Publication:
Analysis of in-flight structural failures of P-3C wing leading edge segments

Loading...
Thumbnail Image
Authors
Lott, Dennis A.
Subjects
Aeroelasticity
Span-load analysis
Panel methods
Finite-element analysis
Stress levels
Stress concentrations
Structural failure
Advisors
Schmidt, Louis V.
Date of Issue
1992-06
Date
June 1992
Publisher
Monterey, California. Naval Postgraduate School
Language
en_US
Abstract
A quantitative analysis was carried out to determine the stresses present in the leading-edge segment of a P-3C aircraft operating within and outside the normal operating envelope of the aircraft. The purpose of the analysis was to ascertain whether a specific weakness may exist in the leading-edge structure which might endanger future operating flight crews. A three-step process consisting of a static aeroelastic span-load analysis, an inviscid two-dimensional panel method, and finite-element analysis was employed in the course of the evaluation. Lift-coefficient distributions from the wing span-load analyses were used in the two-dimensional panel method to determine the pressure distribution around the leading edge, which was then used as input to the finite­ element analysis. Additionally, static aeroelastic-derived wing-twist effects were included in the structural model. The results of the analysis suggest that the leading edge segment studied may experience stress levels sufficient to cause failure within the normal operating envelope.
Type
Thesis
Description
Series/Report No
Department
Aeronautics and Astronautics
Organization
Naval Postgraduate School (U.S.)
Identifiers
NPS Report Number
Sponsors
Funder
Format
109 p.
Citation
Distribution Statement
Approved for public release; distribution is unlimited.
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.
Collections