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原文传递 Aeroelastic Airworthiness Assesment of the Adaptive Compliant Trailing Edge Flaps.

题名：	Aeroelastic Airworthiness Assesment of the Adaptive Compliant Trailing Edge Flaps.
作者：	Herrera, C. Y.; Spivey, N. D.; Lung, S.; Ervin, G.; Flick, P.
关键词：	Aircraft reliability, Trailing edge flaps, Aeroelasticity, Flapping, Flutter, Flight tests, Ground tests, Vibration tests, Flutter analysis, Finite element method, Control surfaces, Project management, Research and development
摘要：	The Adaptive Compliant Trailing Edge (ACTE) demonstrator is a joint task under the National Aeronautics and Space Administration Environmentally Responsible Aviation Project in partnership with the Air Force Research Laboratory and FlexSys, Inc. (Ann Arbor, Michigan). The project goal is to develop advanced technologies that enable environmentally friendly aircraft, such as adaptive compliant technologies. The ACTE demonstrator flight-test program encompassed replacing the Fowler flaps on the SubsoniC Aircraft Testbed, a modified Gulfstream III (Gulfstream Aerospace, Savannah, Georgia) aircraft, with control surfaces developed by FlexSys. The control surfaces developed by FlexSys are a pair of uniquely-designed unconventional flaps to be used as lifting surfaces during flight-testing to validate their structural effectiveness. The unconventional flaps required a multidisciplinary airworthiness assessment to prove they could withstand the prescribed flight envelope. Several challenges were posed due to the large deflections experienced by the structure, requiring non-linear analysis methods. The aeroelastic assessment necessitated both conventional and extensive testing and analysis methods. A series of ground vibration tests (GVTs) were conducted to provide modal characteristics to validate and update finite element models (FEMs) used for the flutter analyses for a subset of the various flight configurations. Numerous FEMs were developed using data from FlexSys and the ground tests. The flap FEMs were then attached to the aircraft model to generate a combined FEM that could be analyzed for aeroelastic instabilities. The aeroelastic analysis results showed the combined system of aircraft and flaps were predicted to have the required flutter margin to successfully demonstrate the adaptive compliant technology. This paper documents the details of the aeroelastic airworthiness assessment described, including the ground testing and analyses, and subsequent flight-testing performed on the unconventional ACTE flaps.
总页数：	Herrera, C. Y.; Spivey, N. D.; Lung, S.; Ervin, G.; Flick, P.
报告类型：	科技报告