摘要
针对某型直升机尾桨/尾梁耦合稳定性进行分析,并根据分析结果进行动力学特性修改。通过灵敏度分析确定结构参数修改变量,并利用正交边界交叉法,以全机垂向一阶弯曲模态频率调整至需求值的同时付出最小重量代价为目标进行结构参数优化,最后进行了地面试验验证与地面开车验证。结果表明,在将尾梁蒙皮及过渡段底部长梁重量增加35.82kg的情况下,该模态频率调整至5.85Hz,基本满足直升机动力学工程设计要求。
The coupling stability of the tail rotor/beam of a helicopter was analyzed,and the dynamic characteristics were modified according to the analysis results.The modified variables of structural parameters were determined by sensitivity analysis,and the structural parameters were optimized with the objective of adjusting the whole helicopter vertical first-order bending mode frequency to the required value and paying the minimum weight cost by using the normal boundary intersection method.Finally,the ground test verification and ground start-up verification were carried out.The results show that the modal frequency is adjusted to 5.85Hz in the case of increasing the weight of the beam and the bottom of the transition beam to 35.82kg,which basically meets the design requirements of the helicopter dynamics engineering.
作者
陈新华
陈浩
王国胜
刘忠超
Chen Xinhua;Chen Hao;Wang Guosheng;Liu Zhongchao(China Helicopter Research and Development Institute,Jingdezhen 333001,China)
出处
《航空科学技术》
2019年第4期43-49,共7页
Aeronautical Science & Technology
关键词
直升机
尾桨/尾梁耦合
优化设计
试验验证
helicopter
couple of tail rotor/beam
optimization design
experimental verification
