Tunnel', (0.32, 0.26, 35.4), loc=((SRB_R + 0.1) * math.cos(ta), (SRB_R + 0.1) * math.sin(ta), 3.55), rot=(0, 0, ta), material=M_SRB, base=True) SRB_EXTRA.append(tun) for k in range(4): a = math.pi / 4 + k * math.pi / 2 SRB_EXTRA.append(box('SRB_Holddown_Post', (0.55, 0.45, 0.7), loc=(2.62 * math.cos(a), 2.62 * math.sin(a), 0.0), rot=(0, 0, a), material=M_JOINT, base=True)) for p in SRB_EXTRA: p.parent = srb_L c = duplicate(p, name=p.name) c.parent = srb_R # ================================================================ 결합 구조(월드) def strut(name, a, b, r=0.12, material=M_STRUT): return curve_tube(name, [a, b], radius=r, material=material, bevel_res=2) # 오비터 앞 바이포드 / 뒤 결합부 strut('ET_Orbiter_Forward_Bipod', (4.05, 1.1, 29.6), (ORB_X + 0.05, 0.0, ORB_Z + 24.3), 0.13) strut('ET_Orbiter_Forward_Bipod', (4.05, -1.1, 29.6), (ORB_X + 0.05, 0.0, ORB_Z + 24.3), 0.13) box('Forward_Bipod_Fitting', (0.6, 0.5, 0.5), loc=(ORB_X - 0.05, 0, ORB_Z + 24.3), material=M_STRUT) torus('ET_Aft_Attach_Ring', R=ET_R + 0.05, r=0.12, loc=(0, 0, 10.4), material=M_STRUT, seg=96, rseg=8) for sy in (1, -1): strut('ET_Orbiter_Aft_Strut', (4.0, sy * 1.3, 10.4), (ORB_X + 0.05, sy * 1.9, ORB_Z + 2.4), 0.16) strut('ET_Orbiter_Aft_Diagonal', (4.0, sy * 1.3, 10.4), (ORB_X + 0.05, sy * 0.4, ORB_Z + 3.4), 0.11) box('ET_Aft_Crossbeam', (0.5, 3.2, 0.45), loc=(4.05, 0, 10.4), material=M_STRUT) # LOX 피드라인(오비터 쪽 +Y) 과 LH2 엄빌리컬(-Y), 케이블 트레이 fa = math.radians(22) fx, fy = (ET_R + 0.32) * math.cos(fa), (ET_R + 0.32) * math.sin(fa) curve_tube('ET_LOX_Feedline', [(fx, fy, 36.8), (fx, fy, 11.6), (fx + 0.35, fy, 10.6), (ORB_X - 0.3, fy, ORB_Z + 1.5)], radius=0.22, material=M_ET, bevel_res=3) for zz in range(13, 36, 3): box('ET_Feedline_Bracket', (0.5, 0.18, 0.18), loc=(fx * 0.965, fy * 0.965, zz), rot=(0, 0, fa), material=M_ET) curve_tube('ET_LH2_Umbilical_Line', [(3.35, -1.7, 9.1), (4.4, -1.7, 8.5), (ORB_X - 0.3, -1.7, ORB_Z + 1.5)], radius=0.2, material=M_ET, bevel_res=3) for sy in (1, -1): box('Orbiter_ET_Umbilical_Plate', (0.45, 1.1, 1.3), loc=(ORB_X - 0.15, sy * 1.7, ORB_Z + 1.5), material=M_BASE) ca = math.radians(-24) cx, cy = (ET_R + 0.1) * math.cos(ca), (ET_R + 0.1) * math.sin(ca) box('ET_Cable_Tray', (0.24, 0.42, 29.5), loc=(cx, cy, 10.8), rot=(0, 0, ca), material=M_ET, base=True) # LOX 탱크 오자이브를 타고 오르는 가압 라인 pa = math.radians(-24) pts = [(r + 0.16, z) for r, z in lox[2:] if z <= ztop] curve_tube('ET_GOX_Pressurization_Line', [(r * math.cos(pa), r * math.sin(pa), z) for r, z in pts], radius=0.09, material=M_ET, bevel_res=2) # SRB-ET 결합: 앞(인터탱크) 볼트 박스, 뒤 스트럿 3개 for sy in (1, -1): box('SRB_Forward_Attach', (0.7, SRB_Y - SRB_R - ET_R + 0.5, 0.6), loc=(0, sy * (ET_R + SRB_Y - SRB_R) / 2, 37.6), material=M_STRUT) for x0, z0 in ((-1.1, 9.5), (0.0, 9.8), (1.1, 9.5)): strut('SRB_Aft_Attach_Strut', (x0, sy * (SRB_Y - math.sqrt(1.95 ** 2 - x0 ** 2) + 0.05), z0), (x0 * 0.85, sy * (math.sqrt(ET_R ** 2 - (x0 * 0.85) ** 2) - 0.08), 10.4), 0.13)