Analytical study of the subsonic wing-rock phenomenon for slender delta wings

Adaptive feedback linearizing control schemes are used to suppress limit cycle oscillations in nonlinear systems where the system parameters are either unknown or uncertain. Parameter convergence is desirable in these schemes as it provides a measure of robustness of the scheme and also permits the unknown/uncertain system parameters to be estimated. In recent work, we have shown how using a persistently exciting forcing it is possible to achieve parameter convergence in nonlinear limit cycling systems. In practice, however, limits on the control input to the plant due to saturation must be considered, and the main goal of this work is to analyze the effect of input saturation on parameter convergence in an adaptive feedback linearization framework. In particular, a technique known as control hedging is incorporated and the effectiveness of this method for very severe saturation constraints has been evaluated. Results are presented for a single degree-of-freedom wing rock dynamics model and a multi degree-of-freedom combustion acoustics model showing successful parameter convergence even in the presence of input saturation.

show abstract

“…The model is simulated with a 1 = −0.05686, a 2 = 0.03254, a 3 = 0.07334, a 4 = −0.3597, a 5 = 1.4681, and d 1 = 1, as given in Ref. [25].…”

Section: Delta Wing Roll Dynamicsmentioning

confidence: 99%

“…The nonlinear model for the delta wing roll dynamics has been taken from [25], and is given as follows: …”

Section: Delta Wing Roll Dynamicsmentioning

confidence: 99%

Parameter convergence in adaptive feedback linearizing control of limit cycling systems with input saturation

Ananthkrishnan

Bansal

Jain

et al. 2010

Int. J. Control Autom. Syst.

View full text Add to dashboard Cite

show abstract

“…Then we have Nayfeh et al (1989) and Elzebda et al (1989) and is based on wind tunnel data in Levin and Katz (1984). The objective of this example is to demonstrate the auto-tuning algorithm presented earlier.…”

Section: Aircraft Wing Rock Examplementioning

confidence: 99%

Stable auto-tuning of hybrid adaptive fuzzy/neural controllers for nonlinear systems

Nounou

Passino

2005

Engineering Applications of Artificial Intelligence

View full text Add to dashboard Cite

“…If this rolling motion is a transient the motion is usually called "wing drop" while if it is periodic in the roll angle it is called "wing rock". Wing rock has been modeled Nayfeh et al [109], Ericcson [110] as a limit cycle oscillation due to nonlinear self-excited coupling between the aerodynamic flow and the rolling motion of the aircraft. Wing drop has been modeled by including this effect Kokolios and Cook [111] and also the oscillating aerodynamic rolling moment that may occur even in the absence of aircraft motion.…”

Section: Abrupt Wing Stallmentioning

confidence: 99%