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飞机不同的装挂重量使飞机每次起飞时实际载荷变化。主要通过飞行参数记录仪(FPR)记录的数据研究战斗机起飞外挂重量对飞机结构疲劳寿命的影响。对某型飞机的一次完整飞行,按不同起飞外挂情况计算其损伤比值,结果表明分散度达到设计基准的27%。通过调查飞机挂弹架次比例,发现情况变化随意性很强,基本无统计规律可循,因而按每架次实际起飞外挂重量计算疲劳损伤显得尤为必要。对3架飞机近3000架次记录数据的分析表明,按实际起飞重量计算的结构疲劳损伤比按设计情况要轻约20%。这一研究结果为基于实际载荷监控进行单机延寿挖潜提供了技术支持。
The different loading weight of the aircraft changes the actual load of the aircraft each time it takes off. Mainly through the flight data recorder (FPR) recorded data to study the impact of aircraft fighter plunge weight on the fatigue life of the aircraft structure. For a complete flight of a certain type of aircraft, the damage ratio is calculated according to different take-off and landing situations. The results show that the dispersion degree reaches 27% of the design basis. By investigating the sub-proportion of aircraft mounts, it is found that the situation is highly variable and basically has no statistical rules to follow. Therefore, it is necessary to calculate the fatigue damage according to the actual weight of the mounts. An analysis of nearly 3,000 records of 3 aircraft shows that structural fatigue damage by actual takeoff weight is about 20% lighter than designed. The results of this study provide technical support for tapping the life of a single machine based on actual load monitoring.