To improve energy utilization efficiency and reduce shock hazards in explosive separation processes for carbon fiber woven composites, this study introduces an innovative separation method that uses symmetrical rectangular weakening grooves prefabricated on both sides of the composite panels, combined with linear shaped-charge cutting techniques. Through integrated numerical simulation and experimental validation, this research utilizes Autodyn simulation software to investigate jet formation states, composite material velocities, and energy variation trends across different explosive separation configurations. Comparative analysis of simulation outputs and experimental measurements elucidates how rectangular weakening grooves and composite groove structures, optimized based on linear jet development characteristics, influence the explosive separation performance of composite material plates. Results demonstrate that the proposed explosive separation method can effectively separate composite materials while preventing extensive delamination during the impact process. The composite groove configuration optimizes jet expansion space, markedly enhancing jet velocity and penetration capacity while minimizing fragment impact on adjacent components.

During aero-engine casing containment tests, the explosive separation method used to achieve the constant-speed fly-off of titanium alloy blades often produces a bright titanium fire phenomenon. This titanium fire obstructs high-speed camera recording of the blade fly-off process. To address this issue, this study analyzed the mechanism of titanium fire generation and proposed a barrier layer method to suppress titanium fire during shaped energy cutting of titanium alloys. Numerical simulations using the Euler algorithm in AUTODYN were conducted to evaluate the blocking effect of the barrier layer and its feasibility for titanium fire suppression. Experimental investigations were then performed to quantitatively assess the brightness reduction of titanium fire, comparing the effectiveness of four barrier materials. The results indicate that 0.1mm thick aluminum and titanium tin foil achieve titanium fire suppression rates of 29.5% and 24%, respectively, demonstrating moderate effectiveness. A 0.1 mm thick copper sheet shows poor performance with a suppression rate of only 4.3%, while a 0.1 mm thick aluminum silicate coating exhibits the best performance, achieving a suppression rate of 70.9%. This study has summarized the mechanism of titanium fire suppression suing barrier layers during shaped energy cutting of titanium alloy plates and validated the feasibility of the barrier layer method. The findings can provide a practical approach for titanium fire elimination in explosion separation processes involving shaped energy cutting of titanium alloys.

A study was conducted using explosive cutting cords to titanium alloy plates to quantitatively investigate the additional kinetic energy generated during blade fracture in aviation engine case inclusion experiments. The additional kinetic energy was analyzed through both computational and experimental approaches. Using AUTODYN software, two computational methods were employed: the center-of-mass motion method(yielding E1) and the particle-by-particle accumulation method(yielding E2). The accuracy of these methods was systematically compared. Experimental validation was achieved by measuring the additional kinetic energy(E3) in controlled explosion experiments. The computational results were verified against experimental data, confirming the reliability of both the simulation and testing methodologies. The study reveals that the maximum additional kinetic energy generated during the severance of titanium alloy plates constitutes a smaller proportion of the total kinetic energy proportion than the threshold proposed by the FAA company. These findings provide critical insights for designing and evaluating cartridge inclusion experiments in aviation safety applications.