The Role of Constraints in the MDO of a Cantilever and Strut-B raced Wing Transonic Commercial Transport Aircraft Multidisciplinary Analysis and Design (MAD) Center for Advanced Vehicles Department of Aerospace and Ocean Engineering, Virginia Polytechnic Institute and State University

Format:

Conference/Event

Author/Creator:

Ko, A., author.

Conference Name:

World Aviation Congress & Exposition (2000-10-10 : San Diego, California, United States)

Language:

English

Physical Description:

1 online resource

Place of Publication:

Warrendale, PA SAE International 2000

Summary:

This study examines the role of different design constraints applied to the multidisciplinary design optimization of a strut-braced wing (SBW) transonic passenger aircraft. Four different configurations are examined: the reference cantilever wing aircraft, a fuselage mounted engine SBW, a wing mounted engine SBW, and a wingtip mounted engine SBW. The mission profile was for 325-passengers, Mach 0.85 and a 7500 nautical mile range with a 500 nautical mile reserve.The sensitivity of the designs with respect to the individual design constraints was calculated using Lagrange multipliers. A design space visualization technique was also used to gain insight into the role of the different constraints in determining the design configuration. This design visualization technique uses a classic thumbprint' plot to represent the design space.As expected, all the designs are very sensitive to the range constraint. The designs are also sensitive to the field performance constraints. The design visualization revealed that the second segment climb gradient constraint was a limiting factor in all the designs. It was also found that the wing mounted engines SBW and tip mounted engines SBW designs are more constrained than the cantilever wing optimum and fuselage mounted engines SBW designs

Notes:

Vendor supplied data

Publisher Number:

2000-01-5609

Access Restriction:

Restricted for use by site license