Accession Number:

ADA622088

Title:

Topology Optimization of an Aircraft Wing

Descriptive Note:

Master's thesis

Corporate Author:

AIR FORCE INSTITUTE OF TECHNOLOGY WRIGHT-PATTERSON AFB OH GRADUATE SCHOOL OF ENGINEERING AND MANAGEMENT

Personal Author(s):

• Walker, David L.

Report Date:

2015-06-11

Pagination or Media Count:

148.0

Abstract:

A Topology Optimization TO was conducted on an aircraft wing in order to mathematically determine an ideal structural case for future aircraft. TO generally involves iteratively reducing individual elemental density until the desired mass or volume constraint is met. Two di erent TO styles where approached a global three-dimensional concept and a more traditional two-dimensional rib and spar optimization which more closely mimics the baseline model. All optimizations were compared against a baseline wing for von-Mises stress, displacement, and buckling. The objective of this research was to develop a design procedure maintaining the baseline structural integrity of the wing while reducing weight. As with many TO designs, Additive Manufacturing AM was studied as a means to produce the wing concerning both the feasibility of manufacture and as a logistical advantage compared to traditional means. Additionally, a fuel tank was integrated into the wing structure as a proof-of-concept for the potential benefits of AM. Finally, a 3D lattice structure was utilized as a conceptual method for improving current design methodology.

Descriptors:

• *AERODYNAMIC LOADING
• *AIRFRAMES
• *SPARS
• *STRUCTURAL INTEGRITY
• *STRUTS
• *TOPOLOGY
• AIR FORCE RESEARCH
• AIRCRAFT DESIGN
• BASE LINES
• BUCKLING
• FINITE ELEMENT ANALYSIS
• FUEL TANKS
• MANUFACTURING
• OPTIMIZATION
• SURVIVABILITY
• THESES
• THREE DIMENSIONAL
• TWO DIMENSIONAL
• WEIGHT REDUCTION

Subject Categories:

• Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE