摘要
推导了某型飞机尾起落架主支柱转角与缓冲器行程的关系,以及尾起落架主支柱转角与轮轴倾角之间的关系,并指出在停机载荷下,尾起落架轮轴倾角受到主支柱转角的影响。将某型飞机与它同类型飞机尾起落架的转弯情况进行了比较,发现某型飞机尾起落架转弯困难的原因是:在停机载荷下,缓冲器压缩量较大,轮叉转动较小的角度就可以导致轮轴与地面之间产生较大的倾角。在满足缓冲性能的基础上,将某型飞机的尾起落架缓冲器重新进行了充填,提高其充气压力,减少灌油量,使尾起落架缓冲器在停机载荷下的压缩量为0。缓冲器经过重新充填后,在停机载荷下,该型飞机尾起落架轮轴与地面的倾角始终为0°,机轮垂直地面,即使在小转弯半径条件下,牵引转弯和首飞滑跑转弯时,尾起落架机轮左右转动也很灵活。改变该飞机尾起落架缓冲器充填参数后,解决了转弯困难的问题。
The relationships between the main strut rotating angle and the buffer displacement, and between the main strut rotating angle and the axle incline angle are established for a certain airplane tail landing gear. When the tail landing gear is exposed to weight loading, the axle incline angle is affected by the main strut ro- tating angle. The turning performance of this airplane is compared with that of the same type of airplane tail landing gear. The reason for difficulty in turning is found to be that the buffer displacement is too great when the tail landing gear is subjected to weight loading, so that the axle incline angle is very large even when the wheel fork is turning a small angle. While ensuring good shock absorption performance, the tail landing gear buffer is filled afresh with higher pressure and less hydraulic oil, which reduces the buffer displacement to zero when the tail landing gear is under weight loading. The axle incline angle is always zero degree after changing the buffer parameters, and the tail wheel remains perpendicular to the ground and the wheel fork is free to run in towing turning and taxing turning in the first flight test even with a small turning radius. Thus, the difficulty in turning is solved by changing buffer parameters.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2009年第6期1012-1016,共5页
Acta Aeronautica et Astronautica Sinica
关键词
尾起落架
转弯困难
主支柱转角
轮轴倾角
缓冲器充填参数
支柱
tail landing gear
difficulty in turning
main strut rotating angle
axle incline angle
buffer parameters
struts
