Hypersonic flutter and flutter suppression system of a wind tunnel model

The aeroelastic behavior of a thin flat rudder model was numerically simulated and experimentally investigated in a hypersonic wind tunnel. In particular, a flutter suppression system taking advantage of collision within small gaps was proposed and a novel system for the flutter simulation of the whole nonlinear aeroelastic system including the flutter suppression system was developed. First, the critical flutter dynamic pressure of the rudder without the flutter suppression system was calculated with different methods. Then, the whole nonlinear aeroelastic system, including theflutter suppression system, was simulated to design the gap size. Finally, the flutter suppression system was experimentally validated in a hypersonic wind tunnel operating at Mach number 5. The typical phenomenon of Limit Cycle Oscillation(LCO) was observed, avoiding the structural failure of the model and the consistency between numerical and experimental results was demonstrated.The proposed suppression system can improve the design and reusability of test models of hypersonic flutter experiments.     

Preliminary forecast for the peak of solar activity cycle 24

Our forecast for the development phase of solar cycle 23 came out to be true; one of the very few to have attained this status out of several forecasts made. We review the details of the forecast and how it fared as the events unfolded in time. We note the present status of IMF intensity B and the planetary index Ap. We draw inferences as to what to expect for the development phase of cycle 24; several forecasts have already been made, they cover all possible scenarios, ranging from a very active to the quietest cycle in a century. Our preliminary forecast for the smoothed sunspot number at cycle 24 maximum is 101 ± 5, indicating that cycle 24 will be about 20% less active than cycle 23; the possibility that next three solar cycles may be progressively less active cannot be ruled out.     

微束等离子焊接

简要介绍了微束等离子焊接的工艺设备。通过对乌克兰巴顿焊接研究所几个实例的介绍，较全面地阐述了微束等离子焊接工艺方案、焊接设备的各项技术要求和特性。与氩弧焊、激光焊进行了比较，认为微束等离子焊接具有电弧收缩、能量集中、适用于薄壁件焊接的特点，在我国具有广阔的应用前景。     

焊接电弧波形和图像的同步采集与再现

进行了焊接电弧高速摄像图像和信号波形的同步采集和再现研究,给出了电弧图像和波形再现具体实现技术,并利用该技术成功地进行了电弧光谱信息检测熔滴过渡过程、二氧化碳短路过渡过程和变极性MIG焊电弧行为的研究。     

构型及二次燃烧对RBCC引射模态推力性能的影响

提出了掺混度模型并数值研究了五种构型和两种燃烧组织模式对RBCC发动机引射模态推力性能的影响,其中改进构型获得了推力增强.得出如下结论:(1)在引射掺混的前段,掺混过程主要由一次流喷管结构决定.而在引射掺混后段,后体构型对掺混过程影响较大.(2)获得较高掺混速率、较优引射比并在掺混过程中产生高于环境压强的流动状态是改进构型获得推力增强的两个重要因素.(3)与SMC燃烧组织模式相比,改进构型的SPI模式有效延迟了二次燃烧,不仅提高了燃烧效率而且没有使引射比过度下降.     

换热预冷发动机预冷特性和发动机性能数值研究

为深入了解换热预冷发动机换热器预冷效果和发动机性能,首先设计了叉排管束式细小通道换热预冷器,并采用非定常数值模拟方法对换热效果进行了仿真,然后结合换热预冷发动机性能计算程序对预冷发动机性能进行了研究。结果表明,飞行马赫数为2.5~4.0且氢气空气质量流比为0.03~0.09条件下,换热预冷器能将来流空气预冷90.6~471.2 K,低温氢气经吸热后温度升幅为266.1~455.3 K,换热效果良好。来流空气经预冷后涡轮发动机的飞行包线最高被拓展至马赫数4.0,达到了与超燃冲压发动机的衔接速域。相比于传统涡轮发动机,氢气空气质量流比为0.03时,本文换热预冷发动机加力状态推力能恢复至设计点推力水平;当氢气空气质量流比增加至0.09时,加力状态推力最高达到设计点推力的两倍左右。马赫数2.6以下换热预冷措施能小幅改善发动机比冲和耗油率（仅计算用于燃烧的氢气量）性能,而飞行速度大于马赫数2.6后换热预冷措施也难以抑制比冲和耗油率迅速恶化的趋势。     

2219铝合金拉锻式摩擦塞补焊工艺研究

针对6~8mm厚2219–T87铝合金拉锻式摩擦塞焊工艺进行了研究。结果表明,塞棒/塞孔及砧板成形孔结构及轴向载荷、焊接转速、进给速度等焊接工艺参数均对焊接质量有重要影响。采用圆弧形塞棒、圆柱形塞孔、阶梯锥形底孔的砧板能够改善塞孔附近材料的流动方向和受力条件,进而消除未焊合缺陷。焊接转速7000r/min、焊接压力20~30kN、轴向拉锻力20~30kN、进给速度1.5mm/s是较优的焊接工艺范围。焊接接头中母材侧的热力影响区软化最为明显,硬度值为79.9HV。在优化参数下,焊接接头的抗拉强度可达365MPa,延伸率6%。     

缝焊接头疲劳强度降低系数和寿命分散系数的研究

为了研究发动机机匣的低循环疲劳寿命，本文根据机匣的实际情况，设计了焊搭接试件，进行对１Ｃｒ１８Ｎｉ９Ｔｉ材料缝焊搭接接头的疲劳性能测试，并用统计分析的方法得到Ｓ－Ｎ曲线和Ｐ－Ｓ－Ｎ曲线，及其缝焊接头的疲劳强度降低系数和疲劳寿命分散系数，与该材料的光滑试件对比，其结果可以看出，缝焊接头的疲劳强度大大低于光滑试件，而其疲劳寿命分散系数比光滑试件好。     

先进的焊接技术─—摩擦搅动焊

摩擦搅动焊是新近发明的一种先进焊接技术,它采用非熔化固态焊接,利用局部产生的摩擦热生成连续的固相焊缝,用它可以焊接传统上认为“不能焊接”的合金和实现不同类金属的焊接。本文简要介绍摩擦搅动焊的焊接工艺、焊缝性能、设备及应用。     

随焊激冷对LY12CZ铝合金焊接热裂纹倾向影响的研究

采用自行研制的柔性接触式激冷器,分别以液氮和水作为冷却介质,研究了随焊激冷对ＬＹ１２ＣＺ铝合金焊接热裂纹率的影响。同时结合跨焊缝两侧横向位移的实时测量结果,分析了随焊激冷影响热裂纹率的作用机理。研究表明,采用随焊激冷工艺能够有效地降低ＬＹ１２ＣＺ铝合金的焊接热裂纹率,其原因在于随焊激冷显著增加了ＢＩＲ（脆性温度区间）内表观横向收缩量。