某型系列飞机应急活门故障分析及预防措施
|
摘要
为了研究某型系列飞机应急活门经常出现的故障:在襟翼处于放下状态时,按下"收上"按钮,襟翼收上过程缓慢,同时伴有应急活门冷气端口渗油的现象.对飞机襟翼收放的原理进行了分析,并对应急活门进行了气压、液压试验.试验结果表明应急活门工作状态良好,试验过程中没有漏气、漏油、渗油现象.造成故障的原因可能有:襟翼处于放下位置,没有按"恢复"按钮,直接按"收上"按钮;附件长期使用,活塞的锥形端面和应急活门冷气端口接触间隙变大,导致渗油,而试验压力比正常工作状态压力大,所以试验过程中未出现渗油现象;油液中含有杂质,夹在锥形端面和冷气端口中间,使得两者间有间隙,导致渗油.
In order to study the frequent failures of a series of aircraft: when the flaps are in the down position,press the "Close"button,the flap retracts slowly,accompanied by the phenomenon of oil leakage in the cold gas port of emergency valve. The principle of aircraft flap is analyzed,and the emergency valve was tested by air pressure experiment and hydraulic pressure experiment. The test results show that the emergency valve works well and there is no air leakage,oil leakage and oil seepage during the test.The cause of the failure may be: the flaps are in the down position,do not press the "restore " button,press the "close " button directly; the attachment has been used for a long time,the contact gap between the conical end of the piston and the emergency valve port has become large,resulting in the oil seepage. The experimental pressure was higher than normal working condition,so no seepage is observed during the test.The oil contains impurities that sandwiched between the conical end and the cold air port,causing the gap between the two,leading to the oil seepage.
In order to study the frequent failures of a series of aircraft: when the flaps are in the down position,press the "Close"button,the flap retracts slowly,accompanied by the phenomenon of oil leakage in the cold gas port of emergency valve. The principle of aircraft flap is analyzed,and the emergency valve was tested by air pressure experiment and hydraulic pressure experiment. The test results show that the emergency valve works well and there is no air leakage,oil leakage and oil seepage during the test.The cause of the failure may be: the flaps are in the down position,do not press the "restore " button,press the "close " button directly; the attachment has been used for a long time,the contact gap between the conical end of the piston and the emergency valve port has become large,resulting in the oil seepage. The experimental pressure was higher than normal working condition,so no seepage is observed during the test.The oil contains impurities that sandwiched between the conical end and the cold air port,causing the gap between the two,leading to the oil seepage.
引文
[1]《飞机设计手册》总编委.飞行控制系统和液压系统设计.飞机设计手册(12册)[M].北京:航空工业出版社,2002.
[2]印正锋,毛德爱,邵明华.自动加油式飞机应急液压系统研究[J].液压与气动,2013(7):75-77.
[3]何永乐,刘彦斌,王宏儒,等.应急刹车活门管嘴液压密封性试验研究[J].航空精密制造技术,2015,51(3):42-44.
[4]张晓燕,张巍.飞机襟翼控制系统故障分析及改进设计[J].航空科学技术,2013(6):41-43.
[5]吴剑秋,梁晓阳,杨钰.飞机机动襟翼伺服控制系统的综合测试系统研制[J].计算机测量与控制,2002,10(8):499-503.
[6]王自知,张健伟.飞机襟翼作动器维修测试系统方案设计[J].航空维修与工程,2017(3):44-46.
[7]任英武.襟翼电气操纵系统故障分析与线路改进[J].中国民航大学学报,2008,26(5):58-59+65.
[8]王自知,张健伟.飞机襟翼作动器维修测试系统方案设计[J].航空维修与工程,2017(3):44-46.
[9]王柏钧.运八回油转换活门结构改进设计简介[J].液压工业,1990(4):44-46.
[10]印正锋,毛德爱,邵明华.自动加油式飞机应急液压系统研究[J].液压与气动,2013(7):75-77.
[11]任义志,李华.某型飞机起落架收放液压系统故障分析及排除[J].西安航空学院学报,2017(9):29-31.
[2]印正锋,毛德爱,邵明华.自动加油式飞机应急液压系统研究[J].液压与气动,2013(7):75-77.
[3]何永乐,刘彦斌,王宏儒,等.应急刹车活门管嘴液压密封性试验研究[J].航空精密制造技术,2015,51(3):42-44.
[4]张晓燕,张巍.飞机襟翼控制系统故障分析及改进设计[J].航空科学技术,2013(6):41-43.
[5]吴剑秋,梁晓阳,杨钰.飞机机动襟翼伺服控制系统的综合测试系统研制[J].计算机测量与控制,2002,10(8):499-503.
[6]王自知,张健伟.飞机襟翼作动器维修测试系统方案设计[J].航空维修与工程,2017(3):44-46.
[7]任英武.襟翼电气操纵系统故障分析与线路改进[J].中国民航大学学报,2008,26(5):58-59+65.
[8]王自知,张健伟.飞机襟翼作动器维修测试系统方案设计[J].航空维修与工程,2017(3):44-46.
[9]王柏钧.运八回油转换活门结构改进设计简介[J].液压工业,1990(4):44-46.
[10]印正锋,毛德爱,邵明华.自动加油式飞机应急液压系统研究[J].液压与气动,2013(7):75-77.
[11]任义志,李华.某型飞机起落架收放液压系统故障分析及排除[J].西安航空学院学报,2017(9):29-31.