摘要
确定A型飞机机翼主梁结构的使用寿命 ,是保证A型飞机使用安全的关键。通过对全机第一关键危险部位 -机翼主梁下凸缘第 2螺栓孔部位的寿命估算、模拟件疲劳对比试验、模拟件耐久性试验 ,全机疲劳试验 ,经过综合分析研究 ,得到A型飞机机翼主梁结构的使用寿命满足 30 0 0飞行小时的结论。这一结论为全机使用寿命的确定奠定了基础。而全机使用寿命的确定是A型飞机生产定型的重要依据 ,也是对现役A型飞机进行维护及大修的重要依据。
Determining the service life of the main spar of A A/C wing structure is vital to warrant the safety of the aircraft in flight?By the life evaluation of the second bottom boom bolt hole of the main spar, its part mock-up fatigue testcomparedwith similar airframe , its part durability test and the relevantcomplete airframe fatigue test, the service life and the instruction for the maintenanceof wing's main spar are consequently given in this dissertation.
出处
《飞机设计》
2002年第2期25-29,共5页
Aircraft Design
