Confronted with the challenges of hierarchical decision-making and dynamic strategy adaptation in UAV swarm defense, this paper introduces HO-SAP, a novel algorithm that synergizes hierarchical and opponent modeling. Our approach structures swarm decisions into tactical and execution layers and employs a learning-based strategy estimation mechanism to infer opponent behavioral patterns from observation sequences, embedding this awareness into the value function for superior generalization. We train a BiLSTM-based classifier to identify opponent strategy types through supervised learning, enabling defenders to adapt their tactics accordingly. Results across diverse adversarial scenarios reveal that HO-SAP significantly outperforms existing methods in critical metrics like defense success rate and interception efficiency, exhibiting exceptional adaptability and tactical planning. The hierarchical model ensures rational and scalable decisions, while opponent modeling enables dynamic responses, establishing an effective learning framework for swarm adversarial tasks.

High-pressure liquid CO₂ jets possess the characteristics of low-temperature cooling and dry, residue-free impact, which makes this technology particularly suitable for removing hydroxyl-terminated polybutadiene (HTPB) propellant from decommissioned solid rocket motors. However, existing studies lack multi-objective optimization of impact efficiency and CO₂ consumption, which limits their engineering applications and further promotion. In this study, a high-accuracy quadratic Response Surface Methodology (RSM) relating process parameters to damaged volume was established using a Box–Behnken design (BBD) combined with three-dimensional topography scanning. A theoretical model for CO₂ consumption was developed based on the Homogeneous Equilibrium Model (HEM). On this basis, the Non-dominated Sorting Genetic Algorithm II (NSGA-II) was used to obtain the Pareto-optimal set for maximizing propellant damaged volume and minimizing CO₂ consumption. The results indicate that nozzle diameter has the most significant effect on damaged volume and exhibits a strong interaction with jet pressure. The knee-point solution gives a jet pressure of 15.35 MPa, a stand-off distance of 5 mm, and a nozzle diameter of 1.8 mm. Compared with the initial condition, this compromise condition increases the damaged volume by 72% while increasing CO₂ consumption by only 4.9%. Furthermore, the temperature in the impact zone was reduced to a minimum of −92.4 °C, with no thermal accumulation observed. These findings reveal the influence of liquid CO₂ jet process parameters on impact efficiency and CO₂ consumption, providing a theoretical basis and parameter references for its engineering application in the safe removal of propellants from decommissioned solid rocket motors.