This paper presents dynamic analysis and nonlinear control of laterally mass varying combat aircraft based on a six degree-of-freedom model derived for a variable mass system. The objective is to investigate the effects of asymmetric lateral mass variation, due to mass ejection, from two different perspectives – the open loop dynamic behavior through bifurcation analysis; and the closed loop control performance while carrying out some demanding maneuvers. Bifurcation analysis reveals considerable coupling between the longitudinal and lateral-directional channels even for a modest lateral shift in the center-of-mass due to store ejection, which in turn is observed to give rise to a spiral-dive like divergent mode even at low angles-of-attack. Thereafter, the well-known high angle-of-attack cobra maneuver is implemented for the symmetric center-of-mass case using sliding mode control technique and using a new single loop control formulation in contrast with the conventional inner-outer loop formulation. The proposed single loop control formulation is further extended to handle the lateral movement of center-of-mass due to asymmetric store ejection using the asymmetric dynamics model proposed and derived in this paper.
Nonlinear dynamics and control of a laterally mass varying fighter aircraft
2018-12-01
17 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Fighter : a history of fighter aircraft
SLUB | 1973
|Nonlinear autopilot design for a fighter aircraft
AIAA | 1995
|Adaptive Control of Advanced Fighter Aircraft in Nonlinear Flight Regimes
Online Contents | 2008
|Training for fighter aircraft; Fighter training 2007
British Library Conference Proceedings | 2007
|Fighter : a history of fighter aircraft
GWLB - Gottfried Wilhelm Leibniz Bibliothek | 1974
|