期刊
MACHINES
卷 9, 期 12, 页码 -出版社
MDPI
DOI: 10.3390/machines9120307
关键词
composite laminates; delamination; design allowable; damage distribution
资金
- National Key Research and Development Program of China [2018YFF0216004]
This paper proposes a novel algorithm for determining design allowables of composite laminates based on initial damages, providing more accurate design allowables for different aircraft structures. Compared to the single-point method, the design allowables calculated based on initial damages can be increased by at least 5% to 20%, significantly improving the economic benefits of aircraft structures and supporting damage tolerance design of composite structures.
With the increasing demands for detailed design of composite aircraft structures, the method of covering all damages with low design allowables cannot meet the current requirements for aircraft structure design. Herein, this paper proposes a novel algorithm for design allowable determination of composite laminates by combining the damage distribution with damage factor model of design allowable, so as to provide different structures with more accurate design allowables based on their initial damages. For the composite laminates with initial delaminations, a model describing the effect of delamination size and depth position on the compression design allowable is developed and the compression design allowable of different aircraft structures are individually determined by employing abundant initial delamination statistics. Compared with the design allowable offered by the single-point method, the design allowable based on the initial damage can be increased by at least 5% to 20%, greatly improving the economic benefits of the aircraft structures and providing an important support for the damage tolerance design of the composite structures.
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