Nonlinear H control theory and implement in flight control

C. C. Kung, C. D. Yang

Research output: Contribution to journalArticlepeer-review

Abstract

This paper investigates the implementation of nonlinear H control theory for F-16 flight control system. The nonlinear equations of motion with six degrees of freedom for F-16 are considered directly to design the nonlinear H flight controller by treating the longitudinal and lateral motions as a whole. The associated Hamilton-Jacobi partial differential inequality is solved analytically, resulting in a nonlinear H controller with simple proportional feedback structure. Real aerodynamic data and engine data of F-16 are employed to determine the angles of control surface deflection from the nonlinear H control command. Feasibility of tracking nonlinear H control command by using F-16 actuator system is discussed in detail, and the stability and robustness of nonlinear H flight control system implemented by F-16 actuators are confirmed over large flight envelope in a six degree-of-freedom flight simulator.

Original languageEnglish
Pages (from-to)23-30
Number of pages8
JournalZhongguo Hangkong Taikong Xuehui Huikan/Transactions of the Aeronautical and Astronautical Society of the Republic of China
Volume33
Issue number1
Publication statusPublished - 2001 Mar 1

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

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