Construction of flight measurement model for folding wing structural load of aircraft

被引：0

作者：

Li, Jun ^{[1
]}

Fan, Huafei ^{[1
]}

He, Fadong ^{[1
]}

Li, Zhirui ^{[1
]}

Li, Wenlong ^{[1
]}

机构：

[1] Chinese Flight Test Establishment, Xi’an,710089, China

来源：

Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2024年 / 45卷 / 23期

关键词：

Strain bridge for load measurement of aircraft folding wing structure will have serious nonlinear response problem in the load calibration ground test. Based on the structural force transmission characteristics and structural load measurement mechanism in the folding region; a piece-wise multivariate linear model is established; with the bending moment with respect to the folding boundary plane being taken as the state variable and the bending moment due to the gravity of the folding section as the boundary load. The method for determining flight measurement load by the piecewise model is presented. The flight test of load measurement of folding wing of a certain type of aircraft is conducted for verification. The results show that the load obtained by the piecewise model is closer to the actual load; and can significantly reduce the influence of the nonlinear response of the strain bridge on load measurement in the folding region and improve the accuracy of the load measurement. At the maximum positive load factor of the symmet⁃ ric pull-up maneuver; the shear and bending moment obtained by the downward load model are 8. 48% and 11. 13% smaller than that obtained by the piecewise model; respectively. At the maximum negative load factor of the symmet⁃ ric push-down maneuver; the shear and bending moment obtained by the upward load model are 14. 87% and 12. 83% larger than that obtained by the piecewise model; respectively. The research provides a theoretical basis and practical method for solving the nonlinear response problem of strain bridge for load measurement of the wing structure. © 2024 Chinese Society of Astronautics. All rights reserved;

D O I：

10.7527/S1000-6893.2024.30370

中图分类号：

学科分类号：

摘要：

引用

共 50 条

[11] FOLDING-WING AIRCRAFT DESIGNED IN BRITAIN
不详
AVIATION WEEK & SPACE TECHNOLOGY, 1984, 121 (11): : 134 - 134
[12] Aircraft health and usage monitoring system for in-flight strain measurement of a wing structure
Kim, Jin-Hyuk
Park, Yurim
Kim, Yoon-Young
Shrestha, Pratik
Kim, Chun-Gon
SMART MATERIALS AND STRUCTURES, 2015, 24 (10)
[13] Flight mechanics of a tailless articulated wing aircraft
Paranjape, Aditya A.
Chung, Soon-Jo
Selig, Michael S.
BIOINSPIRATION & BIOMIMETICS, 2011, 6 (02)
[14] PIVOT-WING AIRCRAFT TO BE FLIGHT TESTED
不详
MACHINE DESIGN, 1978, 50 (09) : 4 - 4
[15] Development of Software for Fidelity Test of Flight Dynamic Model on Fixed Wing Aircraft
Baek, Seung-Jae
Kang, Mun-Hye
Choi, Seong-Hwan
Kim, Byoung Soo
Moon, Yong Ho
JOURNAL OF THE KOREAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 2020, 48 (08) : 631 - 640
[16] Trajectory optimization and control analysis of folding wing aircraft
Yang Bo
Zhu Yichuan
Wei Yanming
Fan Zichen
CHINESE SPACE SCIENCE AND TECHNOLOGY, 2020, 40 (03) : 64 - 75
[17] Dynamic modeling and stability control of folding wing aircraft
Song H.
Jin L.
Lixue Xuebao/Chinese Journal of Theoretical and Applied Mechanics, 2020, 52 (06): : 1548 - 1559
[18] Construction of safety-predicting load model on certain wing
Zhao Y.
Song J.
Tang N.
Zhao, Yan (zhaoyan1031@mail.nwpu.edu.cn), 1600, Chinese Society of Astronautics (41):
[19] Optimal trends in Manoeuvre Load Control at subsonic and supersonic flight points for tailless delta wing aircraft
Suresh, P. S.
Radhakrishnan, G.
Shankar, K.
AEROSPACE SCIENCE AND TECHNOLOGY, 2013, 24 (01) : 128 - 135
[20] Optimisation of energy harvesting for stiffened composite shells with application to the aircraft wing at structural flight frequency
Daraji, Ali H.
Hale, Jack M.
Ye, Jianqiao
THIN-WALLED STRUCTURES, 2021, 161 (161)

← 1 2 3 4 5 →