Research On Adaptive Control Method For Helicopter Flying Quality Design

With the development and improvement of helicopter flying quality specification, the flying quality specification is one of the most important criteria for helicopters design. ADS-33E-PRF is the state of art handing qualities requirements for military rotorcraft, the control law has been designed in this dissertation based on the performance requirements defined in the flying quality specification. Then the optimization of helicopter flying quality is implemented.There exists non-ideal noise when the helicopters flying. A simulation test for helicopters is established in Matlab/Simulink, and the flight simulation experiment of a UH-60 helicopter in non-ideal noise environment is implemented. A mathematical model of the non-idea noise is built in this dissertation, and a comprehensive identification algorithm based on the Recursive Extended Least Squares is designed which can identify the model parameters as well as the noise parameters simultaneously. The identification and verification of the flight dynamics model of the UH-60 helicopter is implemented by using the simulation test data. Finally, a comparative study of the developed method with least square method is presented.The transformation from flying quality parameters into ideal poles which are required in flight control law design is implemented by establishing an ideal model based on the performance requirements defined in the ADS-33E-PRF. The verification and analysis of these designed ideal poles is implemented.Based on the helicopter dynamic model and the designed poles, the flight control law design method is developed in this dissertation which includes two parts, one is the inner loop design, the other one is the outer loop design. The dynamic inversion method is used in the inner loop in order to decouple the helicopter. The pole placement adaptive control is applied in the outer loop in order to implement the flying quality optimization of the helicopter.At last, the closed-loop flight simulation test of hovering turn and slalom is implemented. The results show that the control law design method developed in this dissertation can increase the flying quality of the helicopter obviously, the performance as well as the robustness of the closed-loop system is improved considerably.