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文中充分利用复合材料的可设计性,设计出满足结构刚度强度以及稳定性等性能指标要求且使结构重量更轻的飞行器结构。本文的重点是将梁单元结构的位置参数引入优化设计技术中,较传统的元件参数优化技术更具工程实用性,大大提高了优化工作效率,并由此而产生两个优化方案(区别在于梁元是否偏置)。通过两个优化方案的论证,偏置方案算例较好的数值优化结果充分证明了梁元偏置的有效性和工程设计的实用性,表明了在优化设计工作中对梁元进行偏置设计的优越性和必要性。论文工作对复合材料结构优化设计具有一定的工程参考价值。
In this paper, the design of composite materials is fully used to design aircraft structures that meet the performance requirements of structural stiffness strength and stability and make the structure lighter. The key point of this paper is to introduce the position parameters of beam element structure into the optimization design technology. Compared with the traditional component parameter optimization technology, it is more practical and has greatly improved the optimization work efficiency, resulting in two optimization schemes (the difference is that the beam Yuan is offset). Through the demonstration of two optimization schemes, the better numerical optimization of the example of bias scheme fully proves the effectiveness of the beam element biasing and the practicality of the engineering design, which shows that the bias design of the beam element in the optimization design work The superiority and necessity. Papers work on the optimal design of composite structures has some engineering reference value.