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Hubble Space Telescope (HST): Optical Tube, Solar Wings & HGA
Cylindrical shell baffle tube, open aperture hood, primary mirror ring bulkhead, 2 solar array wings, and high-gain dish antennas.
Verify global structural stiffness, solar array wing deflection, and modal dynamic spectrum of the Hubble Space Telescope under orbital maneuvering acceleration and solar photon pressure, preventing thermo-elastic jitter from degrading optical pointing stability.
1. Geometry & FEA Mesh
- •13.2 m telescope optical tube: Ø 4.3 m aft instrument shroud, conical transition collar, and Ø 3.0 m forward baffle modeled with conformal MITC4 cylindrical shell patches (t = 4 mm and 3 mm)
- •Reinforced by 7 circular ring frames and Ø 2.4 m heavy primary mirror bulkhead ring with 8 radial stiffener struts
- •Aperture door hood modeled as an inclined 45° open quad shell lid (3.2×3.2 m) with perimeter stiffeners at the sunshade rim
- •4-arm orthogonal secondary mirror spider (d = 150 mm) supporting central mirror hub at station x = 11.5 m
- •Two deployable solar array wings (7.2×2.4 m) on articulated boom struts, stiffened with longitudinal and transverse tubular ribs
- •Two steerable high-gain parabolic dish antennas (Ø 1.2 m) on tubular cantilever booms
- •Full model: 1,340 nodes, 653 beam elements, 308 shell quads, 8,040 active DOFs
2. Loads & Boundary Conditions
- •Aft berthing ring nodes at x = 0 fixed in 6 DOFs (representing payload bay latches / orbital gyro stabilization)
- •1g lateral maneuvering inertia load + solar radiation photon pressure p = -50 Pa on both solar wings
- •Zero skips, zero crosses, and 0 shellcheck errors verified by topology audit
3. Simulation Results & Findings
- ✓Maximum static displacement |u| = 604.5 mm at the flexible outer tips of the solar array wings under 1g inertia test
- ✓Optical barrel and mirror bulkhead show negligible elastic distortion (< 0.25 mm), preserving primary-to-secondary alignment
- ✓Fundamental bending frequency f₁ = 0.947 Hz (symmetric solar array out-of-plane flap mode), f₂ = 0.951 Hz (anti-symmetric flap)
- ✓First critical buckling multiplier λ₁ = 3.65 (elastic buckling of solar wing deployable mast compression struts)
Rapid browser-native qualification of space telescope pointing stability and solar wing dynamic coupling without multi-million-dollar legacy aerospace CAE licenses.
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