Abstract: A system and method for automatic modal parameter extraction in structural dynamics analysis are disclosed. In one embodiment, a stabilization diagram of a structure is obtained using a frequency domain parameter extraction technique. The stabilization diagram is a graph of measured transfer functions which include stable poles of the structure for each modal order versus frequencies which include modal frequencies of each stable pole. Further, a user is allowed to input user modal parameters, such as a maximum damping ratio, maximum number of stable poles to be selected from the stabilization diagram, and minimum separation in frequency between consecutive stable poles. Furthermore, stable poles having a damping ratio less than or equal to the maximum damping ratio are obtained. A histogram having bins, with a width equal to the minimum separation in frequency, is obtained. Also, the modal parameter of the structure is automatically extracted using the histogram.

Abstract: A system and method for providing an aircraft noise advisory during departure and/or arrival of an aircraft are disclosed. In one embodiment, predefined allowable aircraft noise level information associated with a plurality of aircraft noise sensors located in the vicinity of airports are obtained. Further, predefined allowable aircraft noise level information associated with one or more of the plurality of aircraft noise sensors is presented on a display device in the aircraft, based on a current location of the aircraft, upon receiving noise data request from a pilot. Furthermore, current aircraft noise level information is obtained from one of the one or more aircraft noise sensors. In addition, the current aircraft noise level information is compared with predefined allowable aircraft noise level information associated with the one of the one or more aircraft noise sensors. Also, the aircraft noise advisory is displayed based on an outcome of the comparison.

Abstract: Shape memory stainless steels with rare earth elements Cerium (Ce) and Lanthanum (La) are disclosed. In one embodiment, raw materials including Manganese (Mn), Silicon (Si), Chromium (Cr), Nickel (Ni), Carbon (C), Ce, La and Iron (Fe) are melted to form a molten alloy of the shape memory stainless steels with rare earth elements Ce and La. Further, the molten alloy is solidified to form an ingot. Furthermore, the ingot is subjected to nondestructive evaluation to assess internal soundness of the ingot. In addition, the evaluated ingot is homogenized to form homogenized shape memory stainless steels with rare earth elements Ce and La.

Abstract: A system and method for simulating aerodynamics over an aircraft for a deflected position of a movable aircraft control surface using a structured chimera mesh are disclosed. In one embodiment, a mesh assembly of the aircraft is created by overlapping a background mesh and a structured chimera mesh for the deflected position of the movable aircraft control surface. Further, mesh cell sizes within overlapping boundaries of the background mesh and the structured chimera mesh are analyzed. Furthermore, the structured chimera mesh is regenerated based on the analysis. In addition, the mesh assembly of the aircraft is reformed based on the regenerated structured chimera mesh. Also, a masked mesh of the aircraft is created by auto masking the reformed mesh assembly. Moreover, aerodynamics is simulated over the aircraft for the deflected position of the movable aircraft control surface using the masked mesh.