飞机撞击下核电厂安全壳载荷曲线相关问题研究

针对大型商用飞机对核电厂反应堆安全壳恶意撞击的安全评估需求,综述了国外确定飞机撞击安全壳载荷曲线的基础理论、试验测试技术和数值模拟方法.首先,从理论上对飞机撞击安全壳的载荷特性和Riera撞击模型进行分析,给出了Riera模型的基本假设、模型各项物理意义及模型的求解方法,明确了靶体碰撞表面的冲击载荷(力)由静载项和动载项组成;其次,分析总结了确定Riera模型中压损载荷参数的试验方法和真实飞机撞击载荷测量的试验技术和实施方法,指出大型商用飞机对核电厂反应堆安全壳恶意撞击属"软冲击"范畴,撞击载荷可用Riera模型计算得到;再者,在数值模拟方面,总结了采用有限元技术进行飞机撞击载荷计算和安全评估的数值模拟方法及其发展趋势;最后,在分析国内开展飞机撞击载荷研究面临问题的基础上,指出从理论上建立飞机撞击载荷-时间曲线计算模型及方法,并通过试验和数值模拟验证是国内确定大型商用飞机撞击安全壳结构载荷曲线比较可行的技术路线.     

Exergetic Sustainability Indicators as a Tool in Commercial Aircraft: A Case Study for a Turbofan Engine

This paper focuses on the exergetic sustainability indicators of a medium-range commercial aircraft engine for constant reference environment and ground running conditions. First, a detailed exergy analysis of turbofan engine have been performed based on engine test cell parameters. Starting from the sustainability considerations and the second law of the thermodynamics, the paper presents six exergy-based sustainability indicators. The indicators of the turbofan engine developed here in conjunction with exergetic analysis and sustainable development are exergy efficiency, waste exergy ratio, exergy destruction factor, recoverable exergy rate, environmental effect factor, and exergetic sustainability index. The investigated sustainable indicators have been calculated by using exergy analysis outputs for aircraft ground running condition. Results from this study show that values of exergy efficiency, waste exergy ratio, exergy destruction factor, recoverable exergy rate, environmental effect factor, and exergetic sustainability index of investigated turbofan engine are found to be 0.315, 0.685, 0.408, 0, 2.174, and 0.460, respectively. These parameters are expected to quantify how the turbofan engine and aircraft become more environmentally benign and sustainable.     

随机不确定性影响下某航炮发射动力学仿真

目的研究随机不确定性对航炮发射动力学响应的影响,提高其射击密集度。方法建立某航炮刚柔耦合动力学模型,利用ADAMS软件进行发射动力学仿真分析。考虑航炮射击过程中的不确定因素,采用非概率凸集模型进行量化,揭示缓冲器弹簧刚度、平衡机弹簧刚度、炮膛合力等参数不确定性对航炮射击密集度的影响规律。结果炮口振动在不确定性因素的影响下,出现振动幅值增大,在区间范围内波动的现象。结论航炮射击时的炮口振动严重影响了射击密集度,因此在设计时必须考虑不确定性因素,所得结果对于提高航炮系统射击密集度具有一定的指导意义。     

某型飞机4号油箱结构损伤分析及修复评估

目的 某型双座机使用中发现4号油箱存在不同程度结构损伤,分析其损伤原因和制定修理方案。方法 对4号油箱结构状态进行深入检查评估后,从结构损伤过程、载荷情况、设计制造和外场使用等方面综合分析损伤原因。对实际损伤结构进行强度计算和评估,制定结构损伤补强修理方案,并提出修理改进建议。结果 通过分析得出,损伤原因主要是4号油箱局部存在设计制造缺陷,且飞机在作大过载飞行时,4号油箱可能处于满油或大量余油的高负载状态。根据损伤原因制定的修理方案合理可行,通过了静强度校核和评估。结论 基于该损伤结构提出的修理方案通过实际修理验证,能够满足油箱结构强度设计要求,提出的改进建议能够改善飞机疲劳品质。     

基于熵权-HDT的航空器维修人误概率确定

人误是造成民用航空维修差错的主要因素。为确定不同情境下人误发生概率,结合某维修基地具体情况,采用熵权法确定主要的影响因子,并基于全决策树法分析主要影响因子对航空器维修人误概率的影响程度。计算结果显示,该维修基地人因可靠性的主要影响因子包括航空器维修人员的安全态度、技能、沟通、工作环境、压力以及工段长领导能力。根据各主要影响因子的不同品质描述等级组合,确定该情境下航空器维修人员的人误概率。鉴于该维修基地人因可靠性影响最明显的因子是"沟通",提出信息及时交流、明确沟通重要性等解决措施。     

