Trim Optimizations of an Adaptive Tailless Aircraft with Composite Wing

摘要：

This paper investigates aeroelastic tailoring and optimal trailing edge control surface deflection to minimize induced drag for a HALE UAV flying wing configuration. The analysis process is conducted on the Finite Element(FE) model of a composite slender wing. Genetic Algorithm(GA) is employed to aeroelastically tailor the wing by setting the composite ply orientation. The study examined conformal and traditional flaps and explored two optimization formulations to minimize drag. The impacts of the conformal control surface are recognized as required deflection saving which can be translated to drag reduction. The results also show that the control demands for the optimal trim can be further reduced if the wing is properly tailored.

关键词： trim optimization adaptive wing active aeroelastic wing aeroelastic tailoring induced drag

作者: Jiang Xie Zhichun Yang Shijun Guo

作者单位: Northwestern Polytechnical University, Xian, 710072, P.R.China Cranfield University, Bedfordshire, MK43 OAL, UK

会议类型: 国际会议

会议名称: 2011 International Conference on Advanced Material Research(ICAMR 2011)(2011年先进材料研究国际会议)

会议地点: 重庆

会议语种:英文

页码: 334-338

在线出版日期: 2011-01-21（万方平台首次上网日期，不代表论文的发表时间）