report

Structural Finite-Element Load-Path Screening

Overall: PASS
Design signature: 9434dbaf01578074fb135f15e620cc7cfda0953da30298c00be7e7cbe7480e2c
Scope: stowed_telescope_to_bus_hexapod_restraints_platform_ring_support_skirt_primary_cell
Nodes / beam elements: 66 / 72
First FEM mode: 27.335 Hz
Represented translational mass: 244.618 kg

Case	Input g (x, y, z)	Max translation (mm)	Min stress FoS	Min buckling FoS	Critical buckling element	Unsupported span (m)	K
quasi_static_axial_compression	0.000, 0.000, -6.000	0.4510	26.307	9.855	strut_4_element_1	2.2900	1.0
quasi_static_lateral_x	2.000, 0.000, 0.000	0.9772	12.776	7.207	strut_1_element_1	2.8373	1.0
quasi_static_lateral_y	0.000, 2.000, 0.000	0.9801	11.759	6.619	strut_3_element_1	2.8373	1.0
sine_vibe_axial_compression	0.000, 0.000, -0.775	0.0582	203.740	76.326	strut_4_element_1	2.2900	1.0
sine_vibe_lateral_x	0.612, 0.000, 0.000	0.2989	41.763	23.558	strut_1_element_1	2.8373	1.0
sine_vibe_lateral_y	0.000, 0.612, 0.000	0.2998	38.439	21.636	strut_3_element_1	2.8373	1.0
random_vibe_axial_compression	0.000, 0.000, -3.109	0.2337	50.775	19.022	strut_4_element_1	2.2900	1.0
random_vibe_lateral_x	2.508, 0.000, 0.000	1.2252	10.190	5.748	strut_1_element_1	2.8373	1.0
random_vibe_lateral_y	0.000, 2.508, 0.000	1.2289	9.379	5.279	strut_3_element_1	2.8373	1.0
shock_axial_compression	0.000, 0.000, -6.611	0.4969	23.875	8.944	strut_4_element_1	2.2900	1.0
shock_lateral_x	4.083, 0.000, 0.000	1.9950	6.258	3.530	strut_1_element_1	2.8373	1.0
shock_lateral_y	0.000, 4.083, 0.000	2.0010	5.760	3.242	strut_3_element_1	2.8373	1.0

Each physical CFRP hexapod strut is subdivided into beam elements while preserving the exact released source endpoints.
Mesh subdivisions are not physical braces: every strut/restraint segment retains the full member span for Euler buckling, Pcr = pi^2 E I / (K L)^2.
The platform-ring, support-skirt, and primary-cell elements use the same dimensional formulas as the released CAD-like geometry.
The stowed launch-restraint elements use the released optimized restraint endpoints and tube section, including explicit platform attachment elements.
The bus-side hexapod and restraint lug nodes are fully restrained; the remaining nodes must retain a connected load path to them and a positive-definite constrained stiffness matrix.

The current finite-element mesh covers the telescope-to-bus hexapod, stowed launch restraints, platform ring, support skirt, and primary-cell ring only.
Other released subassemblies remain represented by payload mass at the primary-cell ring and must be meshed before the full-assembly TODO can close.
Sine, random-vibration, and shock inputs are conservative equivalent-static inertial loads sampled at the first FEM mode; PSD and response-spectrum dynamics remain open.
Buckling uses an Euler member check over each physical unsupported span with K = 1 (pinned ends); coupled frame instability, joint flexibility, and nonlinear/local buckling remain unmodelled.