<p>In the design of pyrotechnic separation devices, while the fracture mechanics and structural optimization of metal material protective covers have been extensively studied. Given the stringent payload constraints of launch vehicles, where costs are calculated per gram, the development of lightweight composite protective covers presents significant engineering potential. Compared with common thermosetting composite materials, carbon fiber fabric-reinforced polyphenylene sulfide (CFF/PPS) thermoplastic composites (referred to as PPS composite material) have the advantages of high temperature resistance, rapid thermoforming and recyclability. This study aims to investigate the feasibility of employing PPS composites as protective covers. To evaluate the performance of PPS composite protective covers, shaped-charge cutting tests were conducted, with separation effectiveness assessed based on the delamination degree of the carbon fiber reinforced polymer (CFRP) separation plate and the damage of the protective cover. The results indicate that while the PPS composite protective cover exhibits sufficient strength, its plasticity is severely limited. During the cutting test, the protective cover fractured, failing to fully perform its intended protective function. However, the CFRP separation plate exhibited minimal delamination, demonstrating an effective cutting performance. This study highlights a critical limitation of PPS composites—low plasticity—which affects their ability to withstand impact and deformation. Despite this, their energy absorption characteristics show promise in reducing shock effects. Future research should focus on enhancing the toughness and impact resistance of PPS composites through material modifications and process optimizations. The ultimate goal is to develop high-plasticity composite protective covers that meet the demanding requirements of spacecraft lightweighting and impact mitigation, thereby advancing their practical application in aerospace engineering.</p>