过失速机动飞机内回路鲁棒解耦控制  

Robust decoupling inner-loop control for apost-stall maneuverable fighter

作　　者：周池军[1,2] 朱纪洪[1] 雷虎民[2] 袁夏明[1] 尹航[1] 

机构地区：[1]清华大学计算科学与技术系,北京100084 [2]空军工程大学防空反导学院,西安710051

出　　处：《清华大学学报（自然科学版）》2015年第11期1197-1207,共11页Journal of Tsinghua University(Science and Technology)

基　　金：国家自然科学基金青年项目(61104082)

摘　　要：针对过失速机动存在的非线性和强耦合问题,提出了一种内回路鲁棒解耦控制方法。控制器设计分为力矩补偿、线性控制和鲁棒补偿这3部分:首先通过查询气动数据库对阻尼力矩以外的气动力矩、惯性耦合力矩及推力附加力矩进行实时补偿;然后利用参考模型对补偿后的线性参数系统设计比例积分控制器;在此基础上采用正弦函数表征气动力矩系数和推力参数摄动,推导了模型不确定性的解析表达式,并采用滑模控制方法进行鲁棒补偿器设计。仿真结果表明:保留阻尼项的设计方案可以有效降低控制能量消耗;所设计的控制器具有较强的鲁棒性,在气动系数和控制系数的最大幅值摄动分别为60%和20%的情况下,仍然能够稳定跟踪参考指令并实现Herbst机动。A robust decoupling control approach was developed for a strongly nonlinear and strongly coupled inner-loop system for post-stall maneuvers. The control process includes moment compensation, linear controller design and robust compensation. The aerodynamic moment, inertial coupling moment and additional moment caused by the thrust vector are first compensated through querying an aerodynamic database with the damping moment not included. A second-order reference model is then employed to determine the proportional and integral coefficients of the linear controller. A series of aerodynamic moment derivatives and thrust force parameter perturbations are then described by sine functions to get an analytical expression for the model uncertainty and a robust compensator based on the sliding mode control methodology.Simulations show that the energy consumption can be reduced when the aerodynamic damping moment is not included. Moreover, the Herhst maneuver and robust command tracking can be achieved, even with 60% parameter perturbations in the aerodynamic derivatives and 20% perturbations with the control derivatives.

关 键 词：过失速机动 阻尼力矩 参考模型 参数摄动 鲁棒补偿 Herbst机动 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]