| 倾转旋翼机直升机状态系统稳定性判断的一种方法 |
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| 引用本文： | 贾大伟,韩景龙.倾转旋翼机直升机状态系统稳定性判断的一种方法[J].直升机技术,2009(1). |
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| 作者姓名： | 贾大伟 韩景龙 |
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| 作者单位： | 1. 中国直升机设计研究所,景德镇,333001
2. 南京航空航天大学振动工程研究所,南京,210016 |
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| 摘 要： | 本文建立了倾转旋翼机直升机模式的非线性气弹分析模型,采用数值方法——纽马克法和牛顿—拉斐逊迭代法相结合的方法计算了直升机悬停状态系统对初始条件的响应,通过响应考察系统从初始时刻到任意时刻之间的响应过程,同时判断出系统的稳定性。
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| 关 键 词： | 倾转旋翼机 直升机模式 气动弹性 稳定性判断 |
A Method of Stability Evaluation of Tiltrotor in Helicopter Mode |
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| Authors: | JIA Dawei HAN Jinglong |
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| Institution: | 1.China Helicopter Research and Development Institute; Jingdezhen; 333001; 2.Vibration Engineering Research Institute; Nanjing University of Aeronautics and Astronautics; Nanjing; 210016); |
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| Abstract: | The nonlinear aeroelastic analysis model of tiltrotor in helicopter mode was founded in this paper,and nonlinear responses of tiltrotor to initial conditions in hover were computed with a combination data method of Newmark method and Neton-Raphson method.By the responses,the response process between initial time and a latter time was observed,and the stability of system was evaluated. |
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| Keywords: | tiltrotor helicopter mode aeroelastic stability evaluation |
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