During the launch phase, rocket nozzles are subjected to complex dynamic loads, including blast wave loading due to engines ignition at lift-off and buffeting loads induced by aerodynamic pressure fluctuations acting on the nozzle. These loads are critical for nozzle design, particularly in preventing buckling. However, traditional buckling analyses often consider these dynamic loads as quasi-static, which can lead to overly conservative designs and an incomplete understanding of the structural response. Dynamic buckling remains a less explored and more challenging phenomenon to model compared to its quasi-static counterpart. Current design standards, such as NASA’s SP-8007 [1] and SP-8019 [2], are known for their conservative nature [3] and often fail to adequately account for the transient and dynamic characteristics of real-world loads. To address this shortcoming, works based on the Asymptotic Numerical Method (ANM) to detect static and dynamic instabilities have been performed. This work, conducted in collaboration between the French Space Agency (CNES) and the LEM3 Laboratory, builds on previous studies of cylindrical samples [4] to investigate dynamic buckling under blast wave loading and buffeting loads. These loads are represented by dynamic pressure fields and mechanical harmonicexcitations applied to the nozzle represented in this study by conical samples. This paper primarily focuses on the methods and numerical results obtained from test-calculation correlations performed on conical samples. The ANM offers a distinct advantage in this context: it efficiently identifies bifurcation paths in large-scale systems, where traditional incremental methods, such as Newton-Raphson, either fail or demand prohibitive computational resources [5]. By leveraging the ANM, this work aims to provide a robust and computationally efficient alternative for detecting early bifurcations, thereby enhancing the reliability of structural predictions for critical aerospace components [6, 7, 8]. This research serves as a preliminary step toward analyzing the nozzle’s complex wall structure, which features hollow channels for thermal management. Ultimately, this work aims to establish a more efficient and reliable framework for structural design in aerospace applications, moving beyond the limitations of current conservative standards.