Browse Topic: Hardening
This paper investigates a sliding-window matrix pencil method for predicting flutter points and limit-cycle oscillation amplitudes of nonlinear aeroelastic systems that experience whirl flutter. The approach applies the matrix pencil method to a short time window that slides along the free decay of a quantity of interest, quantifying the variation in the system's recovery rate to equilibrium with amplitude. The recovery rates at each amplitude and various forward speeds are extrapolated to predict the critical forward speed of zero recovery rate at those amplitudes. This process yields a set of limit-cycle oscillation solutions that can be visualized as a bifurcation diagram. The approach is demonstrated using output data from transient simulations of a propeller-nacelle test case with hardening structural nonlinearities. The impact of each parameter in the sliding-window matrix pencil method is first characterized via sensitivity analyses. Next, the bifurcation diagram is predicted
This specification covers a dilute aluminum/TiB2 metal matrix composite in the form of investment castings.
ABSTRACT Steel components, such as gears for rotorcraft transmissions, are quench hardened to improve the hardness, strength, and fatigue performance. During a quench hardening process, components are heated to form austenite, followed by quenching (either gas or liquid) to transform to hard martensite. With High Pressure Gas Quenching (HPGQ), parts are rapidly cooled by using a pressurized gas such as Nitrogen or Helium. Hardening is a highly nonlinear process due to the plastic deformation caused by thermal stresses and phase transformations, both of which lead to distortion. Reducing distortion caused by hardening has always been pursued by heat treaters for the purposes of improving part quality and reducing cost. A new gas quenching method to minimize distortion of Ferrium C64 gear steel was developed by DANTE Solutions as part of an effort with the US Army's Aviation Development Directorate (ADD). This method utilizes a new state-of-the-art gas quench chamber to control the
(These definitions were prepared by the Joint Committee on Definitions of Terms Relating to Heat Treatment appointed by the American Society for Testing and Materials, The American Society for Metals, the American Foundrymen's Association, and the SAE.) This SAE revision emphasizes the terms used in heat treating ferrous alloys, but also includes for reference some non-ferrous definitions at the end of the document. This glossary is not intended to be a specification, and it should not be interpreted as such. Since this is intended to be strictly a set of definitions, temperatures have been omitted purposely.
ABSTRACT The ability to construct a multifunctional material that provides electromagnetic (EM) hardening on an aircraft structure integral to the material form has been demonstrated. The material's key attribute is the integration of a high level of EM shielding directly into a structural fiber-reinforced graphite composite in a manner that has minimal to no impact on the mechanical characteristics of the host composite. The material form has demonstrated the EM shielding equivalency of an aluminum electronics enclosure structure on a composite alternative for 25% of the weight without impacting structural characteristics. This material form provides a lightweight alternative to traditional means of providing aircraft EM protection from existing and emerging threats, such as high-power microwaves (HPMs) and EM pulse (EMP)/high-altitude EMP (HEMP), without incurring parasitic weight penalties. Its multifunctionality provides a weight-efficient means to address EM shielding in a
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