摘要
现有战斗机座舱压力控制系统存在机械结构惯性大,控制精度低及弹性部件易疲劳等问题。针对以上问题,考虑战斗机高速、小舱容的特点,结合气动式与数字式的优点,对电子气动式压力控制系统展开研究。建立了系统各部件的数学模型,通过对被控对象的数学描述,克服了参数辨识的问题。针对系统的时变、非线性特点,在平衡状态进行零极点配置设计了校正装置;飞行剖面内实施增益调度,完成控制算法的设计。数值仿真结果表明该方法能够实现快速无超调调压,具有较好的控制效果。对于压调系统,该方法可以化为PID形式,所以具有鲁棒性强的优点;相比单纯PID控制,不依赖调试者经验,具有较为严格的推导证明,具有一定的理论意义和实践价值。
There exsit some problems for the present cabin pressure control system for fighter aircraft. For example, the mechanical inertia is large, response time is long and control precision is poor, also, the diaphragm is easily to fatigue. Based on the above issues, considering the high-speed and small tank capacity of fighter, combining the advantage of pneumatic and digital, the research on electronic pneumatic pressure control system was expanded. The mathematical model of the system components was established and problem of parameter identification was overcome on account of the mathematical description of the controlled object. In view of the trait of time-varying and nonlinear of system, the pole-zero configuration was carried out in a state of equilibrium. The correction device was designed, gain scheduling was carried out within the flight profile and the design of control algorithm was finished. The numerical simulation results show that this method can achieve the fast nonovershooting regulator and its control effect is good. For cabin pressure control system, this method can be transformed to PID form, which has strong robustness,＂ Compared with pure PID control method, this method is independent of debugging personnel experience and possesses strict derivation, theoretical significance and practical value.
出处
《系统仿真学报》
CAS
CSCD
北大核心
2014年第3期720-725,共6页
Journal of System Simulation
关键词
座舱压力
电子气动
零极点配置
增益调度
频带宽度
cabin pressure
electronic pneumatic
pole-zero configuration
gain scheduling
band width