中国民航运输航空器偏/冲出跑道统计分析

为了查找民航运输航空器偏/冲出跑道事件的共性特点及成因,对比了国外不同研究机构的相关数据,统计分析了1996年至2010年间中国民航偏/冲出跑道事件。结果表明,6月、7月、8月因常常伴有降水、雷暴等复杂天气现象,事件数量最为集中;着陆阶段航空器偏出跑道是本类事件中最突出的问题。驾驶术欠缺、CRM失效、复杂气象条件、违反SOP、夜航或受灯光不利影响是促成着陆阶段偏出跑道的主要因素。当两种或两种以上风险因素同时存在时,因耦合效应着陆偏出跑道事件的发生概率会明显增加。     

A comparative study of prognostic MM5 meteorological modeling with aircraft, wind profiler, lidar, tethered balloon and RASS data over Philadelphia during a 1999 summer episode

This study presents a comparative evaluation of the prognostic meteorological Fifth Generation NCAR Pennsylvania State University Mesoscale Model (MM5) using data from the Northeast Oxidant and Particle Study (NE-OPS) research program collected over Philadelphia, PA during a summer episode in 1999. A set of model simulations utilizing a nested grid of 36 km, 12 km and 4 km horizontal resolutions with 21 layers in the vertical direction was performed for a period of 101 h from July 15, 1999; 12 UTC to July 19, 1999; 17 UTC. The model predictions obtained with 4 km horizontal grid resolution were compared with the NE-OPS observations. Comparisons of model temperature with aircraft data revealed that the model exhibited slight underestimation as noted by previous investigators. Comparisons of model temperature with aircraft and tethered balloon data indicate that the mean absolute error varied up to 1.5 °C. The comparisons of model relative humidity with aircraft and tethered balloon indicate that the mean relative error varied from –11% to –22% for the tethered balloon and from –5% to –30% for the aircraft data. The mean relative error for water vapor mixing ratio with respect to the lidar data exhibited a negative bias consistent with the humidity bias corresponding to aircraft and tethered balloon data. The tendency of MM5 to produce estimates of very low wind speeds, especially in the early-mid afternoon hours, as noted by earlier investigators, is seen in this study also. It is indeed true that the initial fields as well as the fields utilized in the data assimilation also contribute to some of the differences between the model and observations. Studies such as these which compare the grid averaged mean state variables with observations have inherent difficulties. Despite the above limitations, the results of the present study broadly conform to the general traits of MM5 as noted by earlier investigators.     

飞机用铝合金-CFRP搭接结构的电偶腐蚀预测研究

目的通过有限元仿真,预测飞机复合材料-铝合金搭接试件可能产生的腐蚀部位和腐蚀深度。方法采用动电位极化的方法,测得温度为40℃的5%NaCl溶液中铝合金和复合材料两种材料的极化曲线。以极化曲线及其拟合的电化学动力学参数作为边界条件,建立电偶腐蚀仿真模型。通过模型计算,分别得到两种材料的腐蚀预测结果,将其结果与实验室腐蚀试验结果进行对比。结果电偶试件模型预测得到的电偶电位值与实验测量得到的电偶电位值对比误差为4.2%。搭接试件的腐蚀部位为偶接处3 mm内,其腐蚀分布与搭接件电偶腐蚀模型预测的电位分布规律基本一致,腐蚀深度的预测值和腐蚀实验的实测值对比误差为12.5%。结论该研究的仿真预测结果与试验结果在一定程度上具有一致性,证明了仿真模型的正确性。     

颤振飞行试验激励技术发展的回顾和展望

首先对颤振发生机理、颤振飞行试验实施过程及颤振激励的重要性进行了简单介绍,然后对颤振激励方法的发展历程进行了回顾,对不同颤振激励技术的特点进行了详细分析,并提出了激励技术的选择原则和方法,得出不同激励方法的最佳适用对象。最后,结合新型飞机技术发展需求,对颤振激励技术的发展趋势进行了展望。不同的颤振激励技术服务、支持了不同型号飞机的飞行试验工作,随着各种超高速、轻型化、智能化飞机的出现,对各种新型颤振激励技术的需求会层出不穷,文中的工作对不同特点试验飞机颤振激励技术的选用给出有益的建议和参考。     

大型运输机水上迫降动力学分析及模型验证

目的 完善大型运输机水上迫降分析方法,提高分析精度。方法 以有限元和SPH方法为基础,开展大型运输机水上迫降动力学仿真。基于冯.卡门经典入水冲击理论,构造大型运输机机身底部吸力模型,提出基于工程修正的水上迫降动响应分析方法,并通过试验验证。结果 通过分析得出,飞机接水后,机头迅速上扬,俯仰角达到峰值后,机头向下运动,俯仰角逐渐减小,分析得到的飞机姿态变化与试验的变化趋势基本一致。结论 水上迫降模型试验表明,分析误差能够满足工程设计要求。