海军航空大学学报2018，Vol.33Issue(2)：217-224,8.DOI:10.7682/j.issn.1673-1522.2018.02.007
直升机滑跑地面共振特性研究
Research on Characteristics of Helicopter Running Ground Resonance
魏钢 1刘湘一 2宋山松 2王立国3
作者信息
- 1. 海军驻汉中地区航空军事代表室,陕西汉中723000
- 2. 海军航空大学,山东烟台264001
- 3. 92955部队,辽宁葫芦岛125000
- 折叠
摘要
Abstract
Bases on helicopter trim analysis at steady running, landing gear loadings, rotor pitch sets and flap responses were obtained. Conjoin with static and dynamic test data of landing gear shock absorber and tire, the variations of fuselage lateral and longitudinal mode characteristics with running speed were resolved from free vibration theory. Kinematic cou-pling model of hydraulic damper on rotor blade was applied to calculate the cyclic response of blade lead-lag and the damper axial velocity, then equivalent damping of the damper were predicted under"dual frequency"conditions. After that, the influences of different factors on helicopter running ground resonance were analyzed from rotor/fuselage coupled dynamic model. Results showed that the natural frequency of fuselage lateral mode had a decrement due to running speed. Set collective pitch 2-degree, helicopter ground resonance would happen within the range of 22.8 to 31km/h if large distur-bance occurs at steady running. As the collective pitch of rotor increased, helicopter ground resonance occured at a lower running speed. If the collective pitch of rotor kept low, and the disturbance of damper was small as well, helicopter ground resonance could be avoided when steady running.关键词
直升机/滑跑/地面共振/液压阻尼器/起落架Key words
helicopter/running/ground resonance/hydraulic damper/landing gear分类
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魏钢,刘湘一,宋山松,王立国..直升机滑跑地面共振特性研究[J].海军航空大学学报,2018,33(2):217-224,8.
