## 1 Introduction
Specifically, it was found that the stacking sequence [0\({}^{\circ}\)/90\({}^{\circ}\)] demonstrated a lower level of failure compared to [45\({}^{\circ}\)/ \(-\)45\({}^{\circ}\)] for both CFRP and thin-ply configurations. Another study [21] focused on failure mechanisms, which involved subjecting the thin-ply CFRP laminates to tensile loading. Initially, experiments were conducted to assess the tensile behavior of 15\({}^{\circ}\) and 30\({}^{\circ}\) ply angles, and finally, FEM models were developed to anticipate the failure mode. The failure strains for the mentioned ply angles varied depending on the different fiber areal weights. Specifically, when the ply angle was 15\({}^{\circ}\), the failure strains were 1.187%, 1.35%, and 1.22% for corresponding areal weights of 20, 60, and 120 g/m\({}^{2}\). In contrast, when the ply angle was 30\({}^{\circ}\), the failure strains were 3.52%, 4.94%, and 2.9% for the same areal weights. As such, numerous efforts have sought to quantify the orientation of CFRP laminates using nondestructive evaluation (NDE) in an automated fashion. It should be noted that works related to NDE for the orientation of layered materials to date have been primarily limited to CFRP laminates as opposed to AM components, which is the focus of this work. One of the most notable works was performed by [PERSON] [22], where he investigated the orientation of plies within a unidirectional CFRP skin over a honeycomb sandwich structure. Two techniques were applied to ascertain the ply stacking arrangements. The initial method utilized a portable scanner for the ultrasonic scanning of composites, while the second method required the capture of the full waveform at each point in the scan, the latter of which could effectively distinguish the ply orientations of 0\({}^{\circ}\), 45\({}^{\circ}\), and 90\({}^{\circ}\). [PERSON] et al. [23] enhanced the automation process of stacking sequences by employing the 2D FFT method to examine the ply orientation of CFRP laminates. C-scan images were generated using the longitudinal wave that extracted fiber orientation information. Their laboratory experiments demonstrated the feasibility of determining the fiber orientations by up to 20 plies. In another study [24], evaluating layup configuration, [PERSON] used a contact-mode ultrasonic transducer with shear waves to deduce the percentages of 0\({}^{\circ}\) and 90\({}^{\circ}\) oriented plies from 24 groups of [0\({}^{\circ}\)/90\({}^{\circ}\)] plies. [PERSON] et al. [25] developed a tool titled StackScanTM to automate the process of arranging ply stacking sequences. This tool provided an accelerated method to detect exact ply orientations with an error margin of 0.5\({}^{\circ}\). [PERSON] et al. [26] demonstrated how laser ultrasound systems can be employed to detect variations in the ply alignment of composites. In this method, the laser-generated ultrasound signals were used to produce B-scans with a minimal amount of interference, facilitating the visualization of individual plies. However, due to the strong attenuation of the signal in layered composites, significant signal loss occurs at depths exceeding 7-10 mm. Another investigation of CFRP laminates investigated the heating pattern in such composites, determining them to be influenced by fiber orientations [27]. To explore this unique heating behavior, orientations of carbon fiber laminates were assessed using the 2D FFT method of the captured transient thermal surface distributions, leading to the conclusion that thermography can be implemented on specimens consisting of 12 layers to identify fiber orientations, with the maximum error compared to the designed orientation of 6\({}^{\circ}\). The present study of automating the raster orientation process from the captured waveform is an extension of the earlier study by the current authors [28; 29] that presents a manual approach to identify the raster orientation in a layer-by-layer manner. The study illustrated in this article expands on the methodology proposed in [PERSON] et al.