Modern fighter aircrafts use fly-by-wire technology for flight control. Use of computers in flight control gives freedom in modifying flight control law under certain conditions. Current fighter aircrafts are handling control surface actuator failures in this way. The computers switch to alternate pre-computed flight control laws. With the use of online parameter estimation & reconfigurable control algorithms, unexpected/unknown failures causing change in aerodynamic characteristics can be handled. Some of these algorithms are flight tested in a limited way. The objective of this research proposal is to develop or modify existing parameter estimation algorithms as applied to modern fighter aircraft for application of reconfiguration control. It is also envisaged to develop or modify existing reconfigurable control technique as applied to modern fighter aircraft. Theoretical & simulation studies will be carried out. A combined simulation study of the online parameter estimation and reconfigurable control technique developed will also be carried out.