Fixed-time adaptive model reference sliding mode control for an air-to-ground missile-Reference-Cited by-同舟云学术

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Fixed-time adaptive model reference sliding mode control for an air-to-ground missile

Published:2019-05 Issue:5 Volume:32 Page:1268-1280
ISSN:1000-9361
Container-title:Chinese Journal of Aeronautics
language:en
Short-container-title:Chinese Journal of Aeronautics

Author:

ZHANG Liang,WEI Changzhu^ORCID,WU Rong^ORCID,CUI Naigang

Funder

National Natural Science Foundation of China

Open Fund of National Defense Key Discipline Laboratory of Micro-Spacecraft Technology of China

Fundamental Research Funds for the Central Universities of China

Publisher

Elsevier BV

Subject

Mechanical Engineering,Aerospace Engineering

Reference40 articles.

1. Fault tolerant attitude control for rigid spacecraft;Li;IEEE Trans Aerosp Electron Syst,2017

2. Mohamed E, Yan L. Autopilot design based on robust LQR approach. Proceeding of the 28th Chinese control and decision conference; 2016 May 28–30; Yinchuan. Piscataway: IEEE Press; 2016. p. 769–73.

3. Lhachemi H, Saussié D, Zhu G. Handling hidden coupling terms in gain-scheduling control design: Application to a pitch-axis missile autopilot. AIAA guidance, navigation, and control conference; 2016 Jan 4–8; San Diego, California. Reston: AIAA; 2016. p. 747 1–21.

4. Combined optimal/classical approach to robust missile autopilot design;Nesline;J Guid Control Dyn,1981

5. Full envelope missile autopilot design using gain scheduled robust control;Buschek;J Guid Control Dyn,1999

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