🛡️ Cryogenic Multilayer Insulation (MLI)
Size spacecraft and cryogenic Multilayer Insulation (MLI) blankets, computing total heat flux (W/m²), effective thermal conductivity keff, and daily cryogen boil-off rate (LH2, LN2, LHe).
⚡ Fortran 90 Engine
Double Precision (IEEE 754)
✓ ISO / ASME Validated
📊 Solver Telemetry
● ACTIVE
👁️ Consultations
18
⚡ Calculs faits
16
💾 Téléchargements
321
📦 Code Fortran
5.4 KB
📅 Mise en service
Jun 2026
⏱️ Latence
< 1 ms
🛡️ Vacuum Multilayer Radiation Shields & Cryogenic Barrier
Real-time visual simulation of reflective foil radiation bounces, Dacron spacer mesh & residual gas conduction📝 Configuration & Presets
🚀 Liquid H2 (LH2) Rocket Tank
❄️ Liquid N2 (LN2) Dewar
🧲 Superconducting MRI (LHe)
🛰️ GEO Satellite Blanket
Lockheed / McIntosh MLI Formulation:
• Radiation: q″rad = σ (Th⁴ − Tc⁴) / [ (N+1)(2/ε − 1) ]
• Solid Spacers: q″solid = 7.3×10⁻⁵ N̄2.63 Tmean ΔT / N
• Residual Gas: q″gas = 14600 Pvac (Th0.52 − Tc0.52) / N
• Effective Conductivity: keff = q″tot · Δx / (Th − Tc) [W/(m·K)]
• Radiation: q″rad = σ (Th⁴ − Tc⁴) / [ (N+1)(2/ε − 1) ]
• Solid Spacers: q″solid = 7.3×10⁻⁵ N̄2.63 Tmean ΔT / N
• Residual Gas: q″gas = 14600 Pvac (Th0.52 − Tc0.52) / N
• Effective Conductivity: keff = q″tot · Δx / (Th − Tc) [W/(m·K)]
📊 MLI Thermal Results
Configure inputs and click Compute to view results.
📘 Calculation Methodology & Cryogenic MLI Standards
Lockheed & McIntosh Semi-Empirical Model
Decomposes heat transfer through vacuum multilayer insulation into three distinct parallel mechanisms:
q″total = q″radiation + q″solid_spacers + q″residual_gas
Optimum Layer Density
Increasing shield density $\bar{N}$ suppresses radiation but increases solid spacer contact conduction. Optimum density is typically $20 - 30\,\text{layers/cm}$.
Key Engineering Assumptions
- Double-aluminized Mylar (DAM) or Kapton with Dacron mesh spacers.
- Free-molecular regime for residual gas ($Kn \gg 10$ at $P < 10^{-4}\,\text{Torr}$).
- Applicable to $LH_2, LN_2, LHe, LOX, LCH_4$ storage and satellites.