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.
MA Zhanqi
,
SUN Xiuwen
,
WANG Lingqi
. Temperature design and control of rotor drag-hinge self-lubrication bush fatigue test[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021
, 42(5)
: 524217
-524217
.
DOI: 10.7527/S1000-6893.2020.24217
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