Nonlinear H∞ flight control of general six degree-of-freedom motions

Ciann-Dong Yang, Chien Chung Kung

Research output: Contribution to journalArticle

1 Citation (Scopus)

Abstract

This paper investigates the application of nonlinear H control theory to flight vehicles whose complete six degree-of-freedom nonlinear equations of motion are considered directly without linearization. Nonlinear flight control modes such as velocity control, body-rate control, attitude control, and hovering control are designed in a unified framework such that the derived nonlinear H control law is valid for arbitrary flight vehicles. The most difficult and challenging task involved in applying the nonlinear H control theory is to solve the associated Hamilton-Jacobi partial differential inequality (HJPDI). In this paper we show that the HJPDI of flight control problems can be solved analytically with simple manipulations. A closed-form expression for the nonlinear H flight controller is derived from the solution of HJPDI and shown to be in the simple structure of proportional feedback. The numerical simulations show that the derived nonlinear H control law can ensure global and asymptotical stability of the closed loop system and have strong robustness against wind gusts with varying statistical characteristics.

Original languageEnglish
Pages (from-to)1852-1856
Number of pages5
JournalProceedings of the American Control Conference
Volume3
Publication statusPublished - 2000

Fingerprint

Control theory
Velocity control
Attitude control
Linearization
Closed loop systems
Nonlinear equations
Equations of motion
Feedback
Controllers
Computer simulation

All Science Journal Classification (ASJC) codes

  • Control and Systems Engineering

Cite this

@article{15f5e52638154f32bec04e86805bc1c8,
title = "Nonlinear H∞ flight control of general six degree-of-freedom motions",
abstract = "This paper investigates the application of nonlinear H∞ control theory to flight vehicles whose complete six degree-of-freedom nonlinear equations of motion are considered directly without linearization. Nonlinear flight control modes such as velocity control, body-rate control, attitude control, and hovering control are designed in a unified framework such that the derived nonlinear H∞ control law is valid for arbitrary flight vehicles. The most difficult and challenging task involved in applying the nonlinear H∞ control theory is to solve the associated Hamilton-Jacobi partial differential inequality (HJPDI). In this paper we show that the HJPDI of flight control problems can be solved analytically with simple manipulations. A closed-form expression for the nonlinear H∞ flight controller is derived from the solution of HJPDI and shown to be in the simple structure of proportional feedback. The numerical simulations show that the derived nonlinear H∞ control law can ensure global and asymptotical stability of the closed loop system and have strong robustness against wind gusts with varying statistical characteristics.",
author = "Ciann-Dong Yang and Kung, {Chien Chung}",
year = "2000",
language = "English",
volume = "3",
pages = "1852--1856",
journal = "Proceedings of the American Control Conference",
issn = "0743-1619",
publisher = "Institute of Electrical and Electronics Engineers Inc.",

}

Nonlinear H∞ flight control of general six degree-of-freedom motions. / Yang, Ciann-Dong; Kung, Chien Chung.

In: Proceedings of the American Control Conference, Vol. 3, 2000, p. 1852-1856.

Research output: Contribution to journalArticle

TY - JOUR

T1 - Nonlinear H∞ flight control of general six degree-of-freedom motions

AU - Yang, Ciann-Dong

AU - Kung, Chien Chung

PY - 2000

Y1 - 2000

N2 - This paper investigates the application of nonlinear H∞ control theory to flight vehicles whose complete six degree-of-freedom nonlinear equations of motion are considered directly without linearization. Nonlinear flight control modes such as velocity control, body-rate control, attitude control, and hovering control are designed in a unified framework such that the derived nonlinear H∞ control law is valid for arbitrary flight vehicles. The most difficult and challenging task involved in applying the nonlinear H∞ control theory is to solve the associated Hamilton-Jacobi partial differential inequality (HJPDI). In this paper we show that the HJPDI of flight control problems can be solved analytically with simple manipulations. A closed-form expression for the nonlinear H∞ flight controller is derived from the solution of HJPDI and shown to be in the simple structure of proportional feedback. The numerical simulations show that the derived nonlinear H∞ control law can ensure global and asymptotical stability of the closed loop system and have strong robustness against wind gusts with varying statistical characteristics.

AB - This paper investigates the application of nonlinear H∞ control theory to flight vehicles whose complete six degree-of-freedom nonlinear equations of motion are considered directly without linearization. Nonlinear flight control modes such as velocity control, body-rate control, attitude control, and hovering control are designed in a unified framework such that the derived nonlinear H∞ control law is valid for arbitrary flight vehicles. The most difficult and challenging task involved in applying the nonlinear H∞ control theory is to solve the associated Hamilton-Jacobi partial differential inequality (HJPDI). In this paper we show that the HJPDI of flight control problems can be solved analytically with simple manipulations. A closed-form expression for the nonlinear H∞ flight controller is derived from the solution of HJPDI and shown to be in the simple structure of proportional feedback. The numerical simulations show that the derived nonlinear H∞ control law can ensure global and asymptotical stability of the closed loop system and have strong robustness against wind gusts with varying statistical characteristics.

UR - http://www.scopus.com/inward/record.url?scp=0034540661&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=0034540661&partnerID=8YFLogxK

M3 - Article

VL - 3

SP - 1852

EP - 1856

JO - Proceedings of the American Control Conference

JF - Proceedings of the American Control Conference

SN - 0743-1619

ER -