| タイトル | SSME structural dynamic model development, phase 2 |
| 本文（外部サイト） | http://hdl.handle.net/2060/19860011025 |
| 著者（英） | Foley, M. J.; Wilson, V. L. |
| 著者所属（英） | Lockheed Missiles and Space Co. |
| 発行日 | 1985-11-01 |
| 言語 | eng |
| 内容記述 | A set of test correlated mathematical models of the SSME High Pressure Oxygen Turbopump (HPOTP) housing and rotor assembly was produced. New analysis methods within the EISI/EAL and SPAR systems were investigated and runstreams for future use were developed. The LOX pump models have undergone extensive modification since the first phase of this effort was completed. The rotor assembly from the original model was abandoned and a new, more detailed model constructed. A description of the new rotor math model is presented. Also, the pump housing model was continually modified as additional test data have become available. This model is documented along with measured test results. Many of the more advanced features of the EAL/SPAR finite element analysis system were exercised. These included the cyclic symmetry option, the macro-element procedures, and the fluid analysis capability. In addition, a new tool was developed that allows an automated analysis of a disjoint structure in terms of its component modes. A complete description of the implementation of the Craig-Bampton method is given along with two worked examples. |
| NASA分類 | SPACECRAFT PROPULSION AND POWER |
| レポートNO | 86N20496
NAS 1.26:178708
LMSC-HEC-TR-F042668
NASA-CR-178708 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/154654 |
