高空台飞行环境模拟系统温度延时不确定性μ综合设计

doi:10.13675/j.cnki.tjjs.190553

推进技术 ›› 2020, Vol. 41 ›› Issue (8): 1861-1870.DOI: 10.13675/j.cnki.tjjs.190553

高空台飞行环境模拟系统温度延时不确定性μ综合设计

朱美印^1,2，王曦^1,2，裴希同³，张松³，但志宏³，刘佳帅^1,2，缪柯强^1,2，姜震^1,2

1.北京航空航天大学能源与动力工程学院，北京 100191;2.先进航空发动机协同创新中心，北京 100191;3.中国航发四川燃气涡轮研究院高空模拟技术重点实验室，四川绵阳 621703

发布日期:2021-08-15
作者简介:朱美印，博士生，研究领域为航空发动机控制、高空台数字仿真平台研究以及鲁棒控制等。E-mail：mecalzmy@163.com

Temperature Delay Uncertainty μ Synthesis for Flight Environment Simulation System of Altitude Ground Test Facilities

1.School of Energy and Power Engineering,Beihang University,Beijing 100191,China;2.Collaborative Innovation Center for Advanced Aero-Engine,Beijing 100191,China;3.Science and Technology on Altitude Simulation Laboratory,AECC Sichuan Gas Turbine Establishment，Mianyang 621703,China

Published:2021-08-15

摘要/Abstract

摘要： 针对高空台飞行环境模拟系统温度大延时特性的控制问题，提出了一种考虑温度延时不确定性的两自由度μ综合控制设计方法以提升其温度的控制精度。在考虑变比热容腔微分方程、管壁传热、调节阀流量特性、液压伺服动态、传感器增益以及温度延迟对飞行环境模拟系统造成的建模不确定性的基础上，建立了完整、准确的非线性延时模型。在考虑执行机构参数、温度延时不确定性的基础上，提出了两自由度的μ综合控制设计方法。为了确保设计的控制器具有良好鲁棒伺服跟踪性能，基于分频设计的思想设计性能加权函数和控制量加权函数，并运用D-K迭代算法设计控制器。假定了包含“等马赫数爬升”和“平飞加速”的试验过程来验证μ综合控制器的伺服跟踪性能，仿真结果表明，飞行环境模拟系统温度和压力的稳态和动态误差分别均不大于1.5%和3%。

关键词: 高空模拟试验台;飞行环境模拟系统;温度延时;鲁棒控制;两自由度μ综合控制

Abstract: Aiming at the control problem of large temperature delay of flight environment simulation system (FESS) of altitude ground test facilities (AGTF), a two degree-of-freedom μ synthesis control design method considering temperature delay uncertainty is proposed. A complete and accurate nonlinear model of FESS is established. The FESS modeling uncertainties caused by variable specific heat volume differential equation, pipe heat transfer, control valve flow characteristics, hydraulic servo system dynamics, sensor gain, and temperature delay are considered in this model. By considering the actuator parameter and temperature delay uncertainty of FESS, a two degree-of-freedom μ synthesis control design method is presented. To ensure the designed μ synthesis controller has good robust servo tracking performance, the performance and control output weighting functions are designed according to the frequency division weighting principle. The μ synthesis controller is designed by using the D-K iteration method. A typical engine test condition with Zoom-Climb and Mach Dash is supposed to verify the servo tracking performance of the designed μ synthesis controller. The simulation results show that the relative steady-state and transient errors of temperature and pressure of FESS are both less than 1.5% and 3%， respectively.

Key words: Altitude ground test facilities;Flight environment simulation system;Temperature delay;Robust control;Two-degree-of-freedom μ synthesis control

朱美印，王曦，裴希同，张松，但志宏，刘佳帅，缪柯强，姜震. 高空台飞行环境模拟系统温度延时不确定性μ综合设计[J]. 推进技术, 2020, 41(8): 1861-1870.

ZHU Mei-yin^1,2, WANG Xi^1,2, PEI Xi-tong³, ZHANG Song³, DAN Zhi-hong³, LIU Jia-shuai^1,2, MIAO Ke-qiang^1,2, JIANG Zhen^1,2. Temperature Delay Uncertainty μ Synthesis for Flight Environment Simulation System of Altitude Ground Test Facilities[J]. Journal of Propulsion Technology, 2020, 41(8): 1861-1870.

