Zobrazeno 1 - 10
of 29
pro vyhledávání: '"James M. Buffington"'
Publikováno v:
Journal of Guidance, Control, and Dynamics. 23:561-564
Publikováno v:
Journal of Guidance, Control, and Dynamics. 22:873-883
Adual-timescaleaircrafte ight-controlproblemisaddressedviacontinuoussliding-modecontrol.Sliding-surface boundary-layer recone guration is used to account for actuator dynamics, dee ection limits, and rate limits. A recone gurable sliding-mode e ight
Manual flight control system design for fighter aircraft is one of the most demanding problems in automatic control. Fighter aircraft dynamics generally have highly coupled uncertain and nonlinear dynamics. Multivariable control design techniques off
Autor:
Dale Enns, James M. Buffington
Publikováno v:
International Journal of Control. 68:1209-1230
A longitudinal flight control law is derived that provides desirable precision aircraft-tracking response for small-amplitude commands and desirable gross acquisition response for large-amplitude commands. Dynamic inversion and proportional-plus-inte
Autor:
Dale F. Enns, James M. Buffington
Publikováno v:
Journal of Guidance, Control, and Dynamics. 19:1226-1230
A demonstration that feedback control of systems with redundant controls can be reduced to feedback control of systems without redundant controls and control allocation is presented. It is shown that control allocation can introduce unstable zero dyn
Publikováno v:
Automatica. 30:1527-1540
A full conventional envelope longitudinal axis control design is presented for a fighter aircraft capable of thrust vectoring. An inner-outer loop modular control structure is used to provide good flying quantities in the presence of highly structure
Publikováno v:
Journal of Guidance, Control, and Dynamics. 17:737-746
High-angle-of-attack flight control laws are developed for a supermaneuvera ble fighter aircraft. The methods of dynamic inversion and structured singular value synthesis are combined into an approach which addresses both the nonlinearity and robustn
Publikováno v:
Journal of Guidance, Control, and Dynamics. 17:578-583
The design, implementation, and evaluation of a full-envelope control system for the AIAA controls design challenge aircraft is presented. The control problem is divided into separate longitudinal and lateral/directional designs. The longitudinal con
Publikováno v:
Proceedings of the 37th IEEE Conference on Decision and Control (Cat. No.98CH36171).
A dual time scale aircraft flight control problem is addressed via sliding mode control theory. Actuator dynamics, deflection limits and rate limits are addressed via sliding mode controller re-configuration. The designed re-configurable sliding mode
Publikováno v:
Guidance, Navigation, and Control Conference and Exhibit.