CAJ | 학술논문

某型发动机喷管在装机飞行时出现的小裂纹可能会引发严重的飞行事故。为了避免飞行事故的发生，基于有限元仿真技术，针对该型发动机喷管结构，建立计算模型。并对某喷管整体结构进行了自由振动和模态分析，获得了该喷管模型的多阶自振频率和模态。结果表明：分析值与实测值吻合较好。其中，在20阶振动频率之前，共振造成的破坏主要集中于前转接段，20阶以后，共振造成的破坏转移到喷管的端口位置。所得结果对于结构改进和避免事故的发生具有一定的参考价值和指导意义。
모형발동궤분관재장궤비행시출현적소렬문가능회인발엄중적비행사고。위료피면비행사고적발생，기우유한원방진기술，침대해형발동궤분관결구，건립계산모형。병대모분관정체결구진행료자유진동화모태분석，획득료해분관모형적다계자진빈솔화모태。결과표명：분석치여실측치문합교호。기중，재20계진동빈솔지전，공진조성적파배주요집중우전전접단，20계이후，공진조성적파배전이도분관적단구위치。소득결과대우결구개진화피면사고적발생구유일정적삼고개치화지도의의。
The small cracks appeared in an engine nozzle in the flight would lead to serious aircraft incident. In order to avoid incident, a calculation model for the engine nozzle structure was buih based on infinite element simulation technology. The numerical results of free vibration frequencies and modes were also obtained by analyzing the integrated nozzle structure. The results show that the analysis value is fit to the test value very well. Therefore, the wreck caused resonance mainly focuses on former transfer phase before 20 order vibration frequency, the wreck transfers to port of outlet after 20 order. The result provides reference value and directive meaning to structure improving and incident avoiding.