Abstract
This paper presents a nonlinear methodology for the control of a high angle of attack aircraft, in particular, a modified F-18 aircraft. As a modern combat aircraft demands better maneuverability and performance over domains which include high angles of attack, research in high angle of attack is presently at an advanced stage. An adaptive controller is developed to maneuver an aircraft at a high angle of attack even if the aircraft is required to fly over a highly nonlinear flight regime. The adaptive, controller presented in this paper is based on nonlinear prediction models, and can be constructed to minimize the given cost function or the difference of a described Lyapunov function with respect to the control input at each step. A controller uses system identification parameters to calculate a command signal so that the output of system follows the reference trajectory. The control is calculated to let system follow the reference trajectory under some constraints. This paper shows that nonlinear adaptive control can be utilized effectively to control high performance aircraft such as the F-18 aircraft for rapid maneuvers with large changes in angle of attack.
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Abbreviations
- LF :
-
Lyapunov function
- P :
-
Covariance matrix
- α:
-
Angle of attack
- αref :
-
Reference trajectory of angle of attack
- αcmd :
-
Command signal of angle of attack
- δh :
-
Elevator deflection
- \(\delta _{h_{cmd} } \) :
-
Command signal of elevator deflection
- \(\delta _{v_{cmd} } \) :
-
command signal of thrust vector angle
- δv :
-
Thrust vector angle between Tx and Tz
- ρi :
-
Weighting factor in performance index
- Φ:
-
Regression vector in system identification
- θ:
-
Parameters to be estimated
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Cho, S., Cho, K.R. Nonlinear adaptive control for high angle of attack flight. KSME Journal 9, 147–155 (1995). https://doi.org/10.1007/BF02953616
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DOI: https://doi.org/10.1007/BF02953616