| 航空发动机过渡态试验进气压力线性自抗扰控制方法 |
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| 引用本文： | 钱秋朦,但志宏,张松,裴希同,王信.航空发动机过渡态试验进气压力线性自抗扰控制方法[J].航空动力学报,2019,34(10):2271-2279. |
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| 作者姓名： | 钱秋朦 但志宏 张松 裴希同 王信 |
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| 作者单位： | 中国航空发动机集团有限公司四川燃气涡轮研究院,四川绵阳,621000;中国航空发动机集团有限公司四川燃气涡轮研究院,四川绵阳621000;中国航空发动机集团有限公司四川燃气涡轮研究院高空模拟技术重点实验室,四川绵阳621000 |
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| 基金项目： | 中国航发四川燃气涡轮研究院科研基金(SHYS-2019-0004) |
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| 摘 要： | 航空发动机高空模拟试车台过渡态试验中进气控制系统受扰严重,常规方法难以有效提升进气压力控制品质,提出了一种基于线性自抗扰的进气压力控制方法。采用机理建模和系统辨识手段搭建高置信度进气仿真平台,设计线性自抗扰控制器,实现对发动机扰动影响的实时预估和补偿,形成具有主动抗扰机制的进气压力控制方法。考虑实际使用中存在控制器手/自动及控制器间的切换问题,设计实用型无扰切换方法。仿真环境下,将该方法与比例积分微分(PID)进行对比,结果显示进气压力最大偏离值由7.69kPa缩小至0.9kPa,且能够快速收敛趋于稳定,表明了该方法无需发动机信息即可实现进气压力的有效控制,通用性高,抗扰性优,能够大幅提升发动机过渡态试验中进气系统的调节品质。
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| 关 键 词： | 高空模拟试车台 进气控制系统 过渡态试验 线性自抗扰 无扰切换 |
| 收稿时间： | 2019/1/19 0:00:00 |
Linear active disturbance rejection control method for intake pressure control in aero-engine transient test |
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| QIAN Qiumeng,DAN Zhihong and ZHANG Song.Linear active disturbance rejection control method for intake pressure control in aero-engine transient test[J].Journal of Aerospace Power,2019,34(10):2271-2279. |
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| Authors: | QIAN Qiumeng DAN Zhihong and ZHANG Song |
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| Affiliation: | 1.Sichuan Gas Turbine Establishment,Aero Engine Corporation of China,Mianyang Sichuan 621000,China2.Science and Technology on Altitude Simulation Laboratory,Sichuan Gas Turbine Establishment,Aero Engine Corporation of China,Mianyang Sichuan 621000,China3.Science and Technology on Altitude Simulation Laboratory,Sichuan Gas Turbine Establishment,Aero Engine Corporation of China,Mianyang Sichuan 621001,China |
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| Abstract: | When aero-engine received transient test in altitude test facility, the intake control system was abnormally affected and the quality of intake pressure control couldn’t be improved by conventional control methods, so an intake pressure control method based on linear active disturbance rejection was proposed. The high-intensity intake control system simulation platform was built through mechanism simulation and system identification, and the linear active disturbance rejection law was designed to estimate and compensate engine disturbance in real-time manner. An intake pressure control method with active rejection mechanism was formed. Meanwhile, considering the switching problem between manual and automatic control or between different control laws in actual use, an practical bumpless transfer method was designed. Simulation results compared with PID showed that the intake pressure can be quickly converged and stabilized, meanwhile, the maximum deviation was reduced from 7.69kPa to 0.9kPa. So this method achieves good control effect without engine information and can greatly improve intake pressure control quality in transient test. |
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| Keywords: | altitude test facility intake control system transient test linear active disturbance rejection bumpless transfer |
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