Helicopter Rotor Is Controlled To Coordinate The Loading System Control

Airscrew manipulation control is one of the key technologies to a helicopter. It is very important for studying and improving the flight control system of helicopter to carry out airscrew loading test on the ground and simulate the aerodynamic load acting on the airscrew when flying. In this thesis, the aerodynamic load simulation of one type of helicopter airscrew was studied according to a practical project. Some issues such as strong position disturbance, multi-channel coupling and nonlinearity were analyzed and researched roundly.First, the structure of helicopter airscrew loading system was introduced, On the basis of single channel loading system's math model, the system's dynamic performance was analyzed. Combining the mechanism of strong position disturbance and its math expression, factors influencing the strong position disturbance was investigated. In this thesis, Structure Invariability principle was proposed as feed-forward compensation to the disturbance. It has been tested that the control strategy was feasible.This thesis analyzed the coupling relationship of the channels of the system and proposed its math model. The single channel theory was applied to the multi-channel system and the additional force was restrained effectively.As to electro-hydraulic servo system, it was nonlinear because of the nonlinear servo valve throttle equation ignoring some nonlinear factors such as backlash and dead zone. The time-varying disturbance and strong coupling also made the system nonlinear. Nonlinear control theory and CMAC neural network was applied to propose math model and control according to the system's nonlinearity, and the control system's performance was enhanced compared to pure classical control theory.Simulation results showed that the loading control system can accomplish the loading test control and ensure the system's performance targets.