超声速状态下航空发动机部件蜕化参数估计与性能恢复控制

发布时间：2018-03-22 02:33

  本文选题：超声速　切入点：参数估计　出处：《南京航空航天大学学报》2016年03期 　论文类型：期刊论文

【摘要】：为解决超声速状态下航空发动机部件蜕化参数估计与性能恢复控制的难题,基于改进卡尔曼滤波器,通过一种三维插值方法实现超声速状态包线范围内的发动机部件蜕化参数估计。而航空发动机性能恢复控制是在常规内环控制转速的基础上增加了外环控制回路,该回路主要包括推力估计模型与外环控制器两部分。基于最小二乘支持向量回归机设计了一种推力估计模型,其输入采用特征选择算法筛选推力估计模型的最优输入,相比于传统的不经选择的推力估计模型,精度有较大提高。设计了外环模糊PI(Proportional-integral)控制器自适应调节内环转速指令来实现蜕化发动机性能恢复的目的。最后通过超声速状态下的数字仿真,验证了上述发动机部件蜕化参数估计与性能恢复控制方案的有效性。
[Abstract]:In order to solve the problems of parameter estimation and performance recovery control of aero-engine components under supersonic condition, an improved Kalman filter is proposed. A three-dimensional interpolation method is used to estimate the degradation parameters of engine components in the range of supersonic state envelope. The performance recovery control of aeroengine is based on the conventional inner loop to control the speed of the engine, and the outer loop control loop is added to the control loop. The loop consists of two parts: thrust estimation model and outer loop controller. Based on least squares support vector regression machine, a thrust estimation model is designed, and its input adopts feature selection algorithm to filter the optimal input of thrust estimation model. Compared with the traditional unselected thrust estimation model, The precision is greatly improved. An outer loop fuzzy PIPIProportional-integralcontroller is designed to adaptively adjust the internal ring speed instruction to achieve the purpose of performance recovery of the degenerated engine. Finally, the digital simulation under supersonic condition is carried out. The effectiveness of the proposed scheme for estimating the degradation parameters of the engine components and the performance recovery control scheme is verified.
【作者单位】： 中航工业西安航空计算技术研究所;南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室;
【分类号】：V232
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本文编号：1646703