STRESS ANALYSIS OF COMPOSITE AIRCRAFT WING STRUCTURES UNDER DIFFERENT OPERATING CONDITIONS
Authors
Reyes, Orson Isaac A.
Subjects
Aircraft wings
Aeroelastic behavior
Fluttering behavior
Supersonics
Hypersonics
Airfoil velocity
Material composition
Coupling effects
Failure analysis
Safety
Manufacturability
Feasibility
Aluminum airfoils
Composite airfoils
Structural dynamics
Pressure contours
Drag coefficients
Optimization
Aeroelastic behavior
Fluttering behavior
Supersonics
Hypersonics
Airfoil velocity
Material composition
Coupling effects
Failure analysis
Safety
Manufacturability
Feasibility
Aluminum airfoils
Composite airfoils
Structural dynamics
Pressure contours
Drag coefficients
Optimization
Advisors
Kwon, Young W.
Date of Issue
2024-12
Date
Publisher
Monterey, CA; Naval Postgraduate School
Language
Abstract
The purpose of this study is to explore the structural behavior of a composite aircraft wing under operational conditions using a one-way fluid-structure interaction simulation. This research focuses on the responses of stresses and strains during takeoff, landing, and steady flight conditions. The wing structure, modeled using a carbon-fiber composite, was tested under various angles of attack and air speeds. Testing consisted of computational fluid dynamics solving for pressure mapping induced by the fluid to impose onto the structural solver. Results from these simulation runs indicate that as angles of attack increase, particularly during takeoff, the stress experienced by the wing-body also increases while staying within material limits. The study emphasizes the value of composite materials in aviation applications and efficient computational methods for wing design optimization.
Type
Thesis
Description
Series/Report No
Department
Mechanical and Aerospace Engineering (MAE)
Organization
Identifiers
NPS Report Number
Sponsors
Funder
Format
Citation
Distribution Statement
Distribution Statement A. 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.