| タイトル | Preliminary analysis and design optimization of the short spacer truss of Space Station Freedom |
| 本文（外部サイト） | http://hdl.handle.net/2060/19940011236 |
| 著者（英） | Patnaik, S. N.; Hopkins, D. A.; Berke, L.; Gendy, A. S. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1993-08-01 |
| 言語 | eng |
| 内容記述 | The analysis, dynamic simulation, and design optimization of the short spacer truss of the Space Station Freedom are presented in this report. The short spacer truss will be positioned between the integrated equipment assembly (IEA) and another truss, called the long spacer truss, in the Space Station Freedom. During its launch in the Space Shuttle, the truss will be subjected to considerable in-span distributed inertia loads due to shuttle accelerations. The short spacer truss, therefore, has been modeled as a space frame to account for flexural response. Several parameters have been assumed, since the design specifications are in the process of development; hence the results presented should be considered preliminary. However, the automated analysis and design capabilities that have been developed can readily be used to generate an optimum design of the short spacer truss once the actual specifications have been determined. This report includes static and dynamic analyses of the short spacer truss, which have been obtained with the linear elastic code LE-HOST (in these analyses, LE-HOST data files have been automated to facilitate their future use for different design specifications of the short spacer truss); the dynamic animation of the short spacer truss, which has been carried out by using the results of the dynamic analysis and a post-processing feature of the modeling code PATRAN; and the optimum-weight design of the spacer truss, which was obtained under prescribed stress, displacement, and frequency constraints by using the design code COMETBOARDS. Examination of the analysis and design results revealed that the design could be improved if the configuration of the short spacer truss were modified to a certain extent. A modified configuration, which may simplify fabrication, has been suggested. The performance of this configuration has been evaluated and was found to be satisfactory under both static and dynamic conditions. |
| NASA分類 | STRUCTURAL MECHANICS |
| レポートNO | 94N15709
NASA-TM-4470
E-7653
NAS 1.15:4470 |
| 権利 | No Copyright |
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