摘要
建立了半主动控制起落架缓冲动力学数学模型,模型中流量系数是油孔等效面积、流量或压差的函数,不再是固定值,而是变量。利用定油孔起落架的落震试验对该模型进行了校验。设计了两个简单控制律,第一个控制律按传统变油孔设计准则给定,第二个控制律按给定吸收功量时峰值载荷最小的准则设计。通过数字仿真对这两种控制律下的起落架和被动式起落架的缓冲性能进行比较。结果表明,半主动控制在提高起落架缓冲性方面有较大潜力。
A dynamic model of semi-active control shock absorber of landing gear is developed. In the model, a variable discharge coefficient is adopted instead of a constant one. The discharge coefficient is a function of the equivalent orifice area,flux or pressure difference. The model is verified by the drop tests of fixed orifice landing gear. Two simple control laws are proposed. One is designed according to the design rule of conventional variable orifice, and the other is designed to keep the peak load as small as possible while the same shock energy is absorbed. By the means of numerical simulation, the semi-active control landing gears under the two control laws are compared with the passive one. The results indicate that the semi-active control landing gear has great potential in improving performance of shock absorber of landing gears.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2006年第5期864-868,共5页
Acta Aeronautica et Astronautica Sinica
基金
航空基础科学基金(98B52023
04B52012)
关键词
航空器结构与设计
半主动控制
落震试验
数字仿真
起落架
缓冲器
aircraft ＇ s structure and design
semi-active control
drop test
numerical simulation
landing gear
shock absorber