参考文献

[1] 侯敏杰. 高空模拟试验技术[M]. 北京:航空工业出版社, 2014: 1-60.
[2] 王曦, 朱美印, 张松, 等. 国外高空模拟试车台控制系统技术发展[J]. 燃气涡轮试验与研究, 2017, 30(6): 49-55.
[3] Davis M, Montgomery P. A Flight Simulation Vision for Aero-Propulsion Altitude Ground Test Facilities[J]. Journal of Engineering for Gas Turbines & Power, 2005, 127(1): 21-31.
[4] Krupp, Brian E. Heat Transfer Analysis of AEDC Test Cell J-2 Inlet Ducting Using a Lumped-Parameter Mathematical Model [D]. Tennessee: University of Tennessee, 1998.
[5] Ebrahimi H, Ryder R. CFD Simulations for AEDC Combustion Air Heater (CAH) for APTU Facility[R]. AIAA 2006-8046.
[6] Montgomery P, Burdette R, Klepper J, et al. Evolution of a Turbine Engine Test Facility to Meet the Test Needs of Future Aircraft Systems [R]. ASME GT 2002-30605.
[7] Montgomery P A, Burdette R, Wilhite L, et al. Modernization of a Turbine Engine Test Facility Utilizing a Real-Time Facility Model and Simulation[R]. ASME GT 2001-0573.
[8] Riegler C. Modulares Leistungsberechnungsverfahren für Turboflugtriebwerke mit Kennfelddarstellung für W?rm-eübertragungsvorg?nge[D]. Stuttgart: Institut für Luftfahrtantriebe, 1997.
[9] Borairi M, Every D V. Design and Commissioning of a Multivariable Control System for a Gas Turbine Engine Test Facility[R]. AIAA 2006-3151.
[10] Zhu M, Wang X. An Integral Type μ Synthesis Method for Temperature and Pressure Control of Flight Environment Simulation Volume[R]. ASME GT 2017-63529.
[11] 朱美印, 王曦, 张松, 等. 基于LMI极点配置的高空台飞行环境模拟系统PI增益调度控制研究[J]. 推进技术, 2019, 40(11).
[12] Cengel Y A. Heat Transfer: A Practical Approach, 2nd Ed [M]. New York： McGraw-Hill College, 2002.
[13] 朱美印, 王曦, 但志宏, 等. 高空台进气控制系统压力PI增益调度控制研究[J]. 推进技术, 2019, 40(4): 902-910.
[14] 朱美印, 裴希同, 张松, 等. 一种轮盘式特种调节阀流量特性的修正算法[J]. 燃气涡轮试验与研究, 2016, 29(5): 40-45.
[15] 裴希同, 朱美印, 张松, 等. 一种特种阀流量特性计算的经验公式迭代方法[J]. 燃气涡轮试验与研究, 2016, 29(5): 35-39.
[16] 朱美印, 张松, 但志宏, 等. 一种大口径蝶阀流量特性的坐标定位回归算法[J]. 燃气涡轮试验与研究, 2017, 30(4): 39-44.
[17] 朱美印, 张松, 但志宏, 等. 高空台飞行环境模拟腔μ综合控制设计[J]. 航空动力学报, 2017, 32(12): 3039-3048.
[18] 张松, 朱美印, 但志宏, 等. 飞行环境模拟腔积分型μ综合控制[J]. 推进技术, 2018, 39(3): 660-666.
[19] Zhu M, Wang X. Two Degree-of-Freedom μ Synthesis Control with Kalman Fliter for Flight Environment Simulation Volume with Sensors Uncertainty[R]. ASME GT 2019-90116.
[20] Zhu M, Wang X, Dan Z, et al. Two Freedom Linear Parameter Varying μ Synthesis Control for Flight Environment Testbed[J]. Chinese Journal of Aeronautics, 2019, 32(5): 1204-1214.
[21] Gu D W, Petkov P H, Konstantinov M M. Robust Control Design with MATLAB[M]. Glasgow: Springer, 2005.

高空台飞行环境模拟系统温度延时不确定性μ综合设计

Temperature Delay Uncertainty μ Synthesis for Flight Environment Simulation System of Altitude Ground Test Facilities

PDF

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 0

编辑推荐

Metrics

本文评价