为解决现行飞机起落架缓冲器设计不考虑机体柔性存在的问题,以大柔性飞机支柱型起落架油气式缓冲器为例,采用三质量块飞机着陆模型和功量预估分配法选择缓冲器参数,并对其进行着陆响应动力学分析。研究结果表明,机体一阶模态频率和起落...为解决现行飞机起落架缓冲器设计不考虑机体柔性存在的问题,以大柔性飞机支柱型起落架油气式缓冲器为例,采用三质量块飞机着陆模型和功量预估分配法选择缓冲器参数,并对其进行着陆响应动力学分析。研究结果表明,机体一阶模态频率和起落架与机体连接点位置是影响机体储存着陆功量的两个主要因素:机体一阶模态频率小于2 H z时,机体储存的着陆功量预估公式计算误差小于5%;机体储存能量的耗散效率较低。展开更多
Damping faults in a helicopter rotor hub are diagnosed by using vibration signals from the fuselage. Faults include the defective lag damper and raspings in its flap and feathering hinges. Experiments on the diagnosis...Damping faults in a helicopter rotor hub are diagnosed by using vibration signals from the fuselage. Faults include the defective lag damper and raspings in its flap and feathering hinges. Experiments on the diagnosis of three faults are carried out on a rotor test rig with the chosen fault each time. Fuselage vibration signals from specified locations are measured and analyzed by the fast Fourier transform in the frequency domain. It is demonstrated that fuselage vibration frequency spectra induced by three faults are different from each other. The probabilistic neural network （PNN） is adopted to detect three faults. Results show that it is feasible to diagnose three faults only using fuselage vibration data.展开更多
文摘为解决现行飞机起落架缓冲器设计不考虑机体柔性存在的问题,以大柔性飞机支柱型起落架油气式缓冲器为例,采用三质量块飞机着陆模型和功量预估分配法选择缓冲器参数,并对其进行着陆响应动力学分析。研究结果表明,机体一阶模态频率和起落架与机体连接点位置是影响机体储存着陆功量的两个主要因素:机体一阶模态频率小于2 H z时,机体储存的着陆功量预估公式计算误差小于5%;机体储存能量的耗散效率较低。
文摘Damping faults in a helicopter rotor hub are diagnosed by using vibration signals from the fuselage. Faults include the defective lag damper and raspings in its flap and feathering hinges. Experiments on the diagnosis of three faults are carried out on a rotor test rig with the chosen fault each time. Fuselage vibration signals from specified locations are measured and analyzed by the fast Fourier transform in the frequency domain. It is demonstrated that fuselage vibration frequency spectra induced by three faults are different from each other. The probabilistic neural network （PNN） is adopted to detect three faults. Results show that it is feasible to diagnose three faults only using fuselage vibration data.
