摘要
吸气式高超声速飞行器飞行过程中舵偏不能过大,攻角、角速率等飞行状态必须满足约束,这既是超燃冲压发动机工作条件的要求,也是为了减小飞行器状态散布。针对吸气式高超声速飞行器进行高度控制时,飞行器状态和舵偏必须满足约束的实际问题,引入指令调节器进行高度回路设计。基于PI+LQ方法设计过载控制器,利用高度回路的比例-微分产生过载信号,过载信号经过指令调节器生成调节指令,过载控制器跟踪该指令完成高度跟踪。仿真结果表明,该方法设计的控制系统在阵风干扰情况下能够满足状态约束并实现快速跟踪。
An air-breathing hypersonic flight vehicle requires that its elevator deflection should not be too large and that such flight states as angle of attack and angular velocity must satisfy certain constraints to meet the working conditions of scramjet engine and to reduce the state diffusion of the flight vehicle. Therefore,we proposed the abovementioned control method based on the model predictive control principles and designed two separate controllers： a traditional linear controller that guarantees the tracking of the altitude of the hypersonic flight vehicle in the absence of constraints and a command governor,a nonlinear static device that must modify the reference signals of normal acceleration to meet the constraints imposed by actuators and flight vehicle. The simulation results show that under the interference of gust,our method can effectively fast track maneuver commands,control the altitude of the hypersonic flight vehicle and satisfy its elevator deflection and flight state constraints.
作者
杜昊昱
凡永华
闫杰
Du Haoyu Fan Yonghua Yan Jie(School of Astronautics, Northwestern Polytechnical University, Xi＇an 710072, China)
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
2016年第6期945-950,共6页
Journal of Northwestern Polytechnical University
基金
国家自然科学基金(91216104)资助
关键词
指令调节器
状态约束
受限控制
模型预测控制
最优控制
angle of attack
angular velocity
flight control systems
hypersonic flight vehicles
maneuverability
altitude control
command governor
constrained control
model predictive control
state constraints
