The Design of Fault-Tolerant Flight Control within Actuator Control Authority

被引：0
|
作者：
Yu, Xiang [1 ,2 ]
Fu, Yu [2 ]
Zhang, Youmin [3 ,4 ]
机构：
[1] Hunan Univ, Coll Mech & Vehicle Engn, Changsha 410082, Hunan, Peoples R China
[2] Concordia Univ, Dept Mech & Ind Engn, Montreal, PQ H3G 1M8, Canada
[3] Xian Univ Technol, Xian 710048, Shaanxi, Peoples R China
[4] Concordia Univ, Montreal, PQ H3G 1M8, Canada
来源：
2016 IEEE CHINESE GUIDANCE, NAVIGATION AND CONTROL CONFERENCE (CGNCC) | 2016年
关键词：
Fault-tolerant flight control; actuator amplitude and rate limits; adaptive sliding mode control; CONTROL-SYSTEM DESIGN; RATE-SATURATING ACTUATORS; PERFORMANCE DEGRADATION; SLIDING MODE; DIAGNOSIS; ROBUST; UAV;
D O I：
暂无
中图分类号：
TP [自动化技术、计算机技术];
学科分类号：
0812 ;
摘要：
When faults of some flight actuators have occurred, the aggressive use of fault-free actuators is often caused. This study focuses on a fault-tolerant flight control (FTFC) scheme, which is capable of tolerating aircraft actuator failures and respecting the control authority of healthy actuators. Adaptive sliding mode control (ASMC) technique is exploited in the FTFC design to ensure that the amplitudes and rates of the healthy actuators remain within the limited ranges. Simulation studies of nonlinear Boeing 747 longitudinal model are carried out to validate the effectiveness of the proposed scheme.
引用
收藏
页码：1851 / 1856
页数：6
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