论文部分内容阅读
针对直升机主桨叶和尾桨叶的拉扭承载能力难以通过理论计算获得的难题,研制了一种新型结构拉扭试验装置,详细介绍了该装置的结构原理、标定结果,以及在直升机静强度试验中的应用。
Aiming at the problem that the torsional load carrying capacity of the main blade and the tail blade of the helicopter is difficult to be obtained by theoretical calculation, a new type of structure torsional testing device is developed. The principle of the device, the calibration results and the static strength Application in experiment.