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Analysis of Stability and Control of Helicopter Flight Dynamics Through Mathematical Modeling in Matlab

机译：通过Matlab中的数学建模分析直升机飞行动力学的稳定性与控制。

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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.
机译：本文介绍了直升机飞行动力学的数学模型。直升机是非线性系统。通常，直升飞机被认为比固定翼飞机更加不稳定，并且需要一种恒定的控制策略来应对固有的不稳定性。因此，使用适当的控制技术来确保稳定性是当务之急。为了解决这些问题，数学建模开始于用小扰动理论线性化平移和旋转方程。为简化起见，已作了一些假设。本文忽略了纵向和横向的耦合效应以及尾桨。使用提及的方程式从MATLAB©获得了仿真结果，并结合了以前发布的直升机文献中的现有数据。然后通过使用三种不同型号的直升机估算结果来进行比较分析。线性二次调节器控制也可用于提高飞行动力学的稳定性。从特征值，稳定性导数和时间响应结果来看，稳定性的仿真结果令人满意。

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