基于分支分析与突变理论的耦合动力学  

Coupling dynamics of aircraft using bifurcation analyses and catastrophe theory

作　　者：尹航[1,2] 朱纪洪[1] 张旭东 周池军[1] 

机构地区：[1]清华大学计算机科学与技术系,北京100084 [2]北京航空科技研究中心,北京100076

出　　处：《清华大学学报（自然科学版）》2015年第2期237-242,共6页Journal of Tsinghua University(Science and Technology)

基　　金：国家自然科学基金青年基金资助项目(61104082)

摘　　要：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 maneuver is the main characteristic of modern advanced aircraft. Their enhanced maneuver ability and agility are based on the much more complicated nonlinear dynamic flight characteristics at high angles of attack due to the aerodynamic nonlinearities and kinematic and inertial coupling. Traditional modeling and control methods cannot accurately predict the coupling characteristics of these airplanes. A bifurcation analysis and catastrophe theory methodology was used to study the coupling of the elevator control and the aircraft inertia during fast rolling. The global aircraft dynamic stability and the nonlinear coupling dynamics during maneuver were studied to understand the nonlinear jump and spin caused by inertia coupling. Numeric simulations verify the methodology as a foundation for control law to improve aircraft flying characteristics.

关 键 词：非线性飞行力学 耦合动力学 分支分析与突变理论方法 稳定性 

分 类 号：V249[航空宇航科学与技术—飞行器设计] TP273[自动化与计算机技术—检测技术与自动化装置]