• 主题
高级搜索  >
历史搜索 清空历史
首页> 外文会议>Saint Petersburg International Conference on Integrated Navigation Systems; 20040524-26; Saint Petersburg(RU) >SHUNTING-BASED ROBUST AUTOPILOT DESIGN
【24h】

SHUNTING-BASED ROBUST AUTOPILOT DESIGN

机译：基于顺势的强大自动驾驶仪设计

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

A robust autopilot for attitude control of the aircraft with uncertain parameters is designed. The high gain controller with forced sliding motions is used to secure adaptability in the wide region of the aircraft model parameters. The shunting method is applied to ensure the closed-loop system stability in the face of the lack of the aircraft state information. The sequential reference model is used to assign the desired closed-loop system performance. An example illustrating a typical design procedure for aircraft attitude control in the vertical maneuver plane is given. The numerical simulation results are provided for the light fighter model under the different flight conditions. The system robustness with respect to unmodelled dynamics of the actuators and sensors, airframe bending and high-rate parameter changing on the nosedive regime is numerically studied. The simulation results demonstrate efficiency and high robustness of the suggested control method.
机译：设计了一种用于参数不确定的飞机姿态控制的鲁棒自动驾驶仪。具有强制滑动功能的高增益控制器用于确保飞机模型参数在较大范围内的适应性。在缺乏飞机状态信息的情况下，采用分流方法来确保闭环系统的稳定性。顺序参考模型用于分配所需的闭环系统性能。给出一个示例，说明在垂直机动平面上控制飞机姿态的典型设计程序。为不同飞行条件下的轻型战斗机模型提供了数值模拟结果。数值研究了执行器和传感器的非建模动力学，机身弯曲和俯冲状态下的高速率参数变化方面的系统鲁棒性。仿真结果证明了所提出的控制方法的有效性和高鲁棒性。

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