首页> 外文期刊>Mechanical systems and signal processing >Disturbance observer-based adaptive fault-tolerant control for a quadrotor helicopter subject to parametric uncertainties and external disturbances
【24h】

Disturbance observer-based adaptive fault-tolerant control for a quadrotor helicopter subject to parametric uncertainties and external disturbances

机译:受到参数不确定性和外部干扰的四旋翼直升机基于干扰观测器的自适应容错控制

获取原文
获取原文并翻译 | 示例

摘要

This paper presents a disturbance observer-based adaptive sliding mode control (SMC) strategy for a quadrotor helicopter subject to multiple actuator faults, parametric uncertainties, and external disturbances. Unlike most of the existing control strategies for quadrotor helicopters, actuator faults, parametric uncertainties, and external disturbances can be simultaneously compensated within the proposed control scheme. Firstly, by employing the adaptive control parameters in both continuous and discontinuous control parts, the proposed control strategy can generate appropriate control signals to accommodate actuator faults and parametric uncertainties without merely relying on the robust discontinuous control strategy of SMC. Then, a nonlinear disturbance observer is designed and integrated to attenuate external disturbances while keeping the small value of the discontinuous control gain of SMC. In addition, the stability analysis of the proposed control strategy is given, showing that the presented controller can ensure system tracking performance and make the tracking errors arbitrarily small under the concerned situation. The effectiveness of the proposed control strategy is demonstrated through comparative numerical simulations and experimental tests of a quadrotor helicopter under different faulty and uncertain scenarios. (C) 2018 Published by Elsevier Ltd.
机译:本文为四旋翼直升机提出了一种基于干扰观测器的自适应滑模控制(SMC)策略,该策略具有多个执行器故障,参数不确定性和外部干扰。与大多数现有的四旋翼直升机控制策略不同,在建议的控制方案内可以同时补偿执行器故障,参数不确定性和外部干扰。首先,通过在连续和不连续控制部分中都采用自适应控制参数,所提出的控制策略可以生成适当的控制信号以适应执行器故障和参数不确定性,而不仅依赖于SMC的鲁棒不连续控制策略。然后,设计并集成了一个非线性干扰观测器,以衰减外部干扰,同时保持SMC不连续控制增益的较小值。另外,对所提出的控制策略进行了稳定性分析,表明所提出的控制器能够在相关情况下保证系统的跟踪性能,并使跟踪误差任意减小。通过比较数值模拟和四旋翼直升机在不同故障和不确定情况下的实验测试,证明了所提出控制策略的有效性。 (C)2018由Elsevier Ltd.发布

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