...
  • 主题
高级搜索  >
历史搜索 清空历史
首页> 外文期刊>Journal of the American Helicopter Society >Analysis and Control of a Magnetorheological Landing Gear System for a Helicopter
【24h】

Analysis and Control of a Magnetorheological Landing Gear System for a Helicopter

机译：直升机磁流变起落架系统的分析与控制

获取原文
获取原文并翻译 | 示例
           
页面导航
  • 摘要
  • 著录项
  • 相似文献
  • 相关主题

摘要

This study develops the design analysis and control of adaptive magnetorheological landing gear dampers (MRLGDs) to enable adaptive shock mitigation in a lightweight helicopter. MRLGDs were designed to achieve a desired stroking load of 4000 lb (17.8 kN) over a desired equivalent sink rate range of 6-12 ft/s (1.83-3.65 m/s). The design analysis at low equivalent sink rates, v(s) < 10 ft/s (3.05 m/s), was experimentally validated using ramp displacement inputs on a servo-hydraulic testing machine at low speed. To validate the analysis at high equivalent sink rates, v(s) > 10 ft/s (3.05 m/s), single damper drop tests were performed. Two force feedback control algorithms were developed to achieve the desired constant stroking load over the desired sink rate range, that is, (1) bang-bang current control and (2) continuous current control. The effectiveness of control algorithms was evaluated using both single damper drop tests and an iron-bird test setup with a landing gear system having a pair of forward and aft MRLGDs.
机译：这项研究开发了自适应磁流变起落架减震器（MRLGD）的设计分析和控制，以实现轻型直升机的自适应减震。 MRLGD设计为在6-12 ft / s（1.83-3.65 m / s）的期望等效下沉速率范围内实现4000 lb（17.8 kN）的期望行程载荷。在低等效下沉速率下，v（s）<10 ft / s（3.05 m / s）的设计分析已通过在伺服液压试验机上低速下使用斜面位移输入进行了实验验证。为了在高等效下沉率（v（s）> 10 ft / s（3.05 m / s））下验证分析，执行了单个阻尼器跌落测试。开发了两种力反馈控制算法，以在所需的吸收速率范围内实现所需的恒定行程负载，即（1）爆炸电流控制和（2）连续电流控制。使用单个减振器跌落试验和带有起落架系统的铁鸟试验装置（具有一对前后MRLGD）评估了控制算法的有效性。

著录项

相似文献

  • 外文文献
  • 中文文献
  • 专利
获取原文

客服邮箱：kefu@zhangqiaokeyan.com

京公网安备：11010802029741号 ICP备案号：京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有

  • 客服微信

  • 服务号