| タイトル | A Conceptual Aerospace Vehicle Structural System Modeling, Analysis and Design Process |
| 本文（外部サイト） | http://hdl.handle.net/2060/20070018831 |
| 著者（英） | Mukhopadhyay, Vivek |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 2007-01-01 |
| 言語 | eng |
| 内容記述 | A process for aerospace structural concept analysis and design is presented, with examples of a blended-wing-body fuselage, a multi-bubble fuselage concept, a notional crew exploration vehicle, and a high altitude long endurance aircraft. Aerospace vehicle structures must withstand all anticipated mission loads, yet must be designed to have 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 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 the structural mass comparison and concept ranking. The present application focus on the blended-wing-body vehicle structure and advanced composite material are also discussed. |
| NASA分類 | Spacecraft Design, Testing and Performance |
| レポートNO | AIAA 2007-2372 |
| 権利 | No Copyright |
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