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Full-scale aircraft structural fatigue tests are extremely complex, not only in terms of the test definition and implementation, but also from the control systems viewpoint. The load spectra that these tests are subjected to are also becoming more complex as manufacturers and certifying authorities strive for more realistic loading conditions. At the same time, there is pressure to complete the test more quickly or at least in the same time as previous tests that were simpler and contained fewer cycles. This can only be achieved by optimizing the test configuration and control system parameters or in some cases implementing new control strategies. This is difficult on a full-scale test because of all the complex interactions on these multi-channel tests. Methods that may work well on smaller tests can sometimes result in poorer performance. Thus there is a need for a greater understanding of the system and some predictive capability. This can be achieved with computer modeling.