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Load Case and Constraint Downselection for Structural Optimization
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AI
DOI：10.2514/1.C037564.png)
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Abstract
En 中文
A framework for implementing an envelope-based approach for aircraft structural optimization load case and constraint downselection is proposed. The approach maps structural constraints into a reduced load space to form an envelope. The envelope describes the region in the reduced load space within which the structure can work without failure. The reduced load space is defined as a set of orthonormal load cases that can be used in linear combination to approximate a larger number of complex loads. By identifying the active constraints that form the envelope for combinations of the orthonormal load cases, the critical load cases and constraints can be numerically identified. An industrial case study considering wing cover panels is used to demonstrate the approach. For the examined problem, considering a number of wing cover stiffened panel structural features within a representative airframe industrial design, a reduced number of load cases and structural constraints were identified. The load cases were reduced, retaining 33-92% of the original set, while the structural constraints were reduced from 13 to 3-8 per stiffened panel.
Keywords:
Structural Design and Development
Structural Optimization
Structural Load
Wing Loading
Journal
IF:
2.1
Papers:
226
Citations:
8.8K