Evaluation of the Angle of Attack Limiter of the F-16 C/D Aircraft

摘要

The angle-of-attack (AOA) limiter used in the present fighter aircraft can provide safe, head-up maneuvering capability up to full aerodynamic potential of the fighter. However, the F-16 aircraft flight control system limits the effective normal acceleration (g) command with the AOA. The AOA limiter utilized in the F-16 aircraft adversely impacts air-to-air tracking tasks. Therefore, it should be modified to improve this tracking capability. Two aircraft models are developed to evaluate current AOA limiter effects on the aircraft dynamics. The first model is a linear model which is developed in state space form for the F-16 from linearized aerodynamic data. This is accomplished at four points in the flight enveloped. The second model is a non-linear model which is developed using non-linear equations of motion and flight control system equations and then coded using PTRAN simulation language employed on SIMSTAR hybrid computer system at the Air Force Institute of Technology. After validation, these models are used for the evaluation of the AOA limiter.