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Bacon B.J. Ostroff A.J. Joshi S.M. 《IEEE transactions on aerospace and electronic systems》2001,37(4):1373-1383
A modified derivation of nonlinear dynamic inversion provides the theoretical underpinnings for a reconfigurable control law for aircraft that have suffered combinations of actuator failures, missing effector surfaces, and aerodynamic changes. The approach makes use of acceleration feedback to extract information pertaining to any aerodynamic change and thus does not require a complete aerodynamic model of the aircraft. The control law does require feedback of effector positions to accommodate actuator dynamics. Both accelerometer and rate gyro failure detection and isolation (FDI) systems are implemented, allowing up to three independent failures for each FDI system as long as they are in different axes. Nonlinear simulation results show that the FDI systems improve the robustness to accelerometer/rate gyro uncertainties. An advanced tailless aircraft model is used to demonstrate the concepts. The simulation includes accelerometer and rate gyro noise and bias, failures due to accelerometers, rate gyros, and actuators, and modeled missing surfaces that cause airplane aerodynamic changes 相似文献
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E.A. Bering III L. Bacon K.K. Copper L.J. Hansen M.J. Sanchez 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2008
Many United States, school children perceive science, technology, engineering, and mathematics (STEM) as difficult, boring and often irrelevant subjects. The possible reasons for this problem are endlessly debated. However, the economic, social, and overall national importance of producing graduates who are technically literate and enthusiastic in their support of a rational scientific world is essential to our nation. This apparent STEM crisis should motivate the many scientific and engineering societies to develop STEM outreach programs aimed at students, parents, teachers and schools (grades K-12). 相似文献
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