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Robust flight control of rotorcraft.

机译：旋翼飞机的鲁棒飞行控制。

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摘要

With recent design improvement in fixed wing aircraft, there has been a considerable interest in the design of robust flight control systems to compensate for the inherent instability necessary to achieve desired performance. Such systems are designed for maximum available retention of stability and performance in the presence of significant vehicle damage or system failure. The rotorcraft industry has shown similar interest in adopting these reconfigurable flight control schemes specifically because of their ability to reject disturbance inputs and provide a significant amount of robustness for all but the most catastrophic of situations. The research summarized herein focuses on the extension of the pseudo-sliding mode control design procedure interpreted in the frequency domain. Application of the technique is employed and simulated on two well known helicopters, a simplified model of a hovering Sikorsky S-61 and the military's Black Hawk UH-60A also produced by Sikorsky. The Sikorsky helicopter model details are readily available and was chosen because it can be limited to pitch and roll motion reducing the number of degrees of freedom and yet contains two degrees of freedom, which is the minimum requirement in proving the validity of the pseudo-sliding control technique. The full order model of a hovering Black Hawk system was included both as a comparison to the S-61 helicopter design system and as a means to demonstrate the scaleability and effectiveness of the control technique on sophisticated systems where design robustness is of critical concern.
机译：随着近来固定翼飞机设计的改进，人们对稳健的飞行控制系统的设计产生了极大的兴趣，以补偿实现所需性能所需的固有不稳定性。此类系统旨在在出现严重的车辆损坏或系统故障的情况下最大程度地保持稳定性和性能。旋翼机行业对采用这些可重新配置的飞行控制方案表现出了类似的兴趣，特别是因为旋翼飞机能够拒绝干扰输入并为除灾难性以外的所有情况提供强大的鲁棒性。本文总结的研究集中于在频域中解释的伪滑模控制设计过程的扩展。该技术的应用已在两架众所周知的直升机上进行了模拟，它们是悬停的西科斯基S-61的简化模型和西科斯基也生产的军方“黑鹰” UH-60A。西科斯基直升机模型的详细信息随时可用并被选择，因为它可以限于俯仰和侧倾运动，从而减少了自由度的数量，但包含两个自由度，这是证明伪滑行有效性的最低要求控制技术。悬停的“黑鹰”系统的完整订单模型既包括与S-61直升机设计系统的比较，也包括在复杂性设计中证明控制技术的可扩展性和有效性的方法，而设计鲁棒性是至关重要的。

著录项

  • 作者

    Pechner, Adam Daniel.;

  • 作者单位

    University of California, Davis.;

  • 授予单位 University of California, Davis.;
  • 学科 Engineering Aerospace.;Engineering Mechanical.
  • 学位 M.S.
  • 年度 2010
  • 页码 99 p.
  • 总页数 99
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

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