摘要
针对某战斗类飞机的主起落架自身结构和其受力特点,确定了测量其载荷时应变片粘贴位置及其组桥方式。根据航向载荷作用点的不同并考虑压缩行程的影响,提出了压缩行程影响因子,并把其引入标定方程,同时运用多元回归及优化方法建立标定载荷方程,由此得出实测载荷谱,为起落架的定寿延寿及可靠性设计提供了重要依据。
According to the mechanical structure and the load characteristics of a fighter airplane main undercarriage, the arrangement of the measuring strain gages and the type of the strain gage bridges were decided. Considering the variation of application of the loads and the influence of the landing gear compression stroke, an influence factor of landing gear compression stroke was defined and introduced in the calibration equation as a parameter. The equation between the load imput and the strain gage output was established on a test bench by aid of the multi-variable regression and optimization method. The measured load spectrum of the main undercarriage was derived by means of the calibration equation, providing an important reference for estimating and enhancing the fatigue life and conducting the reliability-based design.
出处
《吉林大学学报（工学版）》
EI
CAS
CSCD
北大核心
2006年第6期1025-1028,共4页
Journal of Jilin University:Engineering and Technology Edition
基金
国家自然科学基金资助项目(50135010)
关键词
工程力学
飞机
主起落架
应变片
载荷谱
标定方程
engineering mechanics
airplane
main undercarriage
strain gage
load spectrum
calibration equation
