以高分子材料自润滑衬套为研究对象，其摩擦阻尼为旋翼摆振铰提供减摆阻尼，在直升机飞行时，摆振铰作周期摆振运动，产生大量的热，引起衬套温度升高，易造成摆振自润滑衬套阻尼值剧烈变化。通过建立旋翼支臂摆振铰自润滑衬套摩擦生热模型，计算了摆振铰摩擦总热流量，按摩擦副接触面最高温度相等假设计算热流量分配。对传热过程应用有限元稳态热进行求解，获得了直升机旋翼运转时摆振铰摩擦副的温度分布，再进行自润滑衬套疲劳耐久性试验装置水冷散热等同性分析，最终确定了试验装置控制温度参数，为旋翼摆振铰自润滑衬套疲劳耐久性考核试验设计和验证提供参数。
The self-lubricating bushing of polymer material, whose friction damping provides lead-lag reduction damping for the rotor drag-hinge, rises in temperature during helicopter flights because of the considerable heat generated by the periodic lead-lag motion of the drag-hinge, which could easily induce drastic changes in its damping value. By establishing the friction heat generation model of the drag-hinge self-lubricating bushing of the rotor arm, we calculate the total friction heat flux in the drag-hinge, and compute the heat flux distribution based on the assumption that the highest temperature of the contact surfaces of the friction pairs is equal. The finite element steady-state heat is applied to the solution of the heat transfer process, and the temperature distribution of the drag-hinge friction pair when the helicopter rotor is running is obtained. Then the water cooling heat dissipation equivalence analysis of the self-lubricating bushing fatigue durability test device is conducted, and the temperature control parameter of the test device is determined, thereby providing parameters for the design and verification of the fatigue durability test of the rotor drag-hinge self-lubricating bushing.
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