舰艇火灾风险管理研究

基于安全学倡导的“人、机、环境、管理”4个基本要素,构建了舰艇火灾风险管理的系统模型,分析了各要素之间的关系及相互作用,并且详细说明了舰艇火灾风险管理的过程。     

FGH96粉末高温合金涡轮盘淬火过程界面换热系数的研究

以试验方法研究了FGH96粉末高温合金涡轮盘在空冷、风冷和油淬等条件下的表面换热行为,进而反算求解得到了界面换热系数,并将其应用到实际盘件热处理过程的数值模拟当中。结果表明,油淬条件下的界面换热系数远大于其他两种冷却方式,其最大值约为空冷换热系数最大值的10倍。现有工艺适合文中涡轮盘的热处理,淬火应力低于材料对应温度的屈服强度。     

湿空气凝结对ONERA M6机翼气动特性影响的数值研究

大气飞行条件下机翼附近的跨声速湿空气流动中空气中含有的水蒸汽可能越过饱和线而发生非平衡凝结。水蒸汽凝结潜热加热气流会改变跨声速流动的特性,从而对机翼气动特性造成显著影响。本文建立了湿空气非平衡凝结流动的数学物理模型,对ONERA M6机翼在跨声速条件下的湿空气非平衡凝结流动进行了分析。结果表明,与干空气流动相比,在攻角为3.06°和空气相对湿度为50%时,ONERA M6机翼表面压力系数有显著变化。造成机翼气动特性显著变化的原因在于:湿空气中水蒸汽凝结放热对跨声速气流加热,导致机翼表面附近的流速、压力与流场结构发生了显著变化。     

棘轮和蠕变条件下材料的附加塑性变形行为研究

针对316L不锈钢进行大量单轴棘轮和蠕变试验研究,对材料在棘轮和蠕变作用下的塑性变形行为以及变形量进行比较和分析.分析发现,材料棘轮和蠕变变形行为之间存在一些相似规律,而且相同试验时间下蠕变变形高于棘轮变形.在持续应力作用下,材料的附加塑性变形与作用应力间体现出上凸的抛物线规律,附加塑性变形先随应力的增长而升高,达到峰值后又逐渐减小.最后,根据这种上凸的抛物线规律提出相应的本构描述方程.     

检漏方法的灵敏度估算

为方便地选择检漏方法 ,设计检漏系统和估算检漏系统的灵敏度 ,文章推导了一些常用检漏方法的灵敏度估算公式 ,这些公式在航天密封产品的检漏实践中具有实用性     

QACVR在赛斯纳“奖状”750飞机上的改装设计方案

提出了QACVR在赛斯纳"奖状"750飞机上的改装设计方案,详细介绍了改装设计中的重点工作。     

Modeling M(3000)F2 based on extreme learning machine

This paper presents an novel extreme learning machine (ELM)-based prediction model for the ionospheric propagation factor M(3000)F2 at Darwin station (12.4°S, 131.5°E; −44.5°dip) in Australia. The proposed ELM model is trained with hourly daily values of M(3000)F2 from the period 1998–2014 except 2001 and 2009. The hourly daily values of 2001 (high solar activity) and 2009 (low solar activity) are used for validating the prediction accuracy. The proposed ELM for modeling M(3000)F2 can achieve faster training process and similar testing accuracy compared with backward propagation neural network (BPNN). In addition, the performance of the ELM is verified by comparing the predicted values of M(3000)F2 with observed values and the international reference ionosphere (IRI −2016) model predicted values. Based on the error differences (the root mean square error (RMSE) and the M(3000)F2 percentage improvement values M(3000)F2_IMP(%)), the result demonstrates the effectiveness of the ELM model compared with the IRI-2016 model at hourly, daily, monthly, and yearly in high (2001) and low (2009) solar activity years. The ELM also shows good agreement with observations compared with the IRI during disturbed magnetic activity.     

Influence of uniaxial tensile pre-strain on forming limit curve by using biaxial tensile test

This paper focused on the effect of pre-strain on forming limit curves (FLC) of 5754-O aluminum alloy sheet through utilizing biaxial tensile approach. Based on Swift model and Yld2000-2d yield criterion, the dimensions of cruciform specimen was optimized through applying finite element method for increasing the strain at specimen center. After that, with the recommended specimen size, the cruciform specimen was tested under various stroke ratios to experimentally characterize the limit strains under different pre-strain levels. Subsequently, the biaxial tensile tests were simulated by Abaqus to obtain the limit strains and validate the material models. It can be observed in both experiments and simulations that the pre-strained uniaxial tension followed by plane tension or equi-biaxial tension can improve the formability of sheet metals. Besides, the strain path change affects the trend of first derivative of strain rate difference between neighboring points with respect to time. An early increase occurred and then fell back to the stable value, the steady evolution continued until to a new increase reaching the critical value. The M–K prediction approach was simulated to verify the influence of pre-strain on FLC. It can be found that the early increase peaks of the major strain incremental ratio rose with the amplitude of pre-strain. Finally, the phenomenon of pseudolocalization caused by the strain path change was explained through evolution of stress state inside the groove.     

基于S3000L的MTA方法在民用飞机领域的应用研究

目前大多数国际主流民用飞机制造商均开始采用S3000L标准进行综合后勤保障设计,以提高飞机的可靠性和维修性。本文通过研究维修任务分析的原理和方法,结合民用飞机研制经验制定出一套可行、有效的维修任务分析操作程序,并运用实例进行了验证和说明,为国内开展民用飞机维修工程分析及其他相关保障工作提供了参考。     

基于NURBS方法的机翼气动外形优化

飞行器气动外形优化就是将设计对象的空气动力学性能分析与最优化方法相结合,通过不断改变设计对象的外形,使其气动性能在满足一定约束条件下达到最优.气动外形优化是一个涉及几何参数化、动网格、流场计算和寻优算法的综合应用平台.随着计算流体力学(CFD)的发展以及高性能计算机的使用,气动外形优化在现代飞行器设计中的作用愈加重要....