一种分离加速度变量的直升机动力学仿真方法  

A Method for Helicopter Dynamic Simulation Based on Separating Acceleration Variable

作　　者：吴靖 刘湘一 宋山松 WU Jing;LIU Xiang-yi;SONG Shan-song(School of Basic Science for Aviation,Navy Aviation University,Yantai Shandong 264001,China)

机构地区：[1]海军航空大学航空基础学院,山东烟台264001

出　　处：《计算机仿真》2023年第8期78-81,共4页Computer Simulation

摘　　要：针对直升机旋翼/机体耦合动态响应仿真中,定义加速度符号变量计算时间过长的问题,采用从变量矩阵中分离加速度变量的方法,分别计算动力学模型中的加速度系数矩阵和非加速度向量,实现快速的响应迭代求解。对比两种不同仿真方法的计算用时发现,分离加速度变量的方法计算用时仅为定义符号变量方法的1‰,可快速为直升机旋翼故障仿真研究提供大量数据样本。以旋翼气动不平衡为例,采用上述仿真方法对旋翼/机体耦合动态响应进行仿真,结果表明上述方法能很好地模拟旋翼不平衡对旋翼/机体耦合动态响应的影响,经分析发现的影响规律可用于旋翼不平衡故障诊断研究。In response to the problem of long calculation time for defining acceleration symbol variables in helicopter rotor/body coupling dynamic response simulation,a method of separating acceleration variables from variable matrices was adopted to calculate the acceleration coefficient matrix and non acceleration vector in the dynamic model,and achieve fast response iteration solution.Compating the calculation time of two different simulation methods,it shows that the method of separating acceleration variables only takes 1 ‰ of the method of defining symbolic variables,which can quickly provide a large number of data samples for helicopter rotor fault simulation research.Taking rotor aerodynamic imbalance as an example,the dynamic response of rotor/fuselage coupling of has been simulated by the above method,and the results show that the method can effectively simulate the influence on dynamic response of rotor imbalance.The influence rule found through the analysis can be used for rotor imbalance fault diagnosis research.

关 键 词：分离 加速度 直升机 旋翼机体耦合 动态响应 

分 类 号：V275.1[航空宇航科学与技术—飞行器设计]