Pitch rate command and normal G command longitudinal flight control systems were designed using linear optimal control theory for a statically unstable, two control surface, fighter-type aircraft at both a power approach and an up-and-away flight condition. The closed-loop systems were then evaluated in man-in-the-loop simulations with pilots attempting random altitude tracking and pitch tracking tasks. The evaluation results indicated that in the power approach flight condition, normal G command was more suitable for altitude tracking and pitch rate command was preferred for pitch tracking. Results for the up-and-away flight condition were inconclusive.
Pitch Rate Versus G Command as the Longitudinal Flight Control System Design Strategy for a Statistically Unstable Fighter Type Aircraft with Two Control Surfaces
1985
32 pages
Report
Keine Angabe
Englisch
Aeronautics , Avionics , Approach , Flight control systems , Attitude control systems , Altitude , Closed loop systems , Command and control systems , Control surfaces , Control theory , Fighter aircraft , Flight , Linear systems , Man machine systems , Optimization , Pilots , Pitch(Inclination) , Pitch(Motion) , Power , Rates , Simulation , Tracking , Aircraft landings , Aerodynamic stability , Altitude tracking , Power approach , Pitch rate command , Instability
Aircraft longitudinal control without a pitch command in the autopilot
Springer Verlag | 2014
|Aircraft longitudinal control without a pitch command in the autopilot
Online Contents | 2014
|