## 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 language | English |
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Pages (from-to) | 23-30 |

Number of pages | 8 |

Journal | Zhongguo Hangkong Taikong Xuehui Huikan/Transactions of the Aeronautical and Astronautical Society of the Republic of China |

Volume | 33 |

Issue number | 1 |

Publication status | Published - 2001 Mar 1 |

## All Science Journal Classification (ASJC) codes

- Aerospace Engineering