Design Optimization of Flexible Aircraft Wings Using Tow-steered Composites.
Degree: PhD, Aerospace Engineering, 2018, University of Michigan
In the last 30 years since their introduction into aerospace applications, composites have become increasingly used, making up as much as 50% of modern aircraft by weight.
Considering this fact, it is surprising that most aircraft today are only scratching the surface of the true potential of composite technology with traditional uniaxial fibers.
With the introduction of automatic fiber placing machines, the fiber direction in laminae is now allowed to be steered spatially throughout each layer.
This process is known as composite tow steering and has been shown to have improved performance over its uniaxial fiber counterpart with no additional weight penalty.
With modern aircraft moving toward larger and more flexible wing designs, it is reasonable to expect that a tow-steered composite wing structure can be tailored to outperform its unsteered counterpart.
However, given the highly coupled nature of the aerodynamics and structural response of the problem it is not obvious nor intuitive to find the composite fiber pattern that would yield an optimal result.
High-fidelity aerostructural solvers have been proven effective for accurately capturing the trade-offs between relevant design disciplines for such aircraft.
Such solvers allow for the performance of tow-steered wing structures to be analyzed in great detail.
By complementing these solvers with gradient-based numerical optimization, high dimensional design spaces can be explored relatively efficiently.
Such methods make it possible to quantify the maximum benefits offered by tow-steered wing structures.
In this thesis, a number of aerostructural optimizations are performed to compare the performance of aluminum, conventional composite and tow-steered composite wing designs.
For these studies, a set of benchmark aeroelastic aircraft models are developed based on the NASA Common Research Model.
A design parameterization scheme, constitutive model, and relevant manufacturing constraints are then developed for tow-steered structures.
A fuel burn minimization is then performed for a tow-steered and conventional composite wing design.
When applied to a Boeing-777-type aircraft wing, tow steering is found to offer improvements of up to 2.4% in fuel savings and 24% in wing weight under the limited set of design constraints, relative to the optimized conventional composite design.
This improvement was found to be due to a combination of improved passive aeroelastic tailoring and local strength tailoring in high-stressed regions in the tow-steered structure.
For a higher aspect ratio wing design improvements of up to 1.5% and 14% in fuel savings and wing weight are found.
Finally, the trade-off between structural weight and fuel burn performance is explored through a Pareto front study.
This study compares the performance of an aluminum, conventional and tow-steered composite wing.
In this study, it is found that when wing planform is free to vary, tow-steering offers improvements of up to 1.5% in fuel savings for a fuel-burn-optimized design and 1.6% in total…
Advisors/Committee Members: Martins, Joaquim R R A (committee member), Saitou, Kazuhiro (committee member), Cesnik, Carlos E (committee member), Sundararaghavan, Veera (committee member).
Subjects/Keywords: Multi-disciplinary design optimization; Tow-steered composites; Aeroelastic wing design; Aerospace Engineering; Engineering
…flexible-wing design tow-steered
composites provide a number of theoretical advantages to their… …conventional (left) and tow-steered (right) layups . . . 5
Example of divergent… …Result of structural optimization of uCRM-9: unsteered (left) vs. tow-steered
Comparison of optimal tow-steered (left) vs. conventional (right)… …paths for tow-steered wing skins . . . . . . . . . . . . . . . . . . . . . . . . . 124…
to Zotero / EndNote / Reference
APA (6th Edition):
Brooks, T. (2018). Design Optimization of Flexible Aircraft Wings Using Tow-steered Composites. (Doctoral Dissertation). University of Michigan. Retrieved from http://hdl.handle.net/2027.42/145830
Chicago Manual of Style (16th Edition):
Brooks, Timothy. “Design Optimization of Flexible Aircraft Wings Using Tow-steered Composites.” 2018. Doctoral Dissertation, University of Michigan. Accessed April 21, 2021.
MLA Handbook (7th Edition):
Brooks, Timothy. “Design Optimization of Flexible Aircraft Wings Using Tow-steered Composites.” 2018. Web. 21 Apr 2021.
Brooks T. Design Optimization of Flexible Aircraft Wings Using Tow-steered Composites. [Internet] [Doctoral dissertation]. University of Michigan; 2018. [cited 2021 Apr 21].
Available from: http://hdl.handle.net/2027.42/145830.
Council of Science Editors:
Brooks T. Design Optimization of Flexible Aircraft Wings Using Tow-steered Composites. [Doctoral Dissertation]. University of Michigan; 2018. Available from: http://hdl.handle.net/2027.42/145830