摘要
为解决现行飞机起落架缓冲器设计不考虑机体柔性存在的问题,以大柔性飞机支柱型起落架油气式缓冲器为例,采用三质量块飞机着陆模型和功量预估分配法选择缓冲器参数,并对其进行着陆响应动力学分析。研究结果表明,机体一阶模态频率和起落架与机体连接点位置是影响机体储存着陆功量的两个主要因素:机体一阶模态频率小于2 H z时,机体储存的着陆功量预估公式计算误差小于5%;机体储存能量的耗散效率较低。
For settling problems in aircraft landing gear shock absorber ctestgn witnout considering the fuselage flexibility, parameters of the shock absorber are calculated by using a three-mass equivalent aircraft system and a landing energy distribution prediction method. Landing dynamic simulations are evaluated for a flexible airplane with the conventional type of oleo-pneumatic main landing gear. Research results show that two important factors of the energy absorbed by the fuselage are the first modal frequency of the fuselage and the joint point of the landing gear and the fuselage. The calculation error of the formula to predict energy absorbed by the fuselage is smaller than 5 % when the frequency is below 2 Hz, and the fuselage vibration energy dissipating efficiency is comparatively low.
出处
《南京航空航天大学学报》
EI
CAS
CSCD
北大核心
2006年第3期356-360,共5页
Journal of Nanjing University of Aeronautics & Astronautics
基金
国家高技术研究发展计划(863-705)资助项目
关键词
航空器结构设计
起落架
参数设计
着陆响应
大柔性飞机
能量耗散
aircraft structure design
landing gear
parameter design
landing response
flexible airplane
energy dissipating
