F-16 nonlinear H control

Chien Chung Kung, Ciann Dong Yang

Research output: Contribution to journalConference articlepeer-review

2 Citations (Scopus)


This paper investigates the implementation of nonlinear H control theory for F-16 flight control system. The complete six degree-of-freedom nonlinear equations of motion 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 guaranteed 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)4480-4485
Number of pages6
JournalProceedings of the IEEE Conference on Decision and Control
Publication statusPublished - 2002 Dec 1
Event41st IEEE Conference on Decision and Control - Las Vegas, NV, United States
Duration: 2002 Dec 102002 Dec 13

All Science Journal Classification (ASJC) codes

  • Control and Systems Engineering
  • Modelling and Simulation
  • Control and Optimization


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