Page 127 - 《爆炸与冲击》2026年第2期

第 46 卷 第 2 期 爆 炸 与 冲 击 Vol. 46, No. 2
2026 年 2 月 EXPLOSION AND SHOCK WAVES Feb., 2026

DOI：10.11883/bzycj-2024-0520

不同垂向速度下翼身融合民机机体的坠撞响应 *

白春玉 ，程斯午未 ，解 江 ，程升杰 ，李思璇 2
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（1. 中国飞机强度研究所，陕西 西安 710065；
2. 中国民航大学安全科学与工程学院，天津 300300；
3. 中国民航大学科技创新研究院，天津 300300）
摘要： 为了研究翼身融合（blended wing body, BWB）新构型民机的结构坠撞响应，以美国国家航空航天局提出的
拉挤杆缝合一体化（pultruded rod stitched efficient unitized structure, PRSEUS）结构为基础，用临界机动载荷（2.5g 过载和
−1.0g 过载）和客舱增压载荷（2 倍客舱增压载荷）共 3 种典型载荷工况作为评估 BWB 结构强度、刚度的输入条件，建
立了一款 450 座级的 BWB 民机结构模型。对垂向 7.92～9.14 m/s 的坠撞工况进行了数值模拟，重点分析了客舱空间保
持情况、客舱地板的加速度响应以及主要承力结构的冲击特性。结果表明：在不同冲击速度下 BWB 机身客舱区域均
基本保持完整，主要破坏发生在客舱地板以下区域，可生存空间得到保持；翼身融合构型民机在坠撞时产生的加速度
响应分布呈现由中央过道向机体侧降低的趋势，且中央过道处的加速度峰值较高；结构吸能方面，隔框是最主要的吸
能结构，其次是机身肋板，而货舱立柱未很好的压溃吸能。
关键词： 翼身融合；坠撞响应；PRSEUS 结构；乘员伤害；适坠性
中图分类号： O347.3; V223 国标学科代码： 13015 文献标志码： A

Crash responses of a blended-wing-body civil aircraft
at different vertical velocities

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BAI Chunyu , CHENG Siwuwei , XIE Jiang , CHENG Shengjie , LI Sixuan 2
（1. Aircraft Strength Research Institute of China, Xi’an 710065, Shaanxi, China;
2. College of Safety Science and Engineering, Civil Aviation University of China, Tianjin 300300, China;
3. Science and Technology Innovation Research Institute, Civil Aviation University of China, Tianjin 300300, China）

Abstract: Significant structural and layout disparities exist between the blended wing body (BWB) civil aircraft and
conventional cylindrical fuselage metal aircraft. These differences render the impact resistance characteristics of the non-
circular fuselage structure and the injury mechanisms for occupants unclear. To address this, a 460-seat BWB aircraft model
was developed based on the pultruded rod stitched efficient unitized structure (PRSEUS) proposed by the National Aeronautics
and Space Administration (NASA). The aircraft features a wingspan of 80 meters, a range of approximately 16,000 km, a
cruising Mach number of 0.85, and a cruising altitude of 11 000 m. Three typical loading conditions were employed to evaluate
the strength and stiffness of the BWB structure: critical maneuvering loads (2.5g positive overload and −1.0g negative
overload) and cabin pressurization loads (double the cabin pressurization load). Through iterative structural design
optimization, the model was confirmed to meet these typical loading requirements while demonstrating sufficient safety
margins. The model incorporated all major structural components of the BWB configuration, including skin, frames, stringers,
cargo floor, cabin floor, support columns, and fuselage ribs. In the finite element modeling process, elements with minimal
influence on the crash response were reasonably simplified to reduce computational complexity. For instance, the outer wings

* 收稿日期： 2024-12-30；修回日期： 2025-06-24
基金项目： 国家重点研发计划（2022YFB4301000）
第一作者： 白春玉（1984－ ），男，硕士，高级工程师，baichunyu2006@163.com
通信作者： 解 江（1982－ ），男，博士，教授，xiejiang5@126.com

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