The invention relates to an aircraft steering engine and a preparation method thereof, in particular to an aircraft steering engine for a high heat flow area and a preparation method thereof, and overcomes the defects that in the prior art, due to the gap heat flow effect, a rudder bearing is overheated due to gap heat flow, the strength and rigidity of a rudder shaft are uncertain, and the connecting part of a horizontal rudder and a rudder cabin is seriously damaged. The aircraft steering engine for the high heat flow area comprises a horizontal rudder, a rudder cabin and a rudder shaft, one end of the rudder shaft is fixedly connected with the horizontal rudder, the other end of the rudder shaft is rotationally connected with the rudder cabin, and the rudder shaft between the horizontal rudder and the rudder cabin is sleeved with an outer heat insulation ring and an inner heat insulation ring; one end face of the outer heat insulation ring is fixedly connected with the bottom face of the horizontal rudder, a first annular groove is formed in the position, around the rudder shaft, of the other end face of the outer heat insulation ring, the inner heat insulation ring is arranged in the first annular groove, a second annular groove is formed in the outer surface of the rudder cabin around the rudder shaft, and the other end face of the outer heat insulation ring is matched with the second annular groove.
本发明涉及飞行器舵机及其制备方法,具体涉及用于高热流区的飞行器舵机及其制备方法,解决现有技术中存在缝隙热流作用使得舵轴承受缝隙热流超温导致舵轴强度和刚度不确定,水平舵与舵舱连接部位产生严重损坏的不足之处。本发明的用于高热流区的飞行器舵机包括水平舵、舵舱以及舵轴,所述舵轴的一端与水平舵固定连接,另一端与舵舱转动连接,水平舵和舵舱之间的舵轴上套设有外隔热环和内隔热环;外隔热环的一个端面与水平舵的底面固定连接,另一个端面上围绕舵轴的位置开设有第一环形槽,内隔热环设置在第一环形槽中,舵舱外表面围绕舵轴设置有第二环形槽,外隔热环的另一个端面与第二环形槽配合设置。
Aircraft steering engine for high heat flow area and preparation method of aircraft steering engine
用于高热流区的飞行器舵机及其制备方法
11.04.2023
Patent
Elektronische Ressource
Chinesisch
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