摘要
通过对比分析了飞行器机动飞行时动载荷数值计算结果和辨识结果,对弹性运动的计算模型进行了验证分析。首先,详细介绍了飞行器的弹性运动模型和结构动力学模型,并简要介绍了模态特征系统实现算法(Eigensystem Realization Algorithm,ERA)环境激励模态辨识方法的理论。其次,计算分析了由于操作机构作动引起的飞行器整体动载荷,研究了两种激励力计算方法间的区别。最后,基于工作模态辨识理论和实测振动数据,辨识了飞行器的动载荷,对计算结果进行了验证。通过研究,发现弹性运动计算模型是介于增量模型和绝对量模型这两者之间的。
The dynamic load calculation and verification technology is investigated. Firstly,the aircraft elastic motion model and structure dynamic model are put forward,and the theory of the ERA method is introduced. Secondly,the dynamic load of the aircraft during maneuver flight is studied under two simulation method of excitation force. At last,the operational modes are identified based on the telemetry data,including the mode frequency and shape. The mode response are derived by mode superposition method and mode orthogonal theory. Then the dynamic load is derived,where the dynamic load calculation technology is verified. According to the research,the real elastic model of the aircraft is situated between the increment model and absolute amount model.
出处
《战术导弹技术》
北大核心
2016年第4期27-33,共7页
Tactical Missile Technology
基金
国家重点实验室2015年开放课题(MCMS-0115G01)
