Control surface inverse algorithm and application to nonlinear H ∞ missile control

Chien Chung Kung; Ciann Dong Yang; Keng Lon Lei

doi:10.1109/CDC.2003.1272505

Control surface inverse algorithm and application to nonlinear H _∞ missile control

Chien Chung Kung, Ciann Dong Yang, Keng Lon Lei

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

1 Citation (Scopus)

Abstract

The proposed nonlinear H_inf missile autopilot in this paper is to resist maximal possible disturbances and counterbalance vortex-induced yawing moments during high AOA flight. The implementation of the nonlinear H_inf missile autopilot is solved by the control surface inverse algorithm (CSIA). The CSIA is an algorithm to compute the associated control surface deflections based on minimizing the global errors between the commands and actual control forces and moments. The derivations of the control law, the control surface inverse algorithm of the autopilot and the satisfying results of the heading reversal maneuver are demonstrated in this paper.

Original language	English
Title of host publication	Proceedings of the IEEE Conference on Decision and Control
Publisher	Institute of Electrical and Electronics Engineers Inc.
Pages	5456-5461
Number of pages	6
ISBN (Print)	0780379241
DOIs	https://doi.org/10.1109/CDC.2003.1272505
Publication status	Published - 2003
Event	42nd IEEE Conference on Decision and Control - Maui, HI, United States Duration: 2003 Dec 9 → 2003 Dec 12

Publication series

Name	Proceedings of the IEEE Conference on Decision and Control
Volume	5
ISSN (Print)	0743-1546
ISSN (Electronic)	2576-2370

Other

Other	42nd IEEE Conference on Decision and Control
Country/Territory	United States
City	Maui, HI
Period	03-12-09 → 03-12-12

All Science Journal Classification (ASJC) codes

Control and Systems Engineering
Modelling and Simulation
Control and Optimization

Access to Document

10.1109/CDC.2003.1272505

Cite this

Kung, C. C., Yang, C. D., & Lei, K. L. (2003). Control surface inverse algorithm and application to nonlinear H _∞ missile control. In Proceedings of the IEEE Conference on Decision and Control (pp. 5456-5461). (Proceedings of the IEEE Conference on Decision and Control; Vol. 5). Institute of Electrical and Electronics Engineers Inc.. https://doi.org/10.1109/CDC.2003.1272505

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title = "Control surface inverse algorithm and application to nonlinear H ∞ missile control",

abstract = "The proposed nonlinear H_inf missile autopilot in this paper is to resist maximal possible disturbances and counterbalance vortex-induced yawing moments during high AOA flight. The implementation of the nonlinear H_inf missile autopilot is solved by the control surface inverse algorithm (CSIA). The CSIA is an algorithm to compute the associated control surface deflections based on minimizing the global errors between the commands and actual control forces and moments. The derivations of the control law, the control surface inverse algorithm of the autopilot and the satisfying results of the heading reversal maneuver are demonstrated in this paper.",

author = "Kung, {Chien Chung} and Yang, {Ciann Dong} and Lei, {Keng Lon}",

year = "2003",

doi = "10.1109/CDC.2003.1272505",

language = "English",

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series = "Proceedings of the IEEE Conference on Decision and Control",

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note = "42nd IEEE Conference on Decision and Control ; Conference date: 09-12-2003 Through 12-12-2003",

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Kung, CC, Yang, CD & Lei, KL 2003, Control surface inverse algorithm and application to nonlinear H _∞ missile control. in Proceedings of the IEEE Conference on Decision and Control. Proceedings of the IEEE Conference on Decision and Control, vol. 5, Institute of Electrical and Electronics Engineers Inc., pp. 5456-5461, 42nd IEEE Conference on Decision and Control, Maui, HI, United States, 03-12-09. https://doi.org/10.1109/CDC.2003.1272505

Control surface inverse algorithm and application to nonlinear H _∞ missile control. / Kung, Chien Chung; Yang, Ciann Dong; Lei, Keng Lon.
Proceedings of the IEEE Conference on Decision and Control. Institute of Electrical and Electronics Engineers Inc., 2003. p. 5456-5461 (Proceedings of the IEEE Conference on Decision and Control; Vol. 5).

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

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N2 - The proposed nonlinear H_inf missile autopilot in this paper is to resist maximal possible disturbances and counterbalance vortex-induced yawing moments during high AOA flight. The implementation of the nonlinear H_inf missile autopilot is solved by the control surface inverse algorithm (CSIA). The CSIA is an algorithm to compute the associated control surface deflections based on minimizing the global errors between the commands and actual control forces and moments. The derivations of the control law, the control surface inverse algorithm of the autopilot and the satisfying results of the heading reversal maneuver are demonstrated in this paper.

AB - The proposed nonlinear H_inf missile autopilot in this paper is to resist maximal possible disturbances and counterbalance vortex-induced yawing moments during high AOA flight. The implementation of the nonlinear H_inf missile autopilot is solved by the control surface inverse algorithm (CSIA). The CSIA is an algorithm to compute the associated control surface deflections based on minimizing the global errors between the commands and actual control forces and moments. The derivations of the control law, the control surface inverse algorithm of the autopilot and the satisfying results of the heading reversal maneuver are demonstrated in this paper.

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