MODAL TEST OF A LARGE SPACECRAFT USING A MASS-LOADED INTERFACE
A finite-element mathematical model of a large spacecraft structure is validated through a modal test survey. The spacecraft is bolted via its adapter to a steel base plate which served as an inertial reaction mass. The inertial base plate supported by five low-frequency air supports provides a free...
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| Veröffentlicht in: | Experimental techniques (Westport, Conn.) Conn.), 1992-11, Vol.16 (6), p.15-20 |
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| container_title | Experimental techniques (Westport, Conn.) |
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| creator | Haughton, J.M. Hauser, J.A. Turner, L.M. |
| description | A finite-element mathematical model of a large spacecraft structure is validated through a modal test survey. The spacecraft is bolted via its adapter to a steel base plate which served as an inertial reaction mass. The inertial base plate supported by five low-frequency air supports provides a free-free boundary for the combined plate/spacecraft system. Sufficient separation between rigid and flexible mode frequencies is verified by measuring rigid-body mode frequencies. This technique is aimed at producing test boundary conditions which could be easily reproduced in analysis and a modal vector set to simulate the in-service modal vectors. (O.G.) |
| doi_str_mv | 10.1111/j.1747-1567.1992.tb00715.x |
| format | Article |
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| ispartof | Experimental techniques (Westport, Conn.), 1992-11, Vol.16 (6), p.15-20 |
| issn | 0732-8818 1747-1567 |
| language | eng |
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| source | SpringerLink Journals - AutoHoldings |
| title | MODAL TEST OF A LARGE SPACECRAFT USING A MASS-LOADED INTERFACE |
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