Abstract: Composite materials have been widely used in aircraft structures, and gradually applied to the main load-bearing structures. However, the brittle characteristic of composite materials has brought new challenges for aircraft crashworthiness design and evaluation. As the important energy-absorbing element, the composite stanchions for the cargo floor structure seriously affect the crashworthiness properties of composite fuselage. Composite stanchions can be designed to absorb much more energy through crushing failures than in a brittle global buckling mode. Based on the design requirements of the civil aircraft composite cargo floor stanchion, the trigger configuration, height, section, and section area were evaluated using quasi-static and dynamic crushing tests. The key influence factors of energy absorption characteristic properties for woven T700GC carbon fiber/epoxy composite stanchions were estimated. It provides reference for the structure design.