某型飞机仪表板振动分析

Analysis of Instrument Panel Vibration of a Certain Type Aircraft

某型飞机在试飞过程中因仪表板振动较大,对试飞任务的完成产生了一定的影响。本文针对该型飞机仪表板原设计方案及改进设计方案分别建立了有限元计算模型,并采用MSC/NASTRAN大质量法计算分析了两种方案下飞机仪表板的强迫响应情况。计算结果表明,改进后的仪表板结构方案振动情况较原方案得到了明显的改善。

Serious instrument panel vibration appeared in the process of test flight of a certain type aircraft, which affects the accomplishment of flight test mission. In the paper, the finite element model is established respectively for original design plan of instrument panel of this type aircraft and improved design plan; the forced responses under two plans also are calculated and analyzed by using MSC/NASTRAN large mass method. The calculation results show the vibration under the improved instrument panel structure plan is reduced obviously, compared with that under the original plan.