【作者】 张志林；

【导师】 姚卫星；

【作者基本信息】 南京航空航天大学 ， 飞行器设计， 2005， 博士

【摘要】 本文全面系统地阐述了飞机座舱透明件设计的主要环节和关键技术,并对其关键技术进行了系统地研究,为座舱透明件设计提供了系统完整的分析方法。所涉及的内容包括:有机玻璃疲劳性能研究、活动舱盖载荷谱编制、座舱玻璃疲劳寿命估算方法研究、座舱玻璃划伤故障容限研究、飞机风挡鸟撞动响应分析方法研究等。根据活动舱盖载荷特性,提出用压力传感器测量活动舱盖载荷的方法,并首次实现了活动舱盖载荷谱飞行测量。根据实测活动舱盖载荷曲线特点,提出了任务类型划分方法,建立了活动舱盖载荷谱数据统计方法和载荷谱编制方法,并依此编制出K8飞机活动舱盖载荷谱。根据有机玻璃特点,利用场强法原理,建立了有机玻璃裂纹形成寿命的局部应力估算方法,采用该方法估算得到的玻璃螺栓孔处的疲劳寿命与边缘连接件疲劳试验结果吻合较好。开展了有机玻璃蠕变试验和不同频率下的疲劳试验,拟合得出了蠕变损伤计算公式,通过研究,建立了蠕变损伤和纯疲劳损伤的分离方法,并用此方法对蠕变/疲劳共同作用下的寿命进行了预测,与试验结果吻合较好,说明该方法有很好的寿命预测能力。从划伤的产生原因着手进行分析,建立了座舱玻璃划伤故障模型,提出了座舱玻璃表面划伤故障预制方法。通过玻璃表面划伤剩余强度试验和疲劳试验,得出了MDYB-3玻璃表面裂纹断裂韧度和表面划伤扩展门槛值,建立了座舱玻璃划伤故障剩余强度准则和划伤故障容限计算方法,并给出了9mm厚MDYB-3玻璃划伤故障容限值,为外场划伤故障分析处理提供了简便易行的方法。在实测鸟撞载荷的基础上,通过研究,建立了柔性靶载荷模型,经与鸟撞试验结果比较发现:柔性靶载荷计算结果与试验结果比较接近,为解耦解法提供了较准确的载荷模型。在基准解的基础上,通过不断地调整鸟体模型参数,使其结果与基准解相符,从而建立了鸟体模型。将鸟体模型用于风挡鸟撞动响应分析,并将分析结果与鸟撞试验结果进行比较,发现鸟体模型能够有效地模拟风挡鸟撞击过程,解决了耦合解法存在的鸟体模型模拟困难的问题,所建立的破坏准则判断失效结果与试验相符,从而为风挡抗鸟撞设计提供了有力的分析工具。更多还原

【Abstract】 In this thesis the main steps in the design for the transparency of aircraft canopy and the windshield are illustrated completely and systematically, the key technology is analyzed, and the design for the transparency of aircraft canopy and the windshield with the systematical and complete analysis method is provided. The content includes the study on the fatigue performance of the Plexiglas, the compiling of the load spectrum of the canopy, the study on the evaluation of the fatigue life of the canopy glass, the study on the allowable limit of the scratch on the canopy glass and the study on the analysis method of the dynamic response of the bird impact on the aircraft windshield.According to the characteristics of the load on the canopy, the method for measuring the load on the canopy with a pressure sensor is presented, and then the flight measurement of the load spectrum of the canopy is realized for the first time. Based on the characteristics of the measured load curve of the canopy, the method for the task type division is brought forward, and the statistic method for the data of the load spectrum of the canopy and the method for compiling the load spectrum are obtained, with which the load spectrum of the K8 aircraft canopy is worked out.According to the characteristics of the Plexiglas, using the principles of the stress field intensity (SFI), a local stress approach for the evaluation of the fatigue life of the Plexiglas structures is proposed. The fatigue life at the bolt holes in the glass structures predicted with this method is well consistent with the result of the fatigue test of the marginal connecting parts. The expressions of the creep damage is acquired by performing the Plexiglas creep test and the fatigue test at the different frequencies. The method for separating the creep damage from the fatigue damage is set up through the analysis. The life under the joint action of the creep and the fatigue was estimated with this method, which is compatible with the test results, so this method is of satisfactory ability in life prediction.By analyzing the reason of producing scratches, the fault model of the canopy glass is set up, and the fault-forecasting method for the scratch on the surface of更多还原