Stability Analysis Of Rotor System Based On Helicopter Aerodynamics Equation

Stability and control are among the most significant considerations of the analysis and design of helicopter rotor. This paper presents analyses of the feathering and flapping equations of main rotor blades by changing some principle symbols value in hover. The objective of the project is to obtain the stable solution for the flapping-feathering system by using engineering software MATLAB to minimize the calculation of the blade equations and analyze the stability regions of the solution by pole-zero plot. The goal of this paper is to analysis the stability of the rotor system when changing some given aerodynamics parameters in the built model. Here we mainly discuss the influence of the flap-pitch coupling Kp in the rotor system and improve the design. The fourth part of the paper which base on the blade model is using modern control systems theory to design a close-loop system to solve an unstable system.After the project was started, new goals were established for the project. The analysis was going to performed only on the hover conditions for the blade. But in the future work, that would be focused on the perform of the forward flight and design of a more stable system controller of the blade under a unstable situation.