for improving lateral direct lift control system of aircraft, we improve dynamic inversion method through combining it with fuzzy control method with correction factors.
用该综合方法对某飞机侧向直接力控制系统进行了设计,并与动态逆方法进行了比较,提供了鲁棒性验证与仿真比较结果。
according to the characters of dynamic inversion method in making multivariable control system decoupling, we design a set of control law for every direct lift control mode.
本文针对动态逆控制方法的不足之处提出了相应的改善措施,并取得了较为理想的效果。
the basic modes of direct lift control are analyzed in this paper.
本文对联接翼气动布局的直接升力控制特性进行了初步的探索。