Performance investigation of extended-state-observer-based roll autopilot design

被引:1
作者
Sirisha, Ch V. [1 ]
Das, Ranajit [1 ]
Talole, S. E. [2 ]
机构
[1] Def Res & Dev Lab, Directorate Syst, Hyderabad 500058, Andhra Pradesh, India
[2] Def Inst Adv Technol, Dept Aerosp Engn, Pune, Maharashtra, India
关键词
Roll autopilot; extended state observer; robust control; MISSILE; CONTROLLERS; BANDWIDTH; TRACKING;
D O I
10.1177/0954410015571430
中图分类号
V [航空、航天];
学科分类号
08 ; 0825 ;
摘要
In this work, performance analysis of the recently appeared extended-state-observer (ESO)-based roll autopilot design is carried out. Firstly, considering a more realistic roll dynamics, performance comparison of the ESO-based design with several classical roll autopilot structures is carried out and the related results are presented. Next, the better performing designs are implemented and validated through a high fidelity nonlinear 6-DOF environment for a typical tactical missile in a realistic engagement scenario. Lastly, performance of the ESO-based design is investigated using Monte Carlo simulations under several subsystem parameter uncertainties. The results show that the ESO-based design offers satisfactory performance in controlling roll angle and its rate in the presence of significant disturbances, parameter uncertainties and cross-coupling effects and thus offers a viable approach towards design of roll autopilot for high performance tactical missiles.
引用
收藏
页码:2205 / 2220
页数:16
相关论文
共 46 条
[1]   LARGE ANGLE-OF-ATTACK MISSILE CONTROL CONCEPTS FOR AERODYNAMICALLY CONTROLLED MISSILES [J].
ARROW, A ;
YOST, DJ .
JOURNAL OF SPACECRAFT AND ROCKETS, 1977, 14 (10) :606-613
[2]   Design and flight test of a robust autopilot for the IRIS-T air-to-air missile [J].
Buschek, H .
CONTROL ENGINEERING PRACTICE, 2003, 11 (05) :551-558
[3]   Full envelope missile autopilot design using gain scheduled robust control [J].
Buschek, H .
JOURNAL OF GUIDANCE CONTROL AND DYNAMICS, 1999, 22 (01) :115-122
[4]   Adaptive autopilot design for guided munitions [J].
Calise, AJ ;
Sharma, M ;
Corban, JE .
JOURNAL OF GUIDANCE CONTROL AND DYNAMICS, 2000, 23 (05) :837-843
[5]   ROLL-ATTITUDE CONTROL OF A MISSILE HAVING A STRONG AERODYNAMIC NONLINEARITY [J].
CHRISTOPHER, PAT .
INTERNATIONAL JOURNAL OF CONTROL, 1980, 31 (02) :209-218
[6]  
ChV Sirisha, 2012, P INT C ADV CONTR OP
[7]  
COLGREN R, 1994, PROCEEDINGS OF THE 1994 AMERICAN CONTROL CONFERENCE, VOLS 1-3, P2109
[8]   Three-axes missile autopilot design: From linear to nonlinear control strategies [J].
Devaud, E ;
Harcaut, JP ;
Siguerdidjane, H .
JOURNAL OF GUIDANCE CONTROL AND DYNAMICS, 2001, 24 (01) :64-71
[9]   A new robust algorithm to improve the dynamic performance on the speed control of induction motor drive [J].
Feng, G ;
Liu, YF ;
Huang, LP .
IEEE TRANSACTIONS ON POWER ELECTRONICS, 2004, 19 (06) :1614-1627
[10]  
Fleeman E.F., 2001, AIAA Education Series