Abstract
This paper presents the mathematical model of helicopter flight dynamics. Helicopters are nonlinear systems. Generally, helicopters are considered to be more unstable than fixed wing aircraft and require a constant control strategy to counter the inherent instability. As a result, ensuring stability with proper control technique is the highest concern. In order to address these issues, the mathematical modeling begins by linearizing the translational and rotational equations with small perturbation theory. For simplification, some assumptions have been made. In this paper, the longitudinal and lateral coupling effect and tail rotor are neglected. Simulation results have been acquired from MATLAB© using the mentioned equations coupled with existing data available from previous published literatures of helicopter. A comparative analysis is then presented by estimating the results with three different models of helicopters. Also Linear Quadratic Regulator control is applied to improve the stability of the flight dynamics. The simulation results for the stability found satisfactory from the eigenvalue, stability derivatives and time response result.
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