This paper presents an approach to the direct lift control characteristics on the joined wing configuration. 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。
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。
The main steps of how to use the eigenstructure assignment and model following technique to calculate the feedback and feedforward gain are explained. By using aircraft Citation ⅱ as an example, the direct lift control law is designed. 在简述了用特征结构配置和模型跟踪技术求算反馈和前馈增益阵的主要步骤之后,以CitationⅡ型飞机为算例,设计了其直接升力控制律。
The application of maneuver flaps in direct lift control of aircraft 机动襟翼在实现直接升力控制中的应用研究
The three principal motion of direct lift control are discussed first, and the direct lift control law design which is a problem of output decoupling is summed up. 文中首先对飞机直接升力控制的3种基本运动模式进行了讨论。归纳出直接升力控制律的设计就是输出解耦控制系统的设计问题。