Set up your own cloud-native simulation in minutes.Start Simulating Now
2 Geometries
4 Meshes
2 Simulation setups
2 ResultsPrecision space-based optical mirrors experience non-uniform thermal loading in orbit due to solar radiation and deep-space cooling. This temperature differential generates internal thermal stresses ($\sigma_{th}$) that induce out-of-plane plate bending ($\delta$), leading to optical defocus and surface degradation. This study presents a comparative structural design and finite element simulation evaluating a $300\text{ mm}$ solid circular mirror disk (Model A) against an engineered lightweight mirror featuring an integrated hexagonal honeycomb backing grid (Model B).Operating under simulated orbital boundary conditions with an effective solar absorptivity of $5\%$ ($Q_{abs} \approx 68 \text{ W/m}^2$), a $3\text{ K}$ radiative sink, and a 3-point kinematic mount support, both geometries were analyzed for mass reduction, steady-state thermal distribution, and structural deflection. Analytical hand calculations using thin-plate thermal curvature theory were performed to validate the simulation order of magnitude. Results demonstrate that the honeycomb-backed configuration achieves a $\approx 55\%$ mass reduction while maintaining high flexural rigidity ($D$), significantly mitigating peak-to-valley thermal surface bowing into the low-micrometer regime without requiring heavy structural active optics.
0
0
by mwavinyamwavinya
by ahmedhussain18ahmedhussain18
by ahmedhussain18ahmedhussain18
by ahmedhussain18ahmedhussain18
t_raja_21 created this project
2 Geometries 4 Meshes 2 Simulation setups 2 ResultsPrecision space-based optical mirrors experience non-uniform thermal loading in orbit due to solar radiation and deep-space cooling. This temperature differential generates internal thermal stresses ($\sigma_{th}$) that induce out-of-plane plate bending ($\delta$), leading to optical defocus and surface degradation. This study presents a comparative structural design and finite element simulation evaluating a $300\text{ mm}$ solid circular mirror disk (Model A) against an engineered lightweight mirror featuring an integrated hexagonal honeycomb backing grid (Model B).Operating under simulated orbital boundary conditions with an effective solar absorptivity of $5\%$ ($Q_{abs} \approx 68 \text{ W/m}^2$), a $3\text{ K}$ radiative sink, and a 3-point kinematic mount support, both geometries were analyzed for mass reduction, steady-state thermal distribution, and structural deflection. Analytical hand calculations using thin-plate thermal curvature theory were performed to validate the simulation order of magnitude. Results demonstrate that the honeycomb-backed configuration achieves a $\approx 55\%$ mass reduction while maintaining high flexural rigidity ($D$), significantly mitigating peak-to-valley thermal surface bowing into the low-micrometer regime without requiring heavy structural active optics.
