A stall/spin event represents a critical loss of aircraft control, typically triggered by the detachment of airflow at an elevated angle of attack. Stall/spin accounts for about one-fifth of all flight accidents, and it is very likely to cause aircraft crash and casualties. It has a great impact on the combat effectiveness of the aircraft, and it is a dangerous flight state that the pilot must avoid. This paper aims at the stall/spin prediction problem of advanced fighter aircraft, and pro-poses an enhanced bifurcation analysis method based on bifurcation mutation theory and multi-scale method. The multi-scale approach accurately determines the equilibrium points of the nonlinear model. Subsequently, the conventional bifurcation analysis method is employed to address the equilibrium bifurcation diagram associated with high angles of attack for advanced fighter aircraft. This analysis examines the characteristics of both stable and unstable branches. Using the F-16 fighter as an illustrative example, we employ a nonlinear model based on Simulink to compute the time history of parameters such as angle of attack and sideslip angle. Specifically, we focus on the stable branch near the stall angle of attack and compare our findings with the predictions obtained through enhanced bifurcation analysis. The comparison results show that the enhanced bifurcation analysis method accurately predicts the spin mode of the F-16 model and verifies the feasibility of the enhanced bifurcation analysis method for analyzing the spin characteristics of an advanced fighter aircraft. The research method of this paper provides an effective tool for the stall/spin prediction of advanced fighter aircraft.
Prediction of Advanced Fighter’s Spin Characteristics Based on Enhanced Bifurcation Analysis
Lect. Notes Electrical Eng.
International Conference on Guidance, Navigation and Control ; 2024 ; Changsha, China August 09, 2024 - August 11, 2024
02.03.2025
9 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
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