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大型飞机座舱温度控制系统具有温度控制非线性、强耦合、大迟滞性等特点,对控制律设计提出很高要求。根据系统设计要求,结合执行机构动作特性,提出了一种新型的座舱温度控制律。系统控制方案采用压气机出口温度控制、组件出口温度控制、座舱供气温度控制和座舱区域温度控制四级控制;压气机出口温度目标值根据大气环境温度确定,座舱供气温度目标值根据座舱区域温度控制误差确定,组件出口温度目标值根据座舱供气温度目标值中的最小值确定;使用专家比例一积分一微分(PID)控制方法设计各级温度控制器,温度控制器的设计融入了解耦控制算法和系统保护控制逻辑,控制周期由各级温度控制响应特性确定。系统地面试验与飞行试验结果显示,该座舱温度控制系统响应速度快,抗干扰能力强,控制精度高,满足系统设计要求。
Large aircraft cockpit temperature control system has the characteristics of non-linear temperature control, strong coupling, large hysteresis, etc., and puts forward very high requirements on the control law design. According to the system design requirements, combined with the actuator operating characteristics, a new cockpit temperature control law is proposed. The system control scheme adopts four levels of compressor outlet temperature control, component outlet temperature control, cockpit air supply temperature control and cockpit area temperature control. The target value of compressor outlet temperature is determined according to the atmospheric environment temperature. The target value of cockpit air supply temperature is determined according to the cabin area Temperature control error is determined, the target value of the outlet temperature of the module is determined according to the minimum value of the target temperature of the air supply in the cockpit; the design of the temperature controller and the temperature controller is designed by using the proportional-integral-derivative (PID) Coupling control algorithm and system protection control logic, the control cycle is determined by the temperature control response characteristics at all levels. System ground test and flight test results show that the cabin temperature control system has fast response, strong anti-interference ability and high control precision to meet the system design requirements.