{'fraction_non_alphanumeric': 0.015131578947368421, 'fraction_numerical': 0.0, 'mean_word_length': 5.945205479452055, 'pattern_counts': {'":': 0, '<': 0, '<?xml version=': 0, '>': 0, 'https://': 0, 'lorem ipsum': 0, 'www.': 0, 'xml': 0}, 'pii_count': 0, 'substrings_counts': 0, 'word_list_counts': {'cursed_substrings.json': 0, 'profanity_word_list.json': 0, 'sexual_word_list.json': 0, 'zh_pornsignals.json': 0}}
A Conceptual Aerospace Vehicle Structural System Modeling, Analysis and Design Process

Using examples of a flying wing mega transport, a crew exploration vehicle, and a high altitude long endurance aircraft, an efficient structural model development and design process is presented. Aerospace vehicle structures must withstand all anticipated mission design loads, yet must be designed with optimal structural weight with the required safety margins. For a viable systems study of advanced concepts, these conflicting requirements must be imposed and analyzed early in the conceptual design cycle, preferably with a high degree of fidelity. In this design process, integrated multidisciplinary analysis tools are used in a collaborative engineering environment. First, parametric solid and surface models including the internal structural layout are developed for detailed finite element analyses. Multiple design scenarios are rapidly generated for analyzing several structural configurations and material alternatives. The structural stress, deflection, strain, and margins of safety distributions are visualized and the design is improved. Over several design cycles, the refined vehicle parts and assembly models are generated. The accumulated design data is used for structural mass comparison and concept ranking. This integrated process is presently being used for advanced composite materials and structures applications under the Subsonic Fixed Wing project in the Fundamental Aeronautics Program. Nomenclature