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过失速机动是现代先进战斗机的重要特征。飞机在大迎角过失速机动飞行时,会产生强烈的运动耦合、惯性耦合等复杂的非线性特性,传统的建模和控制方法都难以准确预测和全面掌握飞机的耦合特性。该文以非线性系统的分支分析和突变理论及相应的数值计算方法为工具,重点对现代先进战斗机急滚机动飞行时的惯性耦合现象和大迎角俯仰运动时的耦合现象进行了特性分析研究,有效全面地揭示了飞机的非线性动力学全局特性以及耦合动力学特性,预测了耦合现象给飞机带来的不利影响,并通过时域仿真验证了该方法的有效性,从而为控制律设计、改善飞机的飞行品质打下基础。
Stall movement is an important feature of modern advanced fighter aircraft. When the aircraft maneuvers at a high angle of attack over a stall, it will produce complex nonlinear characteristics such as kinematic coupling and inertial coupling. The traditional modeling and control methods are difficult to accurately predict and fully grasp the coupling characteristics of the aircraft. Based on the branch analysis and catastrophe theory of nonlinear system and the corresponding numerical calculation method, this paper focuses on the analysis of the characteristics of the coupling phenomena of maneuvering flight of modern advanced fighter aircraft in maneuvering flight and the pitch motion in high angle of attack , The overall and nonlinear dynamic dynamics and the coupling dynamics of the aircraft were revealed effectively and comprehensively. The adverse effects of the coupling phenomena on the aircraft were predicted. The effectiveness of the proposed method was verified by time-domain simulation to design the control law , To improve the aircraft’s flight quality and lay the foundation.