基于PRSEUS结构的翼身融合布局后机身结构优化设计

Optimization Design of Blended-wing-body Layout Rear Fuselage Based on PRSEUS Structure

针对翼身融合布局民机的非圆形截面机身结构承载特征,美国波音公司和美国国家航空航天局(NASA)联合提出了拉挤杆缝合高效一体化结构(PRSEUS),以提高翼身融合布局飞机机身结构的承载效率及稳定性性能。为了深入研究翼身融合布局后机身结构设计及PRSEUS结构在后机身上的应用,本文建立了基于PRSEUS结构的翼身融合布局后机身结构高保真度数值分析模型。筛选出了针对翼身融合布局后机身的5种典型载荷工况作为评估后机身结构强度和刚度的输入条件。借鉴结构区域划分技术,开展了基于PRSEUS结构的翼身融合布局后机身结构优化方法研究,完成了基于分块的PRSEUS结构后机身结构优化设计,保证了后机身结构强度和刚度性能,并进一步减轻了结构重量。

Boeing and NASA jointly proposed PRSEUS structure to improve the carrying efficiency and stability of the aircraft fuselage structure based on the non-circular section of the wing-body fusion layout. In order to deeply study the airframe structure design and the application of PRSEUS structure on the rear fuselage, a high-fidelity numerical analysis model of airframe structure based on PRSEUS structure is established. Five typical load conditions are selected for the fuselage after the wing-body fusion layout, among which four are critical load conditions, which are used as input conditions to evaluate the structural strength and stiffness of the fuselage. By referring to the structural area division technology, the optimization method of the rear fuselage structure based on PRSEUS wing-body fusion layout is studied, and the optimization design of the rear fuselage structure based on PRSEUS block is completed,which ensures the strength and stiffness of the rear fuselage structure and further reduces the weight of the structure.