| 大柔性飞机起落架缓冲器参数设计 |
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| 引用本文： | 史友进,张曾锠.大柔性飞机起落架缓冲器参数设计[J].南京航空航天大学学报,2006,38(3):356-360. |
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| 作者姓名： | 史友进 张曾锠 |
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| 作者单位： | 1. 南京航空航天大学航空宇航学院,南京,210016;盐城工学院基础教学部,盐城,224003
2. 南京航空航天大学航空宇航学院,南京,210016 |
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| 基金项目： | 国家高技术研究发展计划(863计划) |
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| 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。
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| 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 |
| 文章编号： | 1005-2615(2006)03-0356-05 |
| 收稿时间： | 2005-09-07 |
| 修稿时间： | 2005-10-17 |
Parameter Design of Landing Gear Shock Absorber for Flexible Airplane |
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| Shi Youjin,Zhang Zhengchang.Parameter Design of Landing Gear Shock Absorber for Flexible Airplane[J].Journal of Nanjing University of Aeronautics & Astronautics,2006,38(3):356-360. |
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| Authors: | Shi Youjin Zhang Zhengchang |
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| Abstract: | For settling problems in aircraft landing gear shock absorber design without 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. |
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| Keywords: | aircraft structure design landing gear parameter design landing response flexible airplane energy dissipating |
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