摘要
对保持飞行速度恒定及保持飞行迎角恒定两种自动动力补偿系统 (Approach powercompensator system,APCS)所构成的飞行 /推力综合控制进行了评估。在此基础上 ,提出了APCS采用控制规则在线自调整及非线性参数优化的模糊逻辑控制。其设计思想是 ,从工程实现考虑 ,在油门控制律中省去法向加速度 Δaz及舵偏 Δδe两路反馈信息。仅根据迎角误差 Δα及其变化率 Δα的大小 ,在线地自调整加权因子 ,以提高稳态控制精度 ,消除由于量化误差而引起的稳态振荡。利用非线性优化控制算法 ,对 APCS模糊控制器参数进行优化设计 ,进一步改善了当代迎角恒定的飞行 /推力综合控制性能 。
Two approach power compensator systems are evaluated and the simulation results of W γ θ(S) step reponse compared under several situations. On the basis of above, a fuzzy logic control system with self regulating control rules and nonlinear parameter optimization is proposed so as to improve the performances of modern integrated flight/thrust control system with constant attack angle. Considering the easy realization in engineering, the main idea of this method is that the normal acceleration signal Δ a z and the elevator deviation signal Δ δ e are erased from the throttle control law. It adopts analytic control rules, and presents a fuzzy number model of correction factor. According to the errors of attack angle Δ α and its derivative Δ , the fuzzy control rules can regulate themselves online so as to improve the static accuracy and to eliminate the oscillation due to the qualified errors. By optimizing the facors of the fuzzy controller, optimization toolbox and nonlinear control design blockset in Matlab5.1 are used to design the parameters under certain goal functions. The simulation results indicate that the fuzzy logic based APCS with constant angle of attack has better tracking response performance, and easy to be implemented because of saving two feedback loops.
出处
《南京航空航天大学学报》
EI
CAS
CSCD
北大核心
2000年第1期43-46,共4页
Journal of Nanjing University of Aeronautics & Astronautics
基金
高等院校博士学科点专项科研基金! (编号 :980 2 870 3)
国防科研 37.2 .1专项资助项目
关键词
模糊逻辑
ACS
飞行/推力
综合控制
轨迹控制
fuzzy logic
self regulating on line
nonlinear parameter optimization
integrated flight/thrust control
carrier landing
