The Study On Flight Adaptive Control Technology Of Helicopter

Helicopter is developing along with the intelligent direction. The traditional flightcontrol technology is difficult to meet the development of modern helicopter. Helicopteractive control technology, integrated control technology is inevitable trend. With thelaunch of the new concept、 unmanned helicopter, the design of flight control system hasbecome one of the most crucial work. Combined with modeling method and experienceat home and abroad, this paper adopts the Blade element theory and vortex theory orsome experience curve and so on for the main components of the helicopter modeling.The dynamic、static stability and maneuverability are analysed also. To prepare for flightcontrol system and later simulation, the mechanism and simulation methods for electricservo rudder modeling are all used in this paper.To realize active flying, adaptive control is an appropriate choice and is proposedfor aerospace. Any control theory is a controlled object oriented. building accurate modelof object is always an obstacle for control technology into practice. Accurately obtainhelicopter modeling of the complex requirements, the current modeling technology isdifficult to meet. Because not only the structure of the helicopter is complex, theaerodynamic force is very complex and unstable in flight, flight mode also changes overtime. Real-time compution for model parameters, automatic identification for flight mode,and undisturbed switch for helicopter flight control law are requested for today’shecopters. Self-tuning control is tried to applied to the flight attitude control, along withaugmented least squares recursive identification algorithm to design the parameterestimator, and the generalized minimum variance pole assignment self-tuning controller.Simulation of the controller is made to hovering mode by matlab, without considering thecoupling between channels. Good effect is obtainedSelf-tuning control computation is fairly complex. A direct controller design methodbased on data-virtual reference feedback correction control is introduced in this paper,which is to design the helicopter flight controllers, so as to avoid the mathematicalmodeling. To improve the performance of the controller, the basis function of PI D and some improvement on arithmetic for more easy to computing and programming, areall introduced in this paper. Finally, simulation is ideal. Of course, A lot of problems needfurther analysis and improvement.