High performance flight control systems based on the nonlinear dynamic inversion (NDI) principle require highly accurate models of aircraft aerodynamics. In general, the accuracy of the internal model determines to what degree the system nonlinearities can be canceled; the more accurate the model, the better the cancellation, and with that, the higher the performance of the controller. In this ...

Improvements in testing and modeling of nonlinear and unsteady aerodynamic effects for flight dynamics predictions of vehicle performance is critical to enable the design and implementation of new, innovative vehicle concepts. Any configuration which exhibits significant flow separation, nonlinear aerodynamics, control interactions or attempts maneuvering through one or more conditions such as ...

In this paper, the Stability Augmentation System (SAS) is designed to improve the stability while Parallel Evolutionary Optimization based on Lagrangian I1 (PEvolian 11) is successfully applied to satisfy several constraints and to minimize the rising time. A controller to stabilize F-16 aircraft flying with a steady state around the altitude of 25,OOOft is described. The nonlinear pitching mot...

This paper reports the latest development of several techniques for adaptive flight envelope estimation and protection system for aircraft under damage upset conditions. Through the integration of advanced fault detection algorithms, real-time system identification of the damage/faulted aircraft and flight envelop estimation, real-time decision support can be executed autonomously for improving...

the amount of analysis and testing required per mission must be reduced over that performed for the partially re-usable Space Shuttle. A goal for future RLV flight control is to design and test the flight control system to operate within a prescribed flight envelope and loading margin, and requiring only payload/fuel parameters and “route” to be specified for a given mission. It has been estima...

The control augmentation systems are very important to keep the stability and manipulability in the flight control systems. The general flight control laws are designed by static designs and dynamic fits. To improve the adaptive capability, a new method of control laws design was introduced by using dynamic optimization genetic algorithms. The control parameters were adjusted online in the flig...