摘要
航空发动机尾喷管喉部面积控制系统是实现航空发动机能量转化的重要部件,但其工作过程较为复杂,且具有强非线性特性,直接建立精确可靠的系统数学模型具有很大困难。针对上述问题,依据控制系统主要部件的工作机理、大量的设计数据和试车数据,提出了一种尾喷管喉部面积控制系统的建模仿真方法。仿真结果表明,所建立的数学模型可较为精确地模拟尾喷管喉部面积控制系统的工作过程,各项参数变化符合其工作原理,所设计的控制系统能顺利完成发动机尾喷管喉部面积的精确控制,所建数学模型具有较高的置信度。所提出的建模仿真方法可为相关产品的调试及改进提供有益的参考。
Aero engine nozzle throat area control system is an important component to achieve energy conversion of the aero engine, but its work process is more complicated and has a strong nonlinear characteristic, it is very difficult to establish the system mathematical model directly. Aiming at this problem, a simulation method of the nozzle throat area control system is presented in this paper in accordance with the working mechanism of the main components of this control system and a lot of design data and test data. Simulation results show that, the working process of the aero engine nozzle throat area control system can be accurately simulated by the mathematical model established, the parameters change in line with its operating principle, and the precise control of the engine nozzle throat area can be successfully completed by the designed control system, and the mathematical model has enough credita- bility. The presented simulation method can provide a meaningful reference for the debugging and the improvement of the related products.
出处
《计算机仿真》
CSCD
北大核心
2014年第6期111-114,206,共5页
Computer Simulation
基金
中央高校基本科研业务费专项资金资助项目(2013G1321039)
