航空学报 > 2022, Vol. 43 Issue (1): 124931-124931   doi: 10.7527/S1000-6893.2020.24931

基于试验分岔分析的翼身融合飞行器纵向稳定性

付军泉1, 史志伟1, 耿玺1, 朱佳晨1, 王力爽1, 吴大卫2, 潘立军2   

  1. 1. 南京航空航天大学 航空学院, 南京 210016;
    2. 中国商飞上海飞机设计研究院, 上海 201210
  • 收稿日期:2020-10-30 修回日期:2020-12-15 出版日期:2022-01-15 发布日期:2020-12-14
  • 通讯作者: 史志伟 E-mail:szwam@nuaa.edu.cn
  • 基金资助:
    国家自然科学基金(12072155);江苏高校优势学科建设工程资助项目;非定常空气动力学与流动控制工信部重点实验室

Longitudinal stability of blended-wing-body aircraft based on experimental bifurcation analysis

FU Junquan1, SHI Zhiwei1, GENG Xi1, ZHU Jiachen1, WANG Lishuang1, WU Dawei2, PAN Lijun2   

  1. 1. College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
    2. COMAC Shanghai Aircraft Design and Research Institute, Shanghai 201210, China
  • Received:2020-10-30 Revised:2020-12-15 Online:2022-01-15 Published:2020-12-14
  • Supported by:
    National Natural Science Foundation of China (12072155); Project Funded by the Priority Academic Program Development of Jiangsu Higher Education Institutions; Key Laboratory of Unsteady Aerodynamics and Flow Control, Ministry of Industry and Information Technology

摘要: 针对翼身融合布局飞行器的纵向稳定性问题,基于分支和突变理论,求解迎角随升降舵变化的平衡分岔图,并对平衡分支的稳定性和突变点进行了分析。结合风洞虚拟飞行试验技术,发展了试验分岔分析方法,并设计了基于非线性动态逆的伪线性控制器,由此获得并分析了开环试验和闭环试验平衡分岔图。对比分析表明,理论分岔分析与开环试验分岔分析在小迎角范围结果基本一致,验证了试验分岔分析方法的可行性和准确性;翼身融合飞行器产生纵向失稳的主要原因是机翼表面流动分离,从而导致C发生突变引起的;闭环试验分岔分析实现了翼身融合飞行器非线性全局稳定性控制,通过纵向非线性控制器,可以将不稳定平衡分支改造成稳定的平衡分支。

关键词: 翼身融合(BWB), 纵向稳定性, 试验分岔分析, 虚拟飞行试验, 非线性动态逆

Abstract: Bifurcation analysis and the catastrophe theory are used to study the longitudinal stability of Blended-Wing-Body (BWB) aircraft. Equilibrium branches of the angle of attack with the elevator are obtained, and stability of the branches and the catastrophe points analyzed. Then bifurcation analysis is introduced into the virtual flight tests to physically track the equilibrium branches, enabling the experimental bifurcation analysis research in the wind tunnel. A pseudo-linear controller based on the nonlinear dynamic inverse is designed, with the open-loop and closed-loop experimental bifurcation diagrams obtained and analyzed. The comparative analysis shows that the theoretical bifurcation analysis and the open-loop experimental bifurcation analysis are basically consistent in the range of small angles of attack, verifying the feasibility and accuracy of the experimental bifurcation analysis method. The longitudinal instability of the BWB aircraft is mainly caused by the sudden changes of C. The closed-loop experimental bifurcation analysis realizes the nonlinear global stability control, transforming the unstable equilibrium branch into a stable one through the longitudinal nonlinear controller.

Key words: Blended-Wing-Body (BWB), longitudinal stability, experimental bifurcation analysis, virtual flight tests, nonlinear dynamic inversion

中图分类号: