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某型飞机在外场试飞过程中,后机身边条维形段结构连续出现蒙皮裂纹、型材断裂、铆钉松动及掉铆钉头等故障,给飞行安全带来隐患。研究发现,此类故障是由于后机身边条维形段在飞机尾部不稳定扰流环境下,扰流对维形段壁板产生激振导致结构振动疲劳损伤而引起的。通过增强维形段壁板的强度和刚度,可显著降低扰流对维形段蒙皮和铆钉的破坏。经改装飞机几年的飞行表明,后机身边条维形段壁板增强方案有效可行。
During the flight test of a certain type of aircraft in the field, the skin cracks, the profile breakage, the rivet looseness and the first-out rivet head failure continue to occur in the cross-section structure of the fuselage at the rear fuselage, which poses a hidden danger to flight safety. It is found that such failure is caused by the vibration of fatigue caused by the vibration of the section-shaped wall panels caused by the spoiler due to the unsteady disturbance of the rear fuselage section of the rear fuselage in the plane of the aircraft. By strengthening the strength and stiffness of the profiled section wallboard, the damage of the spoiler to the skin and the rivet of the shape section can be significantly reduced. After a few years of modified aircraft flight shows that the rear fuselage section of the dimensional section of the wall plan is effective.