This is a review by two trial lawyers of the practical problems in trying a psychiatric malpractice lawsuit. The substantive rules of law which receive a good deal of attention are found to be most significant in the day-to-day suit than gathering together the facts and medical opinions and presenting them to the jury in a persuasive fashion.
The Space Launch System, NASA's new large launch vehicle for long range space exploration, is presently in the final design and construction phases, with the first launch scheduled for 2019. A dynamic model of the system has been created and is critical for calculation of interface loads and natural frequencies and mode shapes for guidance, navigation, and control (GNC). Because of the program and schedule constraints, a single modal test of the SLS will be performed while bolted down to the Mobile Launch Pad just before the first launch. A Monte Carlo and optimization scheme will be performed to create thousands of possible models based on given dispersions in model properties and to determine which model best fits the natural frequencies and mode shapes from modal test. However, the question still remains as to whether this model is acceptable for the loads and GNC requirements. An uncertainty propagation and quantification (UP and UQ) technique to develop a quantitative set of validation metrics that is based on the flight requirements has therefore been developed and is discussed in this paper. There has been considerable research on UQ and UP and validation in the literature, but very little on propagating the uncertainties from requirements, so most validation metrics are "rules-of-thumb;" this research seeks to come up with more reason-based metrics. One of the main assumptions used to achieve this task is that the uncertainty in the modeling of the fixed boundary condition is accurate, so therefore that same uncertainty can be used in propagating the fixedtest configuration to the free-free actual configuration. The second main technique applied here is the usage of the limit-state formulation to quantify the final probabilistic parameters and to compare them with the requirements. These techniques are explored with a simple lumped spring-mass system and a simplified SLS model. When completed, it is anticipated that this requirements-based validation metric will provide a quantified confidence and probability of success for the final SLS dynamics model, which will be critical for a successful launch program, and can be applied in the many other industries where an accurate dynamic model is required.
This paper presents the results of an investigation into the behavior of an elastic beam that is loaded by a frictionless cylindrical indenter. Results are obtained using a solution which incorporates both local contact behavior as well as global beam behavior. The solution is obtained by superposing an elastic layer solution derived through the use of integral transforms and the cylindrical bending solution for a flat plate. The problem reduces to two coupled Fredholm integral equations of the second kind which are solved numerically. Local contact stresses and load-deflection relations are examined in detail for various geometric and contact parameters. The results are compared to Hertz theory contact stresses and beam theory deflection predictions.
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