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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。
During the test flight, a certain type of aircraft has a large influence on the completion of the test flight due to the large vibration of the instrument panel. In this paper, the finite element model was established for the original design of the aircraft dashboard and the improved design scheme, and the compulsory response of the aircraft dashboard under the two schemes was analyzed and calculated using the mass method MSC / NASTRAN. The calculation results show that the vibration of the improved dashboard structure scheme is obviously improved compared with the original scheme.