The invention discloses an aircraft empennage and elevator jamming adjusting method. The aircraft empennage and elevator jamming adjusting method comprises an original horizontal empennage, an original vertical empennage and a standby horizontal empennage installed on the vertical empennage. The standby horizontal empennage is rotationally mounted on the original vertical empennage through a rotating shaft; and the standby horizontal wing is arranged at the top end of the original vertical tail wing when being unfolded, and is perpendicular to the original vertical tail wing. Under the condition that normal work of the original empennage is not affected, the load of the airplane is basically unchanged, but the probability of flight accidents caused by empennage faults can be effectively reduced, and the burden of a pilot in an emergency is reduced.
本发明公开一种飞机尾翼及升降舵卡阻调节方法,包括原水平尾翼,原垂直尾翼和安装在所述垂直尾翼上的备用水平尾翼;所述备用水平尾翼通过转轴转动安装在所述原垂直尾翼上;所述备用水平翼展开时置于所述原垂直尾翼的顶端,且与所述原垂直尾翼垂直设置。本发明在不影响原尾翼的正常工作的情况下,飞机载荷基本不变,但可以有效减少尾翼故障引起飞行事故发生的概率,减少了突发情况下飞行员的负担。
Airplane empennage and elevator jamming adjusting method
一种飞机尾翼及升降舵卡阻调节方法
2023-04-11
Patent
Elektronische Ressource
Chinesisch
IPC: | B64C AEROPLANES , Flugzeuge |
M28-05 AIRPLANE EMPENNAGE FATIGUE TEST REALISATION
British Library Online Contents | 2003
|