摘要
以先进推力矢量战斗机为背景,构建了基于力矩解算和分配的大迎角综合飞行/推进控制系统结构方案.在此基础上采用模糊方法设计推进稳定性控制系统;以逆动力学方法计算期望力矩;以饱和控制分配原则协调气动舵面和推力矢量的控制.仿真结果表明大迎角下推进系统可稳定工作,综合飞/推控制系统能合理协调气动舵面和推力矢量,控制系统能够快速准确的跟踪指令,完成机动动作.
Research on simulation and design of IFPC （integrated flight and propulsion control system ） of super angle of attack maneuver were done for an advanced vectored-thrust aircraft. A new structure of IFPC was put forward. An engine stability control system was designed to enhance engine stability at super angle. Moment requirements were calculated by rigid body inverse dynamic method, and the aerodynamic surfaces and thrust vector were allocated by the optimal control allocation and the saturation principle. Simulation resuits show that engine operates steadily, and thrust vector supplies extra moment, when the aerodynamic surfaces moment is not enough. The dynamic response of system is rapid, and tracking characteristic is well.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
2007年第6期709-713,共5页
Journal of Beijing University of Aeronautics and Astronautics
基金
国防十五预研资助项目(102010106)
关键词
综合飞行/推进控制
控制分配
推进系统稳定性控制
integrated flight and propulsion control
control allocation
engine stability control
