Multi-variable active disturbance rejection decoupling control between temperature and pressure for flight environment simulation system
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摘要:
高空台飞行环境参数的准确模拟对开展发动机性能测试与评价至关重要，然而发动机过渡态试验中进气环境压力与温度控制变量间的强耦合性制约了环境参数的综合控制品质，同时考虑到过渡态试验任务中的强扰动特性，通过改进扩张状态观测器得到新型自抗扰控制（ADRC）算法，并将其成功应用到进气环境模拟系统的温压解耦控制中。推导出进气环境模拟系统压力和温度回路的仿射模型并进行自抗扰解耦设计，对解耦设计中输入矩阵的可逆性问题进行了深入分析，针对逆矩阵的病态性与不可逆性提出了对应的解决方案。针对高增益线性扩张状态观测器（LESO）对状态与扰动估计存在的抖振现象，设计了误差反馈函数（qsat）得到新型QSAT-ESO算法，基于劳斯判据证明了所设计ESO的稳定性，得到基于QSAT-ESO的ADRC解耦控制方法（QSAT-ADRC）。最后，搭建飞行环境模拟系统仿真平台开展了发动机过渡态试验，对比了所提出的QSAT-ADRC与LADRC的解耦控制方法。结果显示：在规划的过渡态飞行任务剖面下，基于QSAT-ADRC方法控制下的进气压力和温度的绝对积分误差比LADRC方法分别减少63%和88%，同时充分抑制了阀门摆动，有效提升了发动机过渡态飞行任务模拟试验中进气压力与温度的综合控制品质，为提升发动机性能测试与评价的准确性奠定坚实的基础。
Abstract:The accurate simulation of flight environment parameters is of high importance for testing and evaluating an engine. The strong coupling between the inlet ambient pressure and the temperature during the aero-engine transient tests, however, significantly restricts the effective simulation and tunning of flight environment parameters. Simultaneously, considering the strong perturbation in the transient test tasks, an active disturbance rejection control algorithm via the new extended state observer was proposed, and then was successfully applied to the decoupling control in the intake environment simulation system. Based on the intake environment simulation system, the affine model derivation of system’s pressure and temperature loops was built, and the decoupling design was conducted. Meanwhile, the reversibility of the input matrix in decoupling design was deeply analyzed, and corresponding solutions were proposed for the ill-conditioned issue and irreversibility of the inverse matrix. To tackle the chattering phenomenon of state and disturbance estimation in high-gain linear extended state observer (LESO), an error feedback function (qsat) was proposed to design the QSAT extended state observer algorithm (QSAT-ESO) whose stability was proved by Routh criterion, and QSAT-ADRC decoupling control scheme based on QSAT-ESO was presented. With the construction of the intake environment simulation system simulation platform, aero-engine transient tests were carried out, and the comparisons between the QSAT-ADRC and the LADRC decoupling control method were performed. The results showed that, under the planned transient flight mission profile, the absolute integration errors of intake pressure and temperature based on the proposed QSAT-ADRC were reduced by approximately 63% and 88%, respectively, meanwhile the control valve swing was reduced. The proposed control scheme has improved the comprehensive control quality of intake pressure and temperature, and layed a solid foundation for improving the accuracy of aero-engine performance testing and evaluation.
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图 3 自抗扰温压解耦控制结构框图
Figure 3. Active disturbance rejection temperature and pressure decoupling control structure block diagram
图 6 等马赫数下降温压解耦控制
Figure 6. Temperature and pressure decoupling control under the same Mach number descending
图 7 等马赫数爬升温压解耦控制
Figure 7. Temperature and pressure decoupling control under the same Mach number climbing
表 1 进气压力与温度总误差
Table 1. Intake pressure and temperature total error
控制方法 进气压力总误差/Pa 进气温度总误差/K PID 14450 9.56 LESO 2392 2.78 QSAT-ADRC 871.4 0.32 
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表 2 90～125 s进气压力与温度总误差
Table 2. 90—125 s intake pressure and temperature total error
控制方法 进气压力
误差/Pa进气温度
误差/KPID 8017 6.18 LESO 893.1 1.564 QSAT-ADRC 429.1 0.13
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表 3 阀门摆动量
Table 3. Valve swing
控制方法 814阀门摆动量/% 815阀门摆动量/% PID 1075 1057 LESO 41.14 37.59 QSAT-ADRC 39.89 32.92
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