This manuscript presents experimental results of compression tests of repaired sandwich structure typical of a launch vehicle Payload Adapter Fitting (PAF) that is being considered for the National Aeronautics and Space Administration’s (NASA) Space Launch System (SLS) launch vehicle. Specimens with 8-ply quasi-isotropic carbon/epoxy face sheets and aluminum honeycomb core were damaged with representations of misdrilled holes, barely visible impact damage (BVID) or visible impact damage (VID). A patch repair technique not requiring removal of any material is presented and assessed for residual in-plane compressive load-carrying capability on each of the three types of damage. Edgewise compression tests on specimens demonstrated the repairs could recover all measured undamaged compressive load-carrying capability of the misdrilled hole and BVID specimens. For the specimens with VID, an average of about 91% of the average measured undamaged compressive load carrying capability was recovered indicating that larger patches, or perhaps removal and replacement of the damaged material, may be needed for more severe damage if all the measured undamaged compression strength needs to be regained.

该手稿介绍了典型的运载火箭有效载荷适配器配件（PAF）修复的夹心结构压缩测试的实验结果，美国航空航天局（NASA）的航天发射系统（SLS）运载火箭正在考虑该结构。带有8层准各向同性碳/环氧树脂面板和铝蜂窝芯的样品损坏，出现钻孔错误，几乎看不见的冲击损伤（BVID）或可见的冲击损伤（VID）。提出了一种修补技术，不需要去除任何材料，并评估了三种损坏类型中每种损坏的残余面内压缩承载能力。在样品上进行侧向压缩试验表明，修复可以恢复钻孔和BVID样品所有测得的未损坏压缩承载能力。对于具有VID的样品，平均回收了约91％的平均未损坏压缩载荷承载能力，这表明，如果所有未损坏的测量都未损坏，则可能需要更大的补丁，或者可能是去除和更换损坏的材料，才能造成更严重的损坏。需要恢复抗压强度。