| Citation: | Qian Qiumeng, Zhai Chao, Zhang Hehong, et al. Multi-variable active disturbance rejection decoupling control between temperature and pressure for flight environment simulation system[J]. Journal of Aerospace Power, 2026, 41（7）：20240472 doi: 10.13224/j.cnki.jasp.20240472
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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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