Integrated structural-aerodynamic design optimizationThis paper focuses on the processes of simultaneous aerodynamic and structural wing design as a prototype for design integration, with emphasis on the major difficulty associated with multidisciplinary design optimization processes, their enormous computational costs. Methods are presented for reducing this computational burden through the development of efficient methods for cross-sensitivity calculations and the implementation of approximate optimization procedures. Utilizing a modular sensitivity analysis approach, it is shown that the sensitivities can be computed without the expensive calculation of the derivatives of the aerodynamic influence coefficient matrix, and the derivatives of the structural flexibility matrix. The same process is used to efficiently evaluate the sensitivities of the wing divergence constraint, which should be particularly useful, not only in problems of complete integrated aircraft design, but also in aeroelastic tailoring applications.
Document ID
19890026313
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Haftka, R. T. (Virginia Polytechnic Inst. and State Univ. Blacksburg, VA, United States)
Kao, P. J. (Virginia Polytechnic Inst. and State Univ. Blacksburg, VA, United States)
Grossman, B. (Virginia Polytechnic Inst. and State Univ. Blacksburg, VA, United States)
Polen, D. (Virginia Polytechnic Institute and State University Blacksburg, United States)
Sobieszczanski-Sobieski, J. (NASA Langley Research Center Hampton, VA, United States)