Event-Triggered Policy to Spacecraft Attitude Stabilization With Actuator Output Nonlinearities

被引：25

作者：

Dai, Ming-Zhe ^{[1
]}

Xiao, Bing ^{[2
]}

Zhang, Chengxi ^{[3
]}

Wu, Jin ^{[4
]}

机构：

[1] Cent South Univ, Sch Aeronaut & Astronaut, Changsha 410083, Peoples R China

[2] Northwestern Polytech Univ, Sch Automat, Xian 710072, Peoples R China

[3] Harbin Inst Technol Shenzhen Campus, Sch Elect & Informat Engn, Shenzhen 518055, Peoples R China

[4] Hong Kong Univ Sci & Technol, Dept Elect & Comp Engn, Hong Kong, Peoples R China

来源：

IEEE TRANSACTIONS ON CIRCUITS AND SYSTEMS II-EXPRESS BRIEFS | 2021年 / 68卷 / 08期

基金：

中国国家自然科学基金;

关键词：

Space vehicles; Actuators; Attitude control; Convergence; Data communication; Quantization (signal); Circuits and systems; Spacecraft attitude control; event-triggered sampling; actuator output nonlinearities; SLIDING MODE CONTROL; TRACKING CONTROL; ROBUST; SYSTEMS;

D O I：

10.1109/TCSII.2021.3056761

中图分类号：

TM [电工技术]; TN [电子技术、通信技术];

学科分类号：

0808 ; 0809 ;

摘要：

This brief investigates event-triggered control for spacecraft attitude stabilization under the influence of actuator output nonlinearities. Under a designed event-triggered policy, the influences of actuators' inherent nonlinearity and network quantized transmission are evaluated under a unified framework. Compared with the previous results, the influences of data transmission and actuators' inherent nonlinearities are uniformly described as the actuator output nonlinearities, and the event-triggered policy reduces the effects of constants commonly introduced into triggering conditions on the final state convergence regions and achieves Zeno-free triggering. Simulations verify theoretical results.

引用

页码：2855 / 2859

页数：5

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