飞机平衡状态的优化计算方法

分析了飞机定常飞行时平衡状态的基本特性，提出一种平衡状态及平衡面的优化计算方法，并以F－16飞机为模型，对其常规飞行时的平衡状态参数在推力矢量控制下迎角定常飞行时的平衡面进行了计算。仿真结果表明，该方法具有较好的收敛性、稳定性，在飞机定常飞行的配平计算、用分支突变理论分析大迎角非线性特性时平衡面的计算以及推力矢量控制的分析计算中，有广泛的应用价值。

An optimal algorithm of calculating the equilibrium states of aircraft

This paper studies the characteristics of equilibrium states in the steady flight of an aircraft,and presents an optimal algorithm of determining the equilibrium states and equilibrium surface.Taking the fighter F 16 as an example,it calculates the values of equilibrium variables in conventional flight and the equilibrium surface in high angle of attack flight with thrust vectoring control.The result shows that the algorithm has good convergency and steadiness,and that it is useful not only in the calculating of trimming values of state variables in the conventional steady flight, but also in the calculating of equilibrium surface while the nonlinear characteristics of fighter aircraft at high angle of attack is studied by BACTM methods and in the analyzing of thrust vectoring control.