TY - GEN
T1 - Optimum distributed wing shaping and control loads for highly flexible mission-adaptive aircraft
AU - Hammerton, Jared R.
AU - Su, Weihua
AU - Zhu, Guoming
AU - Swei, Sean Shan Min
N1 - Funding Information:
The research is supported by the Convergent Aeronautics Solutions (CAS) project of NASA ARMD. The first author also acknowledges the support of the Alabama Space Grant Consortium (ASGC) Fellowship. The views expressed in this paper are those of the authors and do not reflect the official policy or position of NASA or the U.S. Government.
Publisher Copyright:
© 2017 International Forum on Aeroelasticity and Structural Dynamics (IFASD). All Rights Reserved.
PY - 2017
Y1 - 2017
N2 - This paper explores the optimum wing bending and torsion deformations of a highly flexible mission-adaptive aircraft. With the goal of improving flight performance across the entire flight regime, a modal based optimization subject to trim and other constraints is employed. Distributed control loads are formulated and used to determine the optimization wing geometry as well. The optimization is then performed to achieve the best flight performance which is defined as minimum drag. This study explores the optimum wing geometry for steady level flight at a single velocity, a range of velocities, and a coordinated turn. Additionally, the study also explores the optimum wing shapes with the consideration of the trade-off between flight efficiency and ride quality, where a multi-objective optimization is performed, targeting for minimizing drag to improve performance and reducing the wing bending load of a gust to improve the ride quality.
AB - This paper explores the optimum wing bending and torsion deformations of a highly flexible mission-adaptive aircraft. With the goal of improving flight performance across the entire flight regime, a modal based optimization subject to trim and other constraints is employed. Distributed control loads are formulated and used to determine the optimization wing geometry as well. The optimization is then performed to achieve the best flight performance which is defined as minimum drag. This study explores the optimum wing geometry for steady level flight at a single velocity, a range of velocities, and a coordinated turn. Additionally, the study also explores the optimum wing shapes with the consideration of the trade-off between flight efficiency and ride quality, where a multi-objective optimization is performed, targeting for minimizing drag to improve performance and reducing the wing bending load of a gust to improve the ride quality.
KW - Distributed control
KW - Flexible aircraft
KW - Optimum wing geometry
KW - Wing shaping control
UR - http://www.scopus.com/inward/record.url?scp=85048637159&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:85048637159
T3 - 17th International Forum on Aeroelasticity and Structural Dynamics, IFASD 2017
BT - 17th International Forum on Aeroelasticity and Structural Dynamics, IFASD 2017
T2 - 17th International Forum on Aeroelasticity and Structural Dynamics, IFASD 2017
Y2 - 25 June 2017 through 28 June 2017
ER -