The invention relates to a rudder shaft heat-proof structure with separated heat-proof and force-bearing functions. The rudder shaft heat-proof structure comprises a brush type heat sealing ring and aheat-proof ring. The heat-proof ring is fixedly installed on the surface of a cabin body, a boss is arranged on the upper surface of the heat-proof ring, and a through hole is formed in the center ofthe heat-proof ring; a rudder shaft penetrates through the through hole in the center of the heat-proof ring to be connected with the cabin body and the rudder; the rudder shaft is not contacted withthe central through hole of the heat-proof ring; and a gap between the heat-proof ring and the rudder shaft is thermally sealed by adopting a brush type thermal sealing ring. A groove structure matched with the boss structure of the heat-proof ring in shape is arranged on one side, facing the surface of the cabin body, of the rudder; the total height of the heat-proof ring is greater than a gap between the cabin body and the rudder; and the rudder is not in contact with the heat-proof ring. Separation of force bearing and heat prevention functions of the rudder shaft part is achieved, and a problem that the rigidity and strength reliability of the rudder shaft are uncertain due to the fact that the rudder shaft part bears harsh pneumatic heating is solved.
一种防热、承力功能分离的舵轴防热结构,包括:刷式热密封圈和防热环;防热环固定安装在舱体表面,防热环的上表面设置有凸台,防热环中心开有通孔;舵轴穿过防热环中心的通孔分别连接舱体和舵;舵轴与防热环中心通孔不接触;防热环与舵轴之间的间隙采用刷式热密封圈进行热密封。舵朝向舱体表面一侧设置有与防热环的凸台结构的形状配合的凹槽结构;防热环的总高度大于舱体和舵之间的缝隙;舵与防热环之间不接触。本发明实现舵轴部位承力、防热功能分离,解决了舵轴部位承受严酷气动加热导致舵轴刚强度可靠性不确定的问题。
Rudder shaft heat-proof structure with separated heat-proof and force-bearing functions
一种防热、承力功能分离的舵轴防热结构
2020-11-13
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
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