The damage mechanism of ultra-thick laminates widely used in aerospace and marine industries was obviously different from that of thin laminates. However, compression testing and simulation methods were generally limited to relatively thin laminates. To explore the compressive failure behavior of ultra-thick laminates, Firstly, a layered pre-compaction scheme was proposed to ensure the curing quality of ultra-thick laminates. A heavy-duty compression test equipment (accuracy reached 0.001 mm) was then developed, and a novel compression test method for ultra-thick composite laminates was proposed. The results showed that delamination played a key role in the failure behavior of ultra-thick laminates. The low interlaminar normal strength of ultra-thick laminates (55% of the 2 mm thin laminate) led to premature delamination, and wrinkle defects seriously reduced the compressive strength (11%). The compressive behavior for the matrix-dominant failure specimen predicted by the Puck criterion was the smallest (0.07%), while Tsai-Wu 3D predicted the smallest error (5.1%) for the delamination-dominant specimen. Finally, these findings are helpful for the design of ultra-thick composite structures.

广泛应用于航空航天和海洋工业的超厚层合板的损伤机理与薄层合板明显不同。然而，压缩测试和模拟方法通常仅限于相对较薄的层压板。为探究超厚层合板的压缩破坏行为，首先提出分层预压实方案以保证超厚层合板的固化质量。研制了精度达到0.001 mm的重型压缩试验装置，提出了一种超厚复合材料层合板压缩试验新方法。结果表明，分层对超厚层合板的失效行为起着关键作用。超厚层压板的低层间法向强度（2 毫米薄层压板的 55%）导致过早分层，皱纹缺陷严重降低了抗压强度 (11%)。Puck 准则预测的以基体为主的失效试样的压缩行为最小 (0.07%)，而 Tsai-Wu 3D 预测以分层为主的试样的误差最小 (5.1%)。最后，这些发现有助于超厚复合材料结构的设计。