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**Flight control design using non-linear inverse dynamics.**
*(English)*
Zbl 0649.93051

Summary: Aircraft in extreme flight conditions can encounter severe non-linear effects generated from high angles of attack and high angular rates. Flight control systems based upon non-linear inverse dynamics offer the potential for providing improved levels of safety and performance in these flight conditions over the competing designs developed using linearizing assumptions. Inverse dynamics are generated for specific command variable sets of a 12-state non-linear aircraft model to develop a control system which is valid over the entire flight envelope. Detailed descriptions of the inertial dynamic and aerodynamic models are given, and it is shown how the command variable set are altered as a function of the system state to add stall prevention features to the system. Simulation results are presented for various mission objectives over a range of flight conditions to confirm the effectiveness of the design.

### MSC:

93C95 | Application models in control theory |

76G25 | General aerodynamics and subsonic flows |

93C10 | Nonlinear systems in control theory |

93B50 | Synthesis problems |

93C15 | Control/observation systems governed by ordinary differential equations |

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\textit{S. H. Lane} and \textit{R. F. Stengel}, Automatica 24, No. 4, 471--483 (1988; Zbl 0649.93051)

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### References:

[1] | Asseo, S. J., Decoupling of a class of nonlinear systems and its application to an aircraft control problem, AIAA J. Aircraft, 10, 739-747 (1973) |

[2] | Ehrenstrom, W. A., A lateral-directional controller for high-angle-of-attack flight, (M.S.E. Thesis (1983), Princeton University) |

[3] | Etkin, B., (Dynamics of Atmospheric Flight (1972), John Wiley: John Wiley New York) |

[4] | Falb, P. L.; Wolovich, W. A., Decoupling in the design and synthesis of multivariable control systems, IEEE Trans. Aut. Control, AC-12, 651-659 (1967) |

[5] | Fratter, C., Determination of aerodynamic coefficients for the avionics research aircraft using estimation-before-modeling techniques, (M.S.E. Thesis (1982), Princeton University) |

[6] | Freund, E., Decoupling and pole assignment in nonlinear systems, Electron. Lett., 9, 373-374 (1973) |

[7] | Freund, E., The structure of decoupled nonlinear systems, Int. J. Control, 21, 443-450 (1975) · Zbl 0306.93008 |

[8] | Lane, S. H.; Stengel, R. F., Nonlinear inverse dynamics control laws-a sampled data approach, (Proc. 1987 American Control Conf.. Proc. 1987 American Control Conf., Mineapolis, MN. (1987)), 1224-1226 |

[9] | Menon, P. K.A.; Badgett, M. E.; Walker, R. A., Nonlinear flight test trajectory controllers for aircraft, (AIAA Guidance and Control Conf.. AIAA Guidance and Control Conf., Snow Mass, CO. AIAA Guidance and Control Conf.. AIAA Guidance and Control Conf., Snow Mass, CO, AIAA-85-1890-CP (1985)) · Zbl 0624.93044 |

[10] | Meyer, G.; Cicolani, L., Application of nonlinear system inverses to automatic flight control designs—system concepts and flight evaluations, Theory and Application of Optimal Control in Aerospace Systems. Theory and Application of Optimal Control in Aerospace Systems, AGARD—AG251, 10.1-10.29 (1981) |

[11] | Meyer, G.; Su, R.; Hunt, L. R., Application of nonlinear transformations to automatic flight control, Automatica, 20, 103-107 (1984) · Zbl 0527.93014 |

[12] | Silhouette, X., Estimation of the aerodynamic coefficients and derivatives of the Navion aircraft at high angles of attack, (M.S.E. Thesis (1986), Princeton University) |

[13] | Singh, S. N.; Rugh, W. J., Decoupling in a class of nonlinear systems by state variable feedback, AIAA J. Dynamics Syst. Meas. Control, 323-329 (1972) |

[14] | Singh, S. N.; Schy, A., Nonlinear decoupled control synthesis for maneuvering aircraft, (Proc. 1979 Conf. Decision and Control. Proc. 1979 Conf. Decision and Control, Fort Lauderdale, FL (1979)), 360-370 · Zbl 0428.93027 |

[15] | Singh, S. N.; Schy, A., Output feedback nonlinear decoupled control synthesis and observer design for maneuvering aircraft, Int. J. Control, 31, 781-806 (1980) · Zbl 0431.93029 |

[16] | Sri-Jayantha, M.; Stengel, R. F., A microprocessor-based data-aquisition system for stall/spin research, IEEE Trans. Aero. Elec. Syst., V AES-19, 59-70 (1983) |

[17] | Sri-Jayantha, M., Data aquisition and aerodynamic coefficient estimation at high angles of attack, (Ph.D. Dissertation (1983), Princeton University) |

[18] | Stengel, R. F.; Nixon, W. B., Investigation of the stalling characteristics of a general aviation aircraft, AIAA J. Aircraft, 19, 425-434 (1982) |

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