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首先以主桨叶为研究对象,理论分析了直升机俯冲拉起状态下主桨叶实测载荷的影响因素;其次,以某型直升机旋翼载荷试飞为例,选取其主桨叶上的关键剖面,采用电阻应变计法进行飞行载荷测量,得到了不同重量重心、不同高度、不同法向过载等情况下的实测载荷;分析了实测的主桨叶挥舞弯矩、摆阵弯矩载荷值在直升机整个俯冲拉起过程中的变化规律,分析了实测载荷值随法向过载等的变化规律。为该型直升机试飞提供技术支持的同时,也为后续其他直升机法向过载包线拓展验证试飞提供重要支持。
First of all, taking the main blade as the research object, the paper analyzes the influencing factors of the main blade’s actual load under the condition of the helicopter submerging. Secondly, take a helicopter rotor load test as an example, select the key blade on the main blade, Resistance strain gage method was used to measure the flight load, and the measured loads under different weight center of gravity, different height and different normal overload were obtained. The actual measured values of waving moment and pendulum moment load of the main blade were analyzed in the entire subduction The law of change during the pull-up process and the change law of the measured load value with the normal overload are analyzed. Provide technical support for flight test of this type of helicopter, and provide important support for follow-up verification test of normal overload line extension of other helicopters.